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Mtu Aero Engines Gmbh patents


Recent patent applications related to Mtu Aero Engines Gmbh. Mtu Aero Engines Gmbh is listed as an Agent/Assignee. Note: Mtu Aero Engines Gmbh may have other listings under different names/spellings. We're not affiliated with Mtu Aero Engines Gmbh, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "M" | Mtu Aero Engines Gmbh-related inventors


 new patent  Sealing system for an axial turbomachine and axial turbomachine

The present invention relates to a sealing system for an axial turbomachine for a gas turbine, including a rotor with a radially outward arranged shroud and a housing that surrounds the rotor, wherein a gap is arranged between the shroud and the housing, and wherein the gap is bounded by a seal, which is joined to the housing, and at least one sealing tip arranged at the shroud opposite to the seal, for reducing the flow losses through the gap. At the downstream end region of the seal, another static sealing tip, which is joined to the housing, is arranged for influencing the flow through the gap and/or for influencing the flow downstream of the static sealing tip. ... Mtu Aero Engines Gmbh

 new patent  Turbomachine blade system

A turbomachine blade system, in particular for a compressor or turbine stage of a gas turbine, which includes at least one blade, in particular a moving or guide blade, and at least one moving body for reducing the vibrations of this blade, at least one area of a guide for guiding the body and/or at least one area of a supporting structure for resiliently mounting the body and/or at least one area of the body being or becoming generatively manufactured together with at least one area of the blade, in particular of a vane and/or blade root and/or a shroud situated thereon.. . ... Mtu Aero Engines Gmbh

Seal system for a guide blade system of a gas turbine

A seal system for a moving blade system of a gas turbine includes a seal carrier including a ring section extending in the axial direction and the circumferential direction, on which a radially inner seal element is situated. A first flange section and a second flange section extend outwardly from the ring section in the circumferential direction and the radial direction and are situated at a distance from each other in the axial direction. ... Mtu Aero Engines Gmbh

Ellipsoidal inner central blade storage space

An inner ring according to the invention or an inner ring segment according to the invention for an adjustable guide vane assembly comprises a plurality of uptakes, each for the bearing of an adjustable guide vane. The uptakes here each form an essentially ellipsoidally shaped uptake space for a guide vane head of the respective guide vane. ... Mtu Aero Engines Gmbh

Pulse body module with bearing protection

An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.. ... Mtu Aero Engines Gmbh

Method of making a molybdenum alloy having a high titanium content

The invention relates to method of making a molybdenum alloy which has a high titanium content and further comprises silicon and/or boron. The method comprises subjecting to pressureless sintering or sintering under pressure in an inert gas atmosphere a mixture of one or more powders (i) of an alloy of mo and ti and, optionally, one or more additional metals x and/or (i′) powders of mo and of tin, and (ii) one or more powders comprising one or more powders of silicides of mo and/or ti and/or (iii) one or more powders of nitrides which comprise si3n4 powder and/or bn powder.. ... Mtu Aero Engines Gmbh

Apparatus for laser materials processing

An apparatus for laser materials processing including a laser (4) for generating a laser beam and a laser head (5) which is movable along at least one spatial direction and is connected to the laser via a light guide, and which emits a laser beam (7) capable of processing a material. The present invention also relates to an apparatus for selective laser melting or selective laser sintering having an apparatus for laser materials processing.. ... Mtu Aero Engines Gmbh

Rotor stage for a turbomachine, rotor drum, and rotor

A rotor stage (200) for a turbomachine, including a plurality of rotor blades (9), a rotor main body (7) having at least two rotor arms (3) and a balancing assembly (1) for balancing the rotor stage (200). The rotor arm (3) configured downstream from the rotor main body (7) features the balancing assembly (1). ... Mtu Aero Engines Gmbh

Seal arrangement for a mid turbine frame of a gas turbine

The seal arrangement for a mid turbine frame of a gas turbine, especially an aircraft gas turbine, includes a tubular fluid duct, especially an oil duct, which extends along an axial direction, a bearing sleeve surrounding the fluid duct radially outside and in the peripheral direction, and at least one seal ring arranged between fluid duct and bearing sleeve in the radial direction, this ring being arranged around the fluid duct. The seal ring is taken up at least partly in a groove provided in the bearing sleeve.. ... Mtu Aero Engines Gmbh

Simulation method for developing a production process

A method for developing a production process where a component is built up layer by layer by melting on powder material using a radiation source, and the melted-on powder material is subsequently solidified; in a first phase of the method, material-specific properties of a material being ascertained as a function of process parameters in a multiscale, physically based simulation chain independently of a component geometry; and, in a second phase of the method, taking into account the process parameters and the material-specific properties, an additive build-up of the component using this material being simulated which ensures minimal distortions and internal stresses. Also described is an installation for the generative production of components that includes a processing unit that is adapted for implementing a method for developing a production process.. ... Mtu Aero Engines Gmbh

Positioning element with recesses for a guide vane arrangement

The invention relates to a positioning element for a guide vane arrangement of a guide vane stage of a gas turbine, with at least one base section curved in the peripheral direction; a plurality of uptake openings arranged next to each other in the peripheral direction on the base section, whose aperture axis runs substantially in the radial direction and which are designed to take up a respective radially inner guide vane section; a coupling section provided on the base section, which is or can be coupled to a seal carrier of a seal arrangement. According to the invention, it is proposed that at least one recess is provided in the base section, which is arranged between two neighboring uptake openings and runs from inside to outside at least in the radial direction.. ... Mtu Aero Engines Gmbh

Inner ring for an annular guide vane assembly of a turbomachine

An inner ring (14) for an annular guide vane assembly (10) of a turbomachine, which inner ring enables variable guide vanes (12) to be rotatably supported is provided. The inner ring (14) includes a first and a second securing ring (16a, 16b) which are connected together by at least one securing element (18) extending axially with respect to a centerline (m) of the inner ring (14). ... Mtu Aero Engines Gmbh

Liner element for a turbine intermediate case

A liner element of a hot-gas-conveying duct of a turbine intermediate case of a gas turbine, in particular of an aircraft gas turbine, the liner element includes a central portion having at least one first reinforcement portion projecting in a direction away from the duct and extending substantially straight between an axial forward end and an axial rearward end; at least one of the two axial ends being adjoined by a second reinforcement portion projecting in a direction away from the duct and extending inclinedly or curvedly relative to the straight-line extent of the first reinforcement portion; the first reinforcement portion and the second reinforcement portion together forming a reinforcing element; the entire reinforcing element being disposed within the outer surface of the central portion, in particular in such a way that the reinforcing element is spaced apart from the first connecting portion and from the second connecting portion.. . ... Mtu Aero Engines Gmbh

Liner element of a turbomachine and correspoding connection assembly

A liner element (10), in particular a heat shield element or casing element, of a turbomachine, in particular a gas turbine, including a fastening portion (12) having at least one bore (14-1, 14-2) through which a connection unit (42) having, in particular a pin-type or bolt-type form, is introducible along a bore axis (ba); a liner portion (16) that adjoins the fastening portion (12); the fastening portion (12) and the liner portion (16) being formed in one piece, and having an annular or ring segment shape. The bore (14-1, 14-2) is provided in a depression (24-1, 24-2) formed in the fastening portion (12), the depression (24-1, 24-2) being essentially formed concentrically about the bore (14-1, 14-2).. ... Mtu Aero Engines Gmbh

01/18/18 / #20180017081

Variable turbomachine vane cascade

A variable vane cascade for a turbomachine, in particular for a compressor stage or turbine stage of a gas turbine, having at least one first vane, in particular guide vane that has a first distance from a circumferentially adjacent vane, at least one second vane, in particular guide vane that has at least one second distance from at least one circumferentially adjacent vane that is smaller than the first distance, and an actuating device, in particular for jointly and/or reversibly adjusting the first and second vane from a first position where at least one airfoil cross section of the first vane and an airfoil cross section of the second vane each have a first stagger angle, into a second position where these airfoil cross sections have second stagger angles, the second stagger angle of the first vane differing from the second stagger angle of the second vane, in particular being larger than the second stagger angle of the second vane.. . ... Mtu Aero Engines Gmbh

01/18/18 / #20180016936

Device and method for service-life monitoring

In the case of a device and a method for monitoring the service life of an engine or of a turbine having a compressor blisk and/or a turbine blisk, momentary stresses of blisk substructures, such as the blade (1), the disk (2), and the join region (3) between the blade (1) and the disk (2), are calculated on the basis of operating parameters that are measured in the course of engine or turbine operation; and accumulated damage to the individual substructures, that was caused by the momentary stresses, is estimated.. . ... Mtu Aero Engines Gmbh

01/18/18 / #20180016918

Shrouded blade of a gas turbine engine

The present invention relates to an improved cast-to-size gas turbine blade comprising a blade tip shroud with a stiffening rib extending outwardly from the section of the outer side of the shroud platform located between the upstream sealing fin and the upstream edge. The stiffening rib having substantially planar top surface in form of a trapezium, and two sloping sidewalls extending between the upstream sealing fin and the upstream edge on each side of the top surface and connecting said top surface with adjacent surface of the outer side of the shroud platform. ... Mtu Aero Engines Gmbh

01/18/18 / #20180016668

High temperature resistant tial alloy, production method therefor and component made therefrom

Described is α-tial alloy which, besides titanium, comprises 42 to 48 at. % aluminum, 3 to 5 at. ... Mtu Aero Engines Gmbh

12/28/17 / #20170370238

Thickened radially outer annular portion of a sealing fin

A blisk 10 for a gas turbine includes a rotor blade row 12 extending around a central axis x and, axially spaced therefrom and extending coaxially therewith, at least one annular sealing fin 11. The sealing fin has a radially outer annular portion 111 that is thickened as compared to a radially more inward annular portion 113. ... Mtu Aero Engines Gmbh

12/28/17 / #20170370234

Blade or guide vane with raised areas

The invention relates to a blade or vane, particularly of a turbine stage of a gas turbine, in particular of an aircraft gas turbine, having a blade or vane root and a blade or vane element joined to the blade or vane root, wherein the blade or vane element has a pressure side and a suction side, and wherein the blade or vane root has at least one raised region on its radial outer side facing the blade or vane element. It is proposed according to the invention that the blade or vane has a first raised region on the pressure side and a second raised region on the suction side, wherein the highest point of the first raised region is disposed essentially directly adjacent to the pressure side, and the highest point of the second raised region is disposed essentially directly adjacent to the suction side.. ... Mtu Aero Engines Gmbh

12/14/17 / #20170356590

Pipe arrangement with support sections on the outer pipe

The invention relates to a pipe arrangement (10) with a fluid-carrying inner pipe (12) and an outer pipe (14) that surrounds the inner pipe (12), wherein spacers (20, 24) are arranged between the inner pipe (12) and the outer pipe (14) in such a way that a gap (16) is formed between the inner pipe (12) and the outer pipe (14), wherein the outer pipe (14) is joined at its first axial end section (18) in a material-bonded or cohesive manner to a first spacer (20), which is joined to the inner pipe (12) in a material-bonded manner, and wherein the outer pipe (14) is arranged at its second axial end section (22) at least partially with a radial spacing (26) to a second spacer (24), which is joined to the inner pipe (12) in a material-bonded manner.. . ... Mtu Aero Engines Gmbh

12/14/17 / #20170356293

Balancing weight for a rotor blade of a turbine stage

A balancing weight for a rotor blade of a turbine stage of a gas turbine, in particular of an aircraft gas turbine; including a first bent fastening portion that is couplable to an axial leading edge of a shroud of the rotor blade, a second fastening portion that is couplable to an axial trailing edge of the shroud, and a middle portion that joins the first fastening portion and the second fastening portion; the second fastening portion assumes a first position relative to the first fastening portion prior to a mounting of the balancing weight on the rotor blade, and a second position relative to the first fastening portion subsequently to the mounting of the balancing weight on the rotor blade; in the second relative position, the middle portion or/and the second fastening portion being deformed, in particular plastically deformed.. . ... Mtu Aero Engines Gmbh

12/07/17 / #20170350270

Turbine ring and turbomachine

A turbine ring of a turbomachine is described, having a one-piece ring structure which has an outer ring which is continuous in the circumferential direction of the turbine ring and has a fastening section for fastening the turbine ring on a housing section of the turbomachine, an inner ring which is segmented in the circumferential direction and has a plurality of inner ring segments which are mutually displaceable in the circumferential direction for guiding the hot gas and has front sealing segments and rear sealing segments, as seen in the axial direction of the turbine ring, these sealing segments being spaced a distance apart from one another in the axial direction and extending between the inner ring and the outer ring, as well as a turbomachine having such a turbine ring.. . ... Mtu Aero Engines Gmbh

11/30/17 / #20170341182

Device for inductive heating of a component

The invention relates to a device for inductive heating of a component 10, having a component placement unit for the component, an induction coil, with which the component can be heated inductively, at least in regions, an electrical lead for the induction coil, and a positioning unit, at which the induction coil is arranged in such a way that it can be brought into different relative arrangements with respect to the component placement unit by way of the positioning unit, wherein the electrical lead is guided over a contact, which is formed by contact surfaces that rest against each other and are shifted in position in relation to each other in the contact position when the induction coil is shifted in position by means of the positioning unit.. . ... Mtu Aero Engines Gmbh

11/30/17 / #20170341175

Method and device for additively manufacturing at least a portion of a component

A method for additively manufacturing at least a portion of a component, in particular a component of a turbomachine. The method includes the following steps: a) depositing at least one powder layer of a component material in powder form layer by layer onto a component platform in the region of a buildup and joining zone; b) locally solidifying the powder layer by selectively irradiating the same using at least one high-energy beam in the region of the buildup and joining zone, forming a component layer; c) lowering the component platform by a predefined layer thickness; and d) repeating steps a) through c) until completion of the component portion or of the component. ... Mtu Aero Engines Gmbh

11/23/17 / #the present invention relates to a method for producing a blade or blade arrangement of a turbomachine, which features the following steps:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

11/23/17 / #20170335695

Turbomachine blade assembly

A turbomachine blade assembly including a turbomachine blade (1), in particular for a gas turbine, and at least one tuning element container including a housing (10) attached to the turbomachine blade and an insert (20) disposed in a recess (11) of this housing. A wall (20; 21) of the insert spaces apart two first cavities (31), which each accommodate at least one tuning element (40) provided for impacting contact with the housing (10) and the insert (20).. ... Mtu Aero Engines Gmbh

11/23/17 / #20170335436

Additive manufacturing of high-temperature components from tial

Disclosed is a process for producing a component from a tial alloy by layer-by-layer deposition of powder on a substrate and/or an already produced semifinished product. The component has a proportion of x at % of aluminum which is in the range from about 34 to about 47 at % of aluminum, the powder having a proportion of x+1 at % to x+6 at % of aluminum. ... Mtu Aero Engines Gmbh

11/09/17 / #20170321611

Low noise compressor rotor for geared turbofan engine

A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. ... Mtu Aero Engines Gmbh

11/09/17 / #20170321557

Impulse element module for a turbomachine

An impulse element module for a turbomachine, in particular a turbine stage of a gas turbine, preferably an aircraft gas turbine, including a single-unit receptacle component having a base and side walls that extend peripherally thereon, the side walls and the base bounding a receiving space; a single-unit insert component having a form that is inserted into receiving space of receptacle component; together, the receptacle component and the insert component accommodated therein being designed to define a plurality of spaced apart cavities; and an impulse element, in particular a sphere, being accommodated in each cavity; and a single-unit sealing component that is joined in a material-to-material bond to the receptacle component in a way that allows the receiving space to be sealed and the insert component to be surrounded by the receptacle component and the sealing component.. . ... Mtu Aero Engines Gmbh

10/26/17 / #20170306784

Blade outer air seal for a gas turbine engine

A blade outer air seal (boas) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The boas includes a trough disposed on the radially inner face and an abradable seal received within the trough. ... Mtu Aero Engines Gmbh

10/12/17 / #20170292403

Guide vane segment

A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (a; b) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (l) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.. . ... Mtu Aero Engines Gmbh

10/12/17 / #20170292387

Guide vane segment

A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (v) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (b) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (a) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.. . ... Mtu Aero Engines Gmbh

10/05/17 / #20170284213

Seal segment assembly including mating connection for a turbomachine

A seal segment assembly for a turbomachine, in particular a gas turbine, including a first seal carrier and a second seal carrier, that are adjacently disposed in the circumferential direction, the first seal carrier having a first carrier base and at least one first sealing member that is joined to the first carrier base, and the second seal carrier having a second carrier base and at least one second sealing member that is joined to the second carrier base, the first sealing member and the second sealing member being formed by a plurality of cavities, that are adjacently disposed in the circumferential direction and in the axial direction, in particular evenly spaced, the cavities extending in the radial direction from the particular carrier base. The first carrier base and the second carrier base are intercouplable or are intercoupled in the circumferential direction by a mating connection assembly.. ... Mtu Aero Engines Gmbh

10/05/17 / #20170284212

Seal carrier for a turbomachine, in particular a gas turbine

A seal carrier for a turbomachine, in particular a gas turbine, including a carrier base and at least one seal member, the at least one seal member being connected to the carrier base, and the at least one seal member being formed by a plurality of cavities arranged adjacent one another, in particular in a regular fashion, in the circumferential direction and the axial direction, the cavities extending from the carrier base in the radial direction, is provided. At least one stiffening element on the carrier base, the stiffening element extending along the circumferential direction and at least partially covering the at least one seal member at one of its axial end regions is provided.. ... Mtu Aero Engines Gmbh

10/05/17 / #20170282246

Method and device for the additive manufacture of at least one component region of a component

The invention relates to a method for the additive manufacture of at least one region (16) of a component. Here, at least the following steps are carried out: a) layer-wise application of at least one powder-form component material onto a component platform in the region of a build-up and joining zone (14); b) layer-wise and local solidifying of the component material by selective exposure of the component material by at least one high-energy beam (12) in the region of the build-up and joining zone (14), with the formation of a component layer (15); c) layer-wise lowering of the component platform by a pre-defined layer thickness; and d) repeating steps a) to c) until the component region (16) or the component has been completely fabricated.. ... Mtu Aero Engines Gmbh

09/28/17 / #20170276023

Method for manufacturing a housing of a turbomachine and turbomachine housing

The invention relates to a method for manufacturing a housing of a turbomachine, in particular a gas turbine. The method comprises at least the steps: providing a housing blank (10), manufacturing a housing element (14), producing an assembly opening (12) corresponding to the housing element (14) in the housing blank (10), arranging the housing element (14) in the assembly opening (12), and joining the housing element (14) to the housing blank (10) by means of a welding method. ... Mtu Aero Engines Gmbh

09/21/17 / #the invention relates to a method for producing a mistuning component. the method comprises the following steps:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

09/21/17 / #20170268532

Vane ring, inner ring, and turbomachine

Described is an adjustable guide vane ring of a turbomachine having an axially split inner ring, on which a brush seal is configured, an inner ring for a guide vane ring of this kind, as well as a turbomachine.. . ... Mtu Aero Engines Gmbh

09/21/17 / #20170268378

Adjustable guide vane for turbomachine

Disclosed is an adjustable guide vane for a turbomachine, especially for a turbine stage or compressor stage of a gas turbine, which comprises a vane airfoil for deflecting a working fluid of the turbomachine and which is produced at least partially from a second material, and at least one first vane section which is produced from a first material which is different from the second material.. . ... Mtu Aero Engines Gmbh

09/21/17 / #20170268356

Guide vane plate with a chamfered and a cylindrical edge region

A guide vane (10, 10′) according to the invention for a guide vane ring of a turbomachine has a vane element as well as a guide vane plate (12) for its support on an inner ring (20). The guide vane plate has a cover surface (14) facing the vane element, a base surface (17) lying opposite to the cover surface, and an edge surface (15) joining the cover and base surfaces. ... Mtu Aero Engines Gmbh

09/21/17 / #20170266886

Camera-based determining of roughness for additively manufactured components

The invention relates to a method and a device for the additive manufacturing of components by the layer-by-layer joining of powder particles to one another and/or to an already created pre-product or substrate, via the selective interaction of the powder particles with a high-energy beam (13) to create a layer, wherein a formed layer (14) is captured using a camera (6), wherein a contour of the deposited layer (14) is determined from an image of the deposited layer captured by the camera (6), and wherein the roughness of the surfaces of the formed component is determined from the contour.. . ... Mtu Aero Engines Gmbh

09/14/17 / #the present invention relates to a method for producing and/or repairing wear-stressed recesses or openings on components (22) of a turbomachine, especially of elements of a flow passage boundary, and also to corresponding components, wherein the method comprises:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

09/14/17 / #the invention relates to a method for producing a blade (10) for a turbo machine, especially for an aviation engine, comprising at least the following steps:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

09/07/17 / #20170252860

Micro-forging by a generative manufacturing process

The present invention relates to a device as well as a method for the additive manufacture of components by deposition of material layers by layer-by-layer joining of powder particles to one another and/or to an already produced pre-product or substrate, via selective interaction of the powder particles with a high-energy beam, wherein, for smoothing a surface of the component being produced running crosswise to the deposited material layers in between the deposition of two layers of the component, the complete edge region of the last layer that is applied and that runs along a surface of the component being produced is compacted in a direction of action that has a directional component parallel to the build-up direction of the layers, and/or at least one edge region (19) of a surface of the component (3′) is also compacted.. . ... Mtu Aero Engines Gmbh

08/24/17 / #20170241291

Turbine intermediate casing and sealing arrangement of ceramic fiber composite materials

A turbine intermediate casing for a gas turbine comprising outer and inner wall elements arranged in series in circumferential direction and delimiting a flow passage for exhaust gas; strut fairing elements arranged in radial direction between respective outer and inner wall elements; an outer casing encompassing the outer and inner wall elements; and an annular mounting structure encompassing a bearing region of a shaft of the gas turbine. The strut fairing elements comprise a space for accommodating carrier elements which extend from the annular mounting structure through the flow passage to the outer casing exhaust gas flowing through the flow passage being directed by the strut fairing elements around the carrier elements. ... Mtu Aero Engines Gmbh

08/24/17 / #20170241282

Sealing system made of ceramic fiber composite materials

A sealing system including a first component at least partially manufactured from ceramic fiber composite materials, a second component at least partially manufactured from ceramic fiber composite materials, and a sealing element accommodated between the first component and the second component. The sealing element is designed as a sealing strip. ... Mtu Aero Engines Gmbh

08/24/17 / #20170241279

Guide vane segment for a turbomachine

The invention relates to a guide vane segment for an aircraft engine, having at least one guide vane element, having at least one flange formed in a radial extension direction (r) of the guide vane element and at least one positioning member projecting from the flange in the radial extension direction (r), and at least one seal carrier, which is arranged at the flange and is aligned relative to the guide vane element by way of the positioning member, wherein the flange has a supporting surface on which the seal carrier is supported, wherein a partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle (α) that is different from a zero angle.. . ... Mtu Aero Engines Gmbh

08/24/17 / #20170241272

Hybrid blade for turbomachines

Disclosed is a blade for a turbomachine, comprising an outer shell and an inner core which is at least partially enclosed by the outer shell and has a higher porosity than the outer shell. The outer shell is formed by a ceramic body or a body made of a ceramic matrix composite material, and the inner core is formed by a fiber-reinforced ceramic or a fiber-reinforced ceramic matrix composite material.. ... Mtu Aero Engines Gmbh

08/24/17 / #20170241271

Component of a molybdenum alloy and method for forming an oxidation protection layer therefor

Disclosed is a method for improving the high-temperature stability of a component, in particular a blade of a turbomachine, formed at least partially from a molybdenum alloy that, besides molybdenum, silicon, boron and titanium, comprises iron and/or yttrium. The method comprises depositing a diffusion barrier layer formed from technically pure molybdenum or tungsten or being an alloy based on molybdenum and/or tungsten at least on an outer surface, which comprises the molybdenum alloy, of the component, and depositing silicon on the diffusion barrier layer to form molybdenum silicides and/or tungsten silicides.. ... Mtu Aero Engines Gmbh

08/24/17 / #20170241005

Heat treatment process for components composed of nickel-based superalloys

Disclosed is process for producing a component of a nickel-based superalloy in which a semifinished part of the component is subjected to a solution heat treatment at a temperature from 1300° c. To 1350° c. ... Mtu Aero Engines Gmbh

08/17/17 / #20170234163

Connection system for housing elements of a turbine intermediate casing

A connection system for a hot gas-conducting annular duct of a turbine intermediate casing of a gas turbine includes a first housing element, a second housing element situated next to the first housing element in the circumferential direction, and a fastening unit configured for connecting the first housing element and the second housing element to one another at edges adjacent to one another in the circumferential direction, the fastening unit including a clamping element which is mounted on the one housing element with the aid of a connection, the clamping element resting on a clamping surface provided on the other housing element in such a way that the other housing element is accommodated between the clamping element and the one housing element. It is provided that the top side of the clamping surface facing the clamping element has a clamping surface contour—relative to a longitudinal section which extends along, in particular essentially in parallel to the adjacent edges of the two housing elements—which is designed in such a way that it thwarts a rotation of the clamping element about an axis of the connection.. ... Mtu Aero Engines Gmbh

08/10/17 / #disclosed is a repair method for guide blades of a gas turbine. the method comprises:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

08/10/17 / #20170226897

Housing element for an intermediate turbine housing

A housing element (12) for an intermediate turbine housing of a gas turbine, in particular an aircraft gas turbine; the housing element (12) being installable or installed in the intermediate turbine housing radially outwardly, in each case between a plurality of circumferentially spaced struts; the housing element (12) having a planar form and, relative to the radial outer side (16) thereof, a plurality of depressions (18c), is provided. On the radial inner side (32, 34) thereof, the housing element (12) has at least one recess (26) that is configured outside of the regions in which depressions (18c) are formed on the radial outer side (16).. ... Mtu Aero Engines Gmbh

08/10/17 / #20170226887

Guide vane system for a turbomachine

The invention relates to a guide vane system for a turbomachine with at least one guide vane, which can be rotatably mounted around an adjustment axis and is arranged with a radially inner end region in a corresponding recess of an inner ring, wherein the arrangement of the guide vane on the inner ring is secured by a securing element in a form-fitting manner. For an especially advantageous securing of this arrangement, it is provided that the securing element is designed as an oblong element, which is arranged at least in a recess and/or through-opening of the radially inner end region of the guide vane directed in the peripheral direction of the turbomachine and is arranged at least in a recess and/or through-opening of the inner ring directed in the peripheral direction of the turbomachine. ... Mtu Aero Engines Gmbh

08/10/17 / #20170226621

Thermal barrier coating with high corrosion resistance

Disclosed is a thermal barrier coating system for components of a turbomachine, especially for high temperature-stressed or hot gas-stressed components of a turbomachine, comprising a ceramic coating of fully or partially stabilized zirconium oxide, and an oxide cover coating which comprises aluminum and at least one element from the group lanthanum, magnesium, silicon, calcium and sodium. The aluminum oxide exists at least partially as free α-al2o3. ... Mtu Aero Engines Gmbh

08/03/17 / #20170218792

Rotor-stator combination for an axial turbomachine and aero engine

Disclosed is a rotor-stator combination for an axial turbomachine which comprises a rotor having an impeller and a stator having a diffuser and a casing section. The combination features a one-piece structural design in manufacture and the casing section has at least one radial access which is prepared and designed for installation steps and/or machining steps for rotor sections and/or stator sections which are arranged inside the casing section. ... Mtu Aero Engines Gmbh

08/03/17 / #20170218773

Blade cascade and turbomachine

A blade cascade of a turbomachine having at least one shape variation of a blade situated on the blade side in the proximity of a side wall and extending downstream, and at least one side wall contouring of the side wall or at least one second shape variation of an adjacent blade near the side wall, as well as a turbomachine, are disclosed.. . ... Mtu Aero Engines Gmbh

08/03/17 / #20170218768

Blade of a turbomachine having blade root thermal insulation

Disclosed is an arrangement for fastening a blade root of a blade of a turbomachine in a blade root receptacle, with a blade having a blade root of a first material and with a blade root receptacle of a second material, wherein a thermal barrier layer is arranged between the blade root and the blade root receptacle. Further disclosed is a blade having a blade root with a thermal barrier layer and also a method for operating a turbomachine, in which a blade having a blade root is received in a blade root receptacle and a blade root temperature which is above the blade root receptacle temperature is set.. ... Mtu Aero Engines Gmbh

07/20/17 / #the invention relates to a turbomachine including:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

07/20/17 / #a method for ascertaining the concentration of at least one material in a powder mixture used as starting material for the production of a component in an additive production method, comprising:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

07/20/17 / #20170204975

Method for manufacturing a brush seal with inclined bristle

The invention relates to a method for manufacturing a brush seal with inclined bristles. In order to be able to manufacture these brush seals in an especially cost-effective manner, at least the following steps are provided: provision of a brush blank with at least one metal thread or wire packing fastened at or in at least one wire core; local, at least partial heating of at least the wire core and/or a subregion of the thread or wire packing adjacent to the wire core, by a current flow through the wire core; bending of the thread or wire packing relative to the wire core for producing of the inclined position of the bristles of the brush seal. ... Mtu Aero Engines Gmbh

07/06/17 / #20170191415

Low noise compressor and turbine for geared turbofan engine

A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction configured to effect a reduction in a speed of the fan relative to an input speed from the first turbine rotor. Each of the compressor rotor and the first turbine rotor includes a number of blades in each of a plurality of blade rows, the number of blades configured to operate at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for at least a majority of the blade rows of the first turbine rotor, but does not hold true for any of the blade rows of the compressor rotor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute.. ... Mtu Aero Engines Gmbh

06/29/17 / #20170184128

Low noise turbine for geared turbofan engine

A gas turbine engine has a fan section including a fan. A turbine section has a first turbine and a second turbine. ... Mtu Aero Engines Gmbh

06/22/17 / #20170175756

Guide vane for a turbomachine, guide vane cascade, and method for manufacturing a guide vane or a guide vane cascade

A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade.. ... Mtu Aero Engines Gmbh

06/15/17 / #20170167522

Fastening assembly

A fastening assembly having a component flange (10), in particular of a turbomachine, having at least one bore (11) in which a sleeve (30) is placed that extends through a bolt (20) which has a head (21) that is axially secured between a rim (12) of the bore and a component flange-mounted axial limit stop (13).. . ... Mtu Aero Engines Gmbh

06/15/17 / #20170167282

Component joint

A component joint including a turbomachine component (10) having at least one component flange (11); a mating turbomachine component (20) connected thereto and having at least one mating component flange (21); and at least one seal (30) to provide a seal against an overpressure (p2−p1) on the component side, the at least one seal (30) having a sealing surface (31) that engages into a groove (12) of the turbomachine component (10), the groove (12) being disposed on a mating-component-flange-facing side of the component flange (11) and having a contact surface (13) for sealingly axially supporting the sealing surface (31).. . ... Mtu Aero Engines Gmbh

06/15/17 / #20170165928

Method of repairing damage of aircraft engine components made of weldable thermoplastic materials

Disclosed is a method of repairing damage of an aircraft engine component made of or comprising weldable thermoplastic material, which method comprises welding of the weld filler material into an initially prepared damaged area. Also disclosed are the use of plastic welding technique for repairing damaged aircraft engine components made of weldable thermoplastic materials.. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159676

Gas turbine compressor

A compressor for a gas turbine, in particular of an aircraft engine, having a plurality of arrays (10-25) of flow-directing elements that are serially disposed in a through flow direction from a compressor inlet to a compressor outlet (1, 2); at least one upstream, mistuned array (20) of flow-directing elements and at least one downstream, mistuned array (22) of flow-directing elements each having at least two types of flow-directing elements that differ structurally from one another; and at least 80%, in particular at least 95% of the rotor blades (45) of a furthest downstream rotor blade array (25) that, in the through flow direction, is configured downstream of the downstream, mistuned array (22) of flow-directing elements, being mutually identically constructed.. . ... Mtu Aero Engines Gmbh

06/08/17 / #20170159609

Turbofan aircraft engine with reduced noise emission

The invention relates to a turbofan aircraft engine that comprises a primary duct including a combustion chamber; a first turbine disposed downstream of the combustion chamber; a compressor disposed upstream of the combustion chamber and coupled to the first turbine; and a second turbine disposed downstream of the first turbine and coupled to a fan for feeding a secondary duct of the turbofan aircraft engine. The bypass ratio of the inlet area of the secondary duct to the inlet area of the primary duct is at least 7 and the second turbine comprises at least two stages. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159573

Reduced noise turbofan aircraft engine

The invention relates to a turbofan aircraft engine that comprises a primary duct including a combustion chamber; a first turbine disposed downstream of the combustion chamber; a compressor disposed upstream of the combustion chamber and coupled to the first turbine; and a second turbine disposed downstream of the first turbine and coupled to a fan for feeding a secondary duct of the turbofan aircraft engine. The bypass ratio of the inlet area of the secondary duct to the inlet area of the primary duct is at least 7 and the second turbine comprises at least two stages. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159492

Housing structure of a turbomachine with heat protection shield

The present invention relates to a turbomachine with a housing structure as well as a corresponding housing structure an outer housing wall (1) and an inner housing wall, which, passing around the flow duct of the turbomachine at a distance from each other, surround the outer side of the flow duct, wherein the inner housing wall of the housing structure is formed by an oas (outer air seal, outer fluid seal) (2) in the region of the rotating blades of the turbomachine, which rotate around an axial axis of the turbomachine, wherein a heat protection shield (9) is constructed between the outer housing wall (1) and the oas (2). The heat protection shield has a plurality of spacers (10) in the peripheral direction that are distanced from one another in the peripheral direction and are situated additionally to and in the radial direction outside of the heat protection element (11).. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159482

Run-in coating for an outer air seal of a turbomachine

The invention relates to a run-in coating (10) for an outer air seal of a turbomachine, especially of an aero engine, comprising a substrate (12) of segmented form which carries a honeycomb structure (14) with an run-in surface (15) to face rotor blades of a rotor of the turbomachine, wherein a radial thickness of the honeycomb structure (14) varies in the circumferential direction. The invention furthermore relates to an outer air seal for a turbomachine and also to a turbomachine with an outer air seal.. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159472

Stabilized sealing ring for a turbomachine

Disclosed is a sealing ring (13, 13′, 13″) for a turbomachine, which is constructed so as to be fastened at a radially inner region of a plurality of guide vanes (20) and rotate around a rotor shaft (30). The sealing ring comprises a ring part (15) that extends in the axial direction and has a plurality of stiffened portions (18a, 18b) in succession in the peripheral direction. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159471

Inner ring and guide vane cascade for a turbomachine

An inner ring 10 according to the invention for a guide vane cascade of a turbomachine has a radially outer inner ring surface 11 as well as a plurality of bearing mounts 12 for a respective guide vane plate 21a of a guide vane 20. The bearing mounts 12 each have an opening 13 in the outer inner ring surface 11 as well as a bottom face 14 lying radially opposite the opening. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159470

Inner ring system for an inlet guide vane cascade of a turbomachine

The invention relates to an inner ring system for an inlet guide vane cascade (14) of a turbomachine (10). The inner ring system comprises an intermediate casing (28) for accommodating structural loads and an inner ring (26), which is divided axially into a first ring segment (24a) and a second ring segment (24b), which together form recesses (22) for bearing radially inner end portions (18) of guide vanes (16) of the inlet guide vane cascade (14), wherein at least the second ring segment (24b) is fixed in place on the intermediate casing (28) by screw connection). ... Mtu Aero Engines Gmbh

06/08/17 / #20170159467

Guide vane ring casing for a turbomachine and turbomachine having a guide vane ring casing

An inventive guide vane ring casing 10′ for a turbomachine has a casing surface 11 extending about and facing a central axis a, the casing surface having formed therein a plurality of receiving recesses 12′, each intended to receive a vane disk 21a of a guide vane 20. A radial cut-out 16 is formed between at least two adjacent receiving recesses 12′ in the casing surface 11 and connects the two receiving recesses. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159466

Guide vane segment with radial securing elements

The invention relates to a guide vane segment (10) for a gas turbine comprising at least one radially outer shroud (14) and one radially inner shroud (12), which extend along a respective arc and together form an annular segment, wherein, in the radial direction (rr) between the outer shroud (14) and the inner shroud (12), a plurality of guide vanes (16) are arranged adjacent to one another in the peripheral direction (ur) and are joined to the inner shroud (12) and to the outer shroud (14) in a material-bonded manner and, in particular, are joined in a one-piece manner, wherein, in an axial lengthwise direction (ar), the outer shroud (14) comprises an axially front end wall element (22) and an axially rear end wall element (24) in such a way that the outer shroud (14) and the two end walls (22, 24) form a tub-like profile in lengthwise section.. . ... Mtu Aero Engines Gmbh

06/08/17 / #20170159465

Guide vane segment for a turbomachine

The invention relates to a guide vane cluster (10) for a turbomachine, in particular for a turbojet engine, having at least two vanes (14) that are joined together by way of at least one common platform (12, 16) for the radial delimiting of a flow channel of the turbomachine, wherein each vane (14) has a vane element (17) with a suction side (18) and a pressure side (20) that are joined together by a leading edge (22) and a trailing edge (24), wherein the at least two vanes (14) have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.. . ... Mtu Aero Engines Gmbh

06/08/17 / #20170159464

Run-up surface for the guide-vane shroud plate and the rotor-blade base plate

A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface k1 whose cone axis coincides with the axis of rotation a of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface k2 whose cone axis coincides with the axis of rotation a of a rotor shaft 30.. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159461

Stacking of rotor blades on centroids

A rotor blade for a gas turbine, in particular an aircraft gas turbine, having a blade root element and a stream deflection portion adjoining the blade root element (12) in the longitudinal direction of the blade (rr); respective centroids (24) of blade cross-sectional areas of the stream deflection portion residing on a common stacking axis (26). It is provided that, starting from a first centroid (24) of a first blade cross-sectional area adjoining the blade root element (12), the stacking axis (26) extend within a cone (28) whose apex resides within the first centroid (24), and whose cone height (kh) extends orthogonally to the plane of the blade cross-sectional area; the angle (β) of the cone (28) being greater than 0° and smaller than or equal to 4°; preferably greater than or equal to 0.5° and smaller than or equal to 2°.. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159458

Method for inspecting a rotor blade unit

A method for inspecting a rotor blade unit of a gas turbine, the rotor blade unit including a radially outwardly disposed outer shroud connected by a material-to-material bond to a radially inwardly adjoining rotor blade, the rotor blade having an airfoil including a pressure side and a suction side, as well as an axial leading edge and an axial trailing edge which interconnect the pressure side and the suction side. The method includes: providing a rotor blade unit; processing the outer shroud at its axially forward or axially aft side, the side selected to be processed being the one that has a greater distance from the adjacent axial leading edge or axial trailing edge of the rotor blade, a contact surface being formed by processing the selected side; providing the rotor blade unit having the contact surface in a measuring device, in particular a measuring device for determining the torsion or twist of the rotor blade unit about an axis.. ... Mtu Aero Engines Gmbh

06/08/17 / #20170159444

Blade channel, blade cascade and turbomachine

A blade channel of a turbomachine that is delimited in the circumferential direction of the turbomachine by a pressure side of an airfoil and by an opposite suction side of an adjacent airfoil that, in the radial direction of the turbomachine, is delimited by two opposing side walls, and whose extent in the axial direction of the turbomachine is delimited by leading edges and by trailing edges of airfoils; at least one of the side walls being provided with localized contours, of which at least two are formed as elevations and at least two as depressions; a saddle surface being formed between the contours that, in one rotation, alternately merges into an elevation and a depression; a blade cascade having such blade channels, as well as a turbomachine having such a blade cascade.. . ... Mtu Aero Engines Gmbh

06/08/17 / #20170159443

Contoured surface annular section of a gas turbine

The invention relates to a blade or vane ring for a gas turbine having a plurality of blades or vanes that are arranged next to one another in the peripheral direction (ur), wherein blades or vanes have a flow segment extending essentially in the radial direction, these blades or vanes having a convex suction side, a concave pressure side, a leading edge and a trailing edge, wherein the suction side and the pressure side are joined together by the leading edge and the trailing edge, wherein the blades or vanes transition into an annular segment of the blade or vane ring radially inside and/or radially outside, wherein annular segment connects a first blade or vane (12) and a second blade or vane, which are adjacent to one another, between the suction side of the first blade or vane and the pressure side of the second blade or vane.. . ... Mtu Aero Engines Gmbh

06/08/17 / #20170157704

Determining a scanning speed of a manufacturing device for the additive production of a component

The invention provides a method for determining a scanning speed of a high-energy beam of a manufacturing device for the additive production of a component, in particular a component of a turbomachine, comprising the steps of guiding of the high-energy beam, which is generated by a radiation source of the manufacturing device, over a surface; detection of the path, irradiated during a predetermined period of time with the high-energy beam, on the surface, by recording respective brightness values on the surface by a detection device during the predetermined period of time; calculation of the scanning speed as a function of the predetermined period of time and of the detected irradiated path by an analysis device. The invention further relates to a method for operating a manufacturing device and to a manufacturing device for the additive production of a component of a turbomachine.. ... Mtu Aero Engines Gmbh

06/01/17 / #20170152857

Casing for a turbomachine, installation safeguard and turbomachine

Disclosed is a casing of a turbomachine which comprises at least a first casing portion comprising a first material having a first coefficient of thermal expansion and a second casing portion comprising a second material having a second coefficient of thermal expansion. The second casing portion comprises a casing structuring with flow-guiding elements and is connected in a force-fitting manner to the first casing portion by a radial press fit. ... Mtu Aero Engines Gmbh

06/01/17 / #20170152758

Locking element for a borescope opening of a gas turbine

A locking element for a borescope opening of a gas turbine is disclosed. The borescope opening includes a radially inner opening edge facing a gas-carrying annular channel of the gas turbine where the locking element includes a main section and a locking section connected to the main section. ... Mtu Aero Engines Gmbh

05/18/17 / #20170138209

Device and method for influencing the temperatures in inner ring segments of a gas turbine

A device for influencing the temperatures in inner ring segments of a gas turbine is provided, which includes in the circumferential direction of the gas turbine, at least one outer shell assembly having a plurality of outer ring segments and at least one inner shell assembly having a plurality of inner ring segments. The inner ring segments are equal to or greater in number than the outer ring segments. ... Mtu Aero Engines Gmbh

05/18/17 / #20170136696

Rapid manufacturing method and device for the same comprising oppositely-directed protective gas streams parallel to the powder layer

The invention relates to a device and a method for the additive manufacture of components through the layered bonding of powder particles to one another and/or to a semi-finished product or substrate already produced, using selective interaction of the powder particles with a high-energy beam, wherein, during the bonding of the powder particles into a layer made of powder particles with the aid of the high-energy beam, a gas flow, which has a flow direction having a directional component directed at least partially parallel to the layer of powder particles, is provided across the layer of powder particles and/or the bonding region in the layer of powder particles, wherein the directional component of the gas flow directed at least partially parallel to the layer of powder particles during the bonding of the powder particles in a layer is generated in at least two directions, which have oppositely directed directional components.. . ... Mtu Aero Engines Gmbh

05/18/17 / #20170136574

Method and device for the quality assurance of at least one component during the production thereof by a generative production process

The invention relates to a method for the quality assurance of at least one component (14) during the production thereof, wherein the production takes place by means of at least one additive manufacturing process, which comprises the following steps: building up the component (14) layer by layer, and themographically recording at least one image of each individual layer applied. In order to facilitate nondestructive crack detection in a metal component (14) during the production process (inspection by means of an online process), at least some of the layers applied are subjected to a controlled heat treatment below the melting point of the material of the component before the thermographic recording of the associated image, wherein the heat treatment causes the last layer applied to radiate heat which, if at least one crack develops in the layer, exhibits a characteristic heat profile at the crack.. ... Mtu Aero Engines Gmbh

05/11/17 / #20170129061

Arrangement for joining elements of turbomachines

The present invention relates to an arrangement 1, comprising a first turbomachine element 10 with a first turbomachine element through-opening 12, a second turbomachine element 20, a sliding element 30 with a sliding element through-opening 32 that is arranged, at least in part, in the first turbomachine element through-opening 12, a sleeve 40 that engages through the sliding element through-opening 32 along a through-axis d, and a fastening member 50 that engages through the sleeve 40 for fastening the sleeve 40 to the second turbomachine element 20. Furthermore, the invention relates to a method for fastening the first turbomachine element 10 to the second turbomachine element 20, a turbomachine with the above-mentioned arrangement 1, and use of this arrangement 1.. ... Mtu Aero Engines Gmbh

05/04/17 / #20170122256

Turbine blade and aircraft engine comprising same

The invention relates to a blade for use in a turbine of an aircraft engine. The blade is made of (a) a mo-based alloy strengthened by intermetallic silicides or (b) a ni-based single crystal superalloy. ... Mtu Aero Engines Gmbh

05/04/17 / #20170122218

Low noise compressor and turbine for geared turbofan engine

A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine, a compressor, and a gear reduction positioned between the fan and the first turbine. Each of the compressor and the first turbine includes a number of blades in each of a plurality of blade rows, the number of blades rotatable at least some of the time at a rotational speed in operation, and the number of blades and the rotational speed being such that the following formula holds true for the plurality of the blade rows of the first turbine, but does not hold true for any of the blade rows of the compressor rotor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute.. ... Mtu Aero Engines Gmbh

05/04/17 / #20170122217

Low noise compressor and turbine for geared turbofan engine

A gas turbine engine has a fan including a plurality of fan blades, a turbine section having a first turbine, a compressor, and a gear reduction positioned between the fan and the first turbine. Each of the compressor and the first turbine includes a number of blades in each of a plurality of blade rows, the number of blades rotatable at least some of the time at a rotational speed in operation, and the number of blades and the rotational speed being such that the following formula holds true for at least a majority of the blade rows of the first turbine, but does not hold true for any of the blade rows of the compressor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute.. ... Mtu Aero Engines Gmbh

05/04/17 / #20170122118

Ductile compensation layer for brittle components

Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. In the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. ... Mtu Aero Engines Gmbh

05/04/17 / #20170122107

Turbine rotor for a low pressure turbine of a gas turbine system

The invention relates to a turbine rotor for a low pressure turbine of a gas turbine system, in particular of an aero engine, comprising four bladed rotor disks which are arranged in series in the flow direction, wherein at least two of the rotor disks consist at least in part of a nickel-based superalloy which has the following chemical composition: fe 4%, co 8.5%, cr 15.7%, mo 3.1%, w 2.7%, al 2.25%, ti 3.4%, nb 1.1%, b 0.01%, c 0.015%, zr 0.03% and remainder ni. The invention further relates to a low pressure turbine for a gas turbine system, and to a gas turbine system.. ... Mtu Aero Engines Gmbh

04/27/17 / #20170114644

Rotating blade

The present invention relates to a rotating blade for a turbomachine, in particular a compressor stage or a turbine stage of a gas turbine, particularly of an aircraft engine, having a blade element (10) for deflecting the flow, with a pressure side and a suction side (11), these sides being joined by a leading edge and a trailing edge (12, 13), wherein a stacking axis (s) of the blade element (10), in the radial direction (r) over a radius r from a root of a blade element at r=0 to a tip of a blade element at r=h, has a course x(r) in a first downstream direction (x) perpendicular to the radial direction (r) and parallel to a principal axis of the turbomachine and has a course y(r) in a second direction (y) perpendicular to the radial direction (r) and to the first direction (x).. . ... Mtu Aero Engines Gmbh

04/20/17 / #20170107843

Module for a gas turbine

The invention relates to a module for a gas turbine comprising a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient, a rotationally symmetrical component for guiding hot gas of a second material having a linear thermal expansion coefficient which is lower than the first coefficient, at least one annular structure arranged radially within the component, and at least three struts having a radially inner end secured on the outer casing and a radially outer end secured on the annular structure. The component also comprises at least one first fixing which is free in radial direction and fixed in axial direction and arranged between the component and the outer casing and/or the annular structure, as well as at least three second fixings having an elastic effect in radial, axial and/or circumferential direction and being arranged between the component and the strut and/or the annular structure.. ... Mtu Aero Engines Gmbh

04/13/17 / #the present invention relates to a component of a turbomachine with a repair layer and a method for repairing wear-damaged components (1, 10) of a turbomachine, in particular of elements of a flow duct boundary, having the following method steps:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

04/13/17 / #20170101887

Containment for a continuous flow machine

A containment for a continuous flow machine, in particular for a gas turbine, is disclosed. The containment has at least one annular housing with at least one axial section of lesser radial wall thickness and at least one axial section adjacent thereto of greater wall thickness, where the housing is designed and constructed so that the section of greater wall thickness is at a distance in the axial direction of the continuous flow machine from a trailing edge of a guide vane lying downstream in the direction of flow of the continuous flow machine, and extends downstream in the direction of flow of the continuous flow machine over a leading edge of the next downstream guide vane.. ... Mtu Aero Engines Gmbh

04/13/17 / #20170100800

Repair method for sealing segments

Disclosed is a method for repairing a sealing segments, formed at least partially in a monocrystalline fashion, of a flow channel wall of a turbomachine. At first a repair region of the sealing segment is established, independently of defects which may be present, and subsequently a part of a base material of the sealing segment is removed in the repair region. ... Mtu Aero Engines Gmbh

04/06/17 / #20170096906

Sealing fin armoring and method for the production thereof

A method for coating a sealing fin (2) on a component of a turbomachine, in particular on a blade tip (6) of a blade (1) of a turbomachine, with armoring (3, 30, 300), and to a corresponding component, in which method a blade (1) having at least one sealing fin (2) and a slurry which comprises particles of mcraly or particles for forming an mcraly layer (31), where m is nickel and/or cobalt, are provided, the slurry is applied onto the sealing fin and dried, and the sealing fin with the applied slurry is subjected to an aluminizing process so that the mcraly layer comprises an al-rich sublayer (32).. . ... Mtu Aero Engines Gmbh

03/30/17 / #an apparatus and a method for producing and/or repairing a component. the method comprises:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

03/16/17 / #the present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point σ and the aspect ratio arax, which is defined by the quotient between average channel height (h) and average chord length (lax), satisfy the condition

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

03/09/17 / #a device and a method for producing a blade airfoil from a workpiece which comprises at least two gaps and at least one blank arranged between the two gaps, wherein the blank comprises two opposite lateral faces which are bounded by a base, a top and a first and a second edge. the method comprises:

Mtu Aero Engines Ag

. . ... Mtu Aero Engines Gmbh

03/09/17 / #20170067487

Turbomachine blade

A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber (10) in which at least one impulse element (11) is disposed with play, at least one second impact chamber (20) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber (10) along a first matrix axis (a) and in which at least one impulse element (21) is disposed with play, and at least one third impact chamber (30) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber (10) along a second matrix axis (b) transversely to the first matrix axis (a) and in which at least one impulse element (31) is disposed with play, the first matrix axis (a) and an axis of rotation (r) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.. . ... Mtu Aero Engines Gmbh

03/09/17 / #20170067366

Device for bounding a flow channel of a turbomachine

A device for bounding a flow channel of a turbomachine, comprising a wall that, viewed in the circumferential direction of the turbomachine, has a multiplicity of wall segments, and including a multiplicity of outer segments that extend radially around the outside of the wall segments; each wall segment having a uniformly curved first cross-sectional contour; each outer segment including at least one second cross sectional contour that deviates from the uniformly curved first cross-sectional contour; the second cross-sectional contour having a multiplicity of depressions that are inwardly directed in the radial direction of the gas turbine; at least a portion thereof being attached to the radially outer surface of a corresponding wall segment.. . ... Mtu Aero Engines Gmbh

03/09/17 / #20170066084

Thermography for quality assurance in an additive manufacturing process

The invention relates to a method and a device for the quality assurance of at least one component (14) during its production, wherein production is achieved by means of an additive manufacturing method with at least one processing laser (22), said method comprising the following steps: —layered assembly of the component (14), —thermographic recording of a plurality of images, over a defined period, of at least one component region (17) in the laser beam by means of at least one recording sensor (18), —detecting a temporal change in the heat distribution in a molten-pool-free component region, wherein the occurrence of a defect, (e.g. A crack, foreign material, a pore, a bonding fault or similar) in the uppermost component layer or beneath same is detected on the basis of a characteristic temporal change in the heat distribution at the defect (30).. ... Mtu Aero Engines Gmbh

03/02/17 / #20170058383

Rhenium-free nickel base superalloy of low density

The invention relates to a substantially rhenium-free nickel base alloy showing a high creep resistance and relatively low density which comprises in % by weight: aluminum from 3.0 to 7.7, cobalt from 0 to 16.8, chromium from 3 to 11.8, molybendum from 3.1 to 11.3, tantalum from 0 to 3.9. In addition to nickel and unavoidable impurities this alloy may further comprise one or more of titanium, tungsten, carbon, phosphorus, copper, zirconium, silicon, hafnium, yttrium, niobium, and germanium.. ... Mtu Aero Engines Gmbh

02/23/17 / #20170051382

Optimized nickel-based superalloy

A nickel-based alloy for high-temperature applications, in particular for use in turbomachines, which has a chemical composition as set forth in the claims, wherein the ratio of the fractions of ta to al in percent by weight is greater than or equal to 1 and less than or equal to 2, and wherein the ratio of the fractions of co to w in percent by weight is greater than or equal to 2 and less than or equal to 5.. . ... Mtu Aero Engines Gmbh

02/16/17 / #20170044910

Bladed gas turbine rotor

The present invention relates to a bladed rotor for a gas turbine, with a body and a plurality of rotating blades where contact regions of a cylindrical surface of the body and front faces of the rotating blades are joined together cohesively. At least one of these contact regions and/or at least one of these front faces has at least one blind hole, in which at least one impulse body is arranged with play of movement and which is sealed and rotating blades are joined with the cylindrical surface. ... Mtu Aero Engines Gmbh

02/09/17 / #20170037741

Guide vane ring element for a turbomachine

The present invention relates to a guide vane ring element (10) for a turbomachine, such as a gas turbine, with at least one drilled hole (30) for the at least partial uptake of a flange (21) of a rotatable guide vane (20), wherein an edge of the drilled hole on the vane element side is designed convexly along the edge in a first circumferential portion (31a, 31b) and, in particular, has a radius (r).. . ... Mtu Aero Engines Gmbh

02/09/17 / #20170036284

Method for machining a workpiece having an irregular edge

A method for machining a workpiece is provided. An electrode is moved linearly in the direction of the workpiece to cause material to be removed from the workpiece, at least one end of a surface of the workpiece running obliquely to a guide edge of the electrode machining this surface. ... Mtu Aero Engines Gmbh

02/02/17 / #20170030196

Gas turbine

The present invention relates to a gas turbine, in particular an aircraft engine gas turbine having a shaft and a bladed turbine rotor joined therewith that has a first rotor segment which has a downstream rotating cascade of the turbine rotor and bounds a first space in the radial direction, this first space communicating with a first gas passage disposed in the shaft, and has a second rotor segment axially adjacent to the first rotor segment, which has at least one second rotating cascade of the turbine rotor and bounds in the radial direction a second space axially adjacent to the first space, this second space communicating with a second gas passage, wherein the first rotor segment has at least one first discharge opening for the discharge of gas from the first space upstream of the furthest downstream rotating cascade.. . ... Mtu Aero Engines Gmbh

02/02/17 / #20170030195

Method for repairing a gas turbine blade having at least one cavity

Disclosed is a method of repairing gas turbine blade which has at least one cavity and which has damage in the region of its blade tip, which damage extends through a rim region and a core region of the blade into the at least one cavity. The method comprises at least: a) removing blade material at least in the region of the damage, forming at least one cutaway reaching into the cavity; b) replacing the damaged region by filling the at least one cutaway with a repair material using at least one generative production method; and c) finishing the blade at least in the region of the at least one refilled cutaway. ... Mtu Aero Engines Gmbh

01/19/17 / #20170016132

Method for the electroplating of tial alloys

The present invention relates to a method for the coating of a surface of a tial alloy, in which at least one layer is electroplated on the surface of the tial alloy, wherein the surface of the tial alloy is subjected to an at least two-step surface treatment for the formation of a roughened surface, this treatment comprising at least one electrochemical processing and at least one electroless chemical processing.. . ... Mtu Aero Engines Gmbh








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