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Mtu Aero Engines Ag patents


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

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


 new patent  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... Mtu Aero Engines Ag

 new patent  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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

Simulation 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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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,... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

Bearing assembly, in particular for a turbomachine, and turbomachine having such a bearing assembly

A bearing assembly (2) is provided, in particular for a turbomachine, including: an inner bearing race (3); an outer bearing race (4) having at least one cooling channel (15) formed within it or in its outer surface; rolling elements (7) made of ceramic and disposed between the inner bearing race... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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. % niobium, 0.05 to 1 at. % molybdenum, 0.2 to 2.2 at. % silicon, 0.2 to 0.4 at. % carbon, 0.05 to 0.2 at. % boron, and optionally tungsten, zirconium and hafnium,... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

Device and 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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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 %... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

Method of producing blades or blade arrangements of a turbomachine with erosion protection layers and correspondingly produced component

Furthermore, the invention relates to correspondingly produced blades or blade arrangements.... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives... Mtu Aero Engines Ag

Turbomachine blade assembly

The present invention relates to a turbomachine blade or vane arrangement having a first turbomachine blade or vane (10), a second turbomachine blade or vane (20) adjacent to it, and at least one tuning element guide housing (30) with at least one cavity, in which at least one tuning element... Mtu Aero Engines Ag

Method for producing a blade for a turbomachine

Disclosed is a method for producing a blade for a turbomachine, in particular for an aero engine. The method comprises providing at least one blade airfoil with a first platform region and at least one blade root with a second platform region and joining the blade airfoil and the blade... Mtu Aero Engines Ag

Method for producing a blade for a turbomachine

Also disclosed is a blade which is obtainable and/or obtained by this method.... Mtu Aero Engines Ag

Guide vane ring for a turbomachine

A guide vane ring for a turbomachine minimizes a leakage flow that passes through a recess (11) into which a guide vane disk is inserted. It has a guide vane row having a plurality of guide vanes (20), each having a vane airfoil (24) and a vane disk (21), as... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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

A method for manufacturing at least a metallic portion of a component: a) depositing metallic material layer by layer onto at least one building platform; b) locally fusing and/or sintering the material layer by layer by supplying energy by at least one high-energy beam in the region of a buildup... Mtu Aero Engines Ag

Coupling assembly for components of ceramic matrix composites for a turbine center frame

A coupling assembly, including a first component and a second component overlapping one another in a join region; a joining device allowing the first component and the second component to rest against each other clampingly in the join region; the joining device including a clamp resting on the first component... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

09/21/17 / #20170266745

Method of producing an impulse mistuning component

d) joining the lid (32, 32′) and the container (36), wherein joining is carried out by soldering/brazing.... Mtu Aero Engines Ag

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,... Mtu Aero Engines Ag

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,... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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 Ag

09/14/17 / #20170259385

Component having wear-protected openings and recesses and process for the production thereof

at least partially heat-treating the component (22) for soldering the molded repair part (15) onto the component.... Mtu Aero Engines Ag

09/14/17 / #20170260865

Process for producing a blade for a turbomachine

A further aspect of the invention relates to a blade which is obtainable and/or is obtained by means of such a method.... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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. and a precipitation heat treatment at a temperature range from 900° C. to 1150° C.... Mtu Aero Engines Ag

08/24/17 / #20170241271

Component of a molybdenum alloy and 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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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 Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

08/10/17 / #20170226860

Repair turbine blades

applying material and removing material by machine on the guide blade, such that the calculated target geometry is produced.... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

07/20/17 / #20170203387

Method for ascertaining a concentration of at least one material in a powder for an additive production method

ascertaining by an analysis unit the concentration of at least one material in the powder mixture depending on the detected at least one brightness value and at least one predetermined reference brightness value for a concentration and/or a concentration range of the material.... Mtu Aero Engines Ag

07/20/17 / #20170204740

Turbomachine stage

.... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

Patent Packs
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... Mtu Aero Engines Ag

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. A gear reduction between the fan and the first turbine includes an epicycle gear train. The gear reduction is configured to receive an input from the first turbine... Mtu Aero Engines Ag

06/22/17 / #20170175756

Guide vane for a turbomachine, guide vane cascade, and 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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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)... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

Patent Packs
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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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. The locking... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

05/25/17 / #20170145837

Method of making a bladed rotor for a turbomachine

A method of making a bladed rotor for a turbomachine, in particular for an aircraft engine, is disclosed. The method comprises the steps a) providing a rotor base of the rotor, b) providing at least one blade root, c) providing at least one blade body, d) making at least one... Mtu Aero Engines Ag

05/25/17 / #20170145842

Vane segment with peripheral securing

The invention relates to a guide vane segment for an aircraft gas turbine, comprising at least a radially outer shroud and a radially inner shroud, which extend along a respective circular arc and together form a ring segment, wherein, in the radial direction, between the outer shroud and the inner... Mtu Aero Engines Ag

05/25/17 / #20170145846

Brush sealing arrangement for a turbomachine, installation securing arrangement and turbomachine

Disclosed is a brush sealing arrangement for a turbomachine, comprising at least one stator, one rotor and one brush seal. The brush seal comprises at least one brush element and one ring for receiving the brush element. The brush sealing arrangement seals a gap between the stator and the rotor.... Mtu Aero Engines Ag

05/25/17 / #20170146017

Method, compressor and turbomachine

Disclosed is a method for operating a compressor of a turbomachine, in which, when viewed in the direction of a main flow, a slowly dropping degree of reaction being raised in one compressor area more quickly than previously dropped and the raised degree of reaction then being reduced again in... Mtu Aero Engines Ag

05/25/17 / #20170146025

Compressor, method and turbomachine

Described is a method for operating a compressor of a turbomachine, in which, when considered in the direction of a main flow, an, in particular, radially averaged degree of reaction has dropped in a front compressor area from a maximum to a minimum, is held constant or virtually constant across... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

05/18/17 / #20170136696

Rapid manufacturing 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... Mtu Aero Engines Ag

05/18/17 / #20170138209

Device and 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... Mtu Aero Engines Ag

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,... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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... Mtu Aero Engines Ag

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. An aircraft engine and in particular, a turbofan aircraft engine including a corresponding turbine blade... Mtu Aero Engines Ag








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