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Rolls royce Deutschland Ltd x26 Co Kg
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Rolls royce Deutschland Ltd & Co Kg patents


      
Recent patent applications related to Rolls royce Deutschland Ltd & Co Kg. Rolls royce Deutschland Ltd & Co Kg is listed as an Agent/Assignee. Note: Rolls royce Deutschland Ltd & Co Kg may have other listings under different names/spellings. We're not affiliated with Rolls royce Deutschland Ltd & Co Kg, we're just tracking patents.

ARCHIVE: New 2015 2014 2013 2012 2011 2010 2009 | Company Directory "R" | Rolls royce Deutschland Ltd & Co Kg-related inventors


Method for balancing and assembling a turbine rotor

Rolls-royce Deutschland Ltd & Co Kg

Method for balancing and assembling a turbine rotor

Search recent Press Releases: Rolls royce Deutschland Ltd & Co Kg-related press releases
Count Application # Date Rolls royce Deutschland Ltd & Co Kg patents (updated weekly) - BOOKMARK this page
12015005290802/26/15 new patent  Bleed duct assembly for a gas turbine engine
22015004719102/19/15Method for balancing and assembling a turbine rotor
32015002712701/29/15Combustion chamber tile of a gas turbine
42015003078701/29/15Laser depositioning device and producing a component by direct laser depositioning
52015001330701/15/15Turbofan jet engine
62015001695001/15/15Device and discharging sealing air in a turbofan engine
72015001699401/15/15Aircraft engine
82015000753101/08/15Jet engine with at least one oil separator, through which an air-oil-volume flow can be guided
92015001038501/08/15Gas turbine with high-pressure turbine cooling system
102015000024601/01/15Jet engine with at least one oil separator
112014037355512/25/14Accessory mounting for a gas turbine engine
122014036655512/18/14Accessory mounting for a gas turbine engine
132014036327712/11/14Assembly for a fluid flow machine
142014036328312/11/14Shroud arrangement for a fluid flow machine
152014035614312/04/14Assembly for a fluid flow machine
162014035614412/04/14Assembly for a fluid flow machine
172014035245012/04/14Method for determining a machining result during surface machining of components
182014031814810/30/14Burner seal for gas-turbine combustion chamber head and heat shield
192014031815010/30/14Removable swirler assembly for a combustion liner
202014031457810/23/14Securing segment for the vibration damping of turbine blades and rotor device
212014023803008/28/14Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes
222014024186008/28/14Flight gas turbine with a first rotatable shaft
232014023408008/21/14Device and bleeding compressor air in a turbofan engine
242014023409608/21/14Turbomachine component with an erosion and corrosion resistant coating manufacturing such a component
252014016159106/12/14Lubricant system
262014015044206/05/14Gas turbine centripetal annular combustion chamber and flow guidance
272014014414505/29/14Gas turbine combustion chamber
282014014414605/29/14Tile fastening arrangement of a gas-turbine combustion chamber
292014014082005/22/14Aeroengine sealing arrangement
302014014189405/22/14Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
312014013050105/15/14Combustion chamber tile of a gas turbine
322014013096405/15/14Method for manufacturing a shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
332014012428905/08/14Nozzle with guiding devices
342014012700105/08/14Gas-turbine engine with a telescopic air inlet in the engine lining
352014012700305/08/14Stator vane adjusting device of a gas turbine
362014012701005/08/14Nozzle with guiding devices
372014012700505/08/14Method for producing a component, component and turbomachine having a component
382014011602505/01/14Aeroengine thrust reverser arrangement
392014011602605/01/14Aeroengine thrust reverser arrangement
402014011988305/01/14Bleed flow passage
412014011994205/01/14Turbine rotor blade of a gas turbine
422014009653304/10/14Bearing chamber venting system for an aircraft engine and providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber
432014007953903/20/14Turbine blade of a gas turbine with swirl-generating element and its manufacture
442014006492803/06/14Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
452014006495203/06/14Assembly of an axial turbomachine and manufacturing an assembly of this type
462014005056102/20/14Oil supply supplying oil for a turboprop engine
472014003372302/06/14Unknown
482014003373102/06/14Method for fuel temperature control of a gas turbine
492014002653401/30/14Oil supply system for an aircraft engine
502014002659201/30/14Assembly for a jet engine of an aircraft
512014002670001/30/14Accessory gearbox device for a jet engine
522014003010601/30/14Compressor blade of a gas turbine as well as manufacturing said blade
532014003010701/30/14Decoupled compressor blade of a gas turbine
542014003010901/30/14Low-modulus gas-turbine compressor blade
552013032687612/12/13Method for repairing compressor or turbine drums
562013031894512/05/13Aviation gas turbine thrust reversing device
572013030640111/21/13Sound absorber for a gas turbine exhaust cone, and the production thereof
582013030640211/21/13Method for the production of a sound absorber, especially for a gas turbine exhaust cone
592013030640311/21/13Method for the production of a sound absorber, especially for a gas turbine exhaust cone
602013030909111/21/13Oil supply system for a propeller turbine engine
612013030214311/14/13Cooling device for a jet engine
622013026642410/10/13Stator vane adjusting device of a gas turbine
632013025973210/03/13Method for producing engine components with a geometrically complex structure
642013023038309/05/13Aircraft gas turbine with adjustable fan
652013021998208/29/13Rolling tool device
662013021639108/22/13Method for the production of a one-piece rotor area and one-piece rotor area
672013020575308/15/13Aircraft gas turbine thrust-reversing device
682013020578808/15/13Unknown
692013020667608/15/13Measuring device having a pressure sensor
702013019904008/08/13Device and treatment of high-pressure turbine blades of a gas turbine
712013019918708/08/13Gas-turbine combustion chamber having non-symmetrical fuel nozzles
722013020208808/08/13Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
732013019223208/01/13Annular combustion chamber of a gas turbine
742013019561008/01/13Noise-reduced turbomachine
752013018670707/25/13Unknown
762013018022707/18/13Fastening element and de-icing device of an aircraft gas-turbine engine
772013016045906/27/13Accessory mounting for a gas turbine
782013016605606/27/13Method for selecting a geometry of a blade
792013015662606/20/13Method for manufacturing a part by metal injection moulding
802013015700006/20/13Component and turbomachine having a component
812013013957806/06/13Pressure-measuring device and pressure-measuring a turbomachine
822013014246706/06/13Method and device for adjusting the bearing play in a ceramic hybrid bearing
832013012950405/23/13Bearing device and turbomachine having a bearing device
842013012950505/23/13Bearing device and turbomachine having a bearing device
852013012411405/16/13Method for determining a flow behaviour of a medium
862013009817904/25/13Accessory gearbox device for a jet engine
872013009170404/18/13Method for repairing rotor blades
882013008690804/11/13Gas turbine combustion chamber arrangement of axial type of construction
892013005571603/07/13Gas-turbine combustion chamber with a holding means of a seal for an attachment
902013005709303/07/13Generator and accessory gearbox device with a generator
912013004262702/21/13Combustion chamber head of a gas turbine with cooling and damping functions
922013004509302/21/13Method for the manufacture of a component for high thermal loads, a component producible by this method and an aircraft engine provided with the component
932013002596201/31/13Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element
942013000814701/10/13Aircraft gas turbine with variable bypass nozzle
952013001124601/10/13Gas-turbine aircraft engine with structural surface cooler
962012032535412/27/12Apparatus and the creation of an impingement jet generating annular swirls as well as turbomachine with an apparatus of this type
972012032147712/20/12Rotor device for a jet engine with a disk wheel and several rotor blades
982012030465812/06/12Segment component in high-temperature casting material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and the manufacture of an annular combustion chamber
992012029880211/29/12De-icing device of an aircraft gas-turbine engine
1002012028513811/15/12Aircraft gas-turbine engine with oil cooler in the engine cowling
1012012028835911/15/12Gas-turbine engine with bleed-air tapping device
1022012028208211/08/12Gas-turbine balancing device
1032012026642610/25/12Method and surface strengthening and/or smoothing of an integrally bladed rotor area of a jet engine
1042012026961910/25/12Fluid-flow machine
1052012024711010/04/12Device for mixing fuel and air of a jet engine
1062012025131210/04/12Stator of an axial compressor stage of a turbomachine
1072012025132410/04/12Rotor of an axial compressor stage of a turbomachine
1082012024058309/27/12Segmented combustion chamber head
1092012024059509/27/12Combustion chamber head with holding means for seals on burners in gas turbines
1102012022239609/06/12Jet engine device with a bypass duct
1112012020472308/16/12Centrifugal oil separator for an aircraft engine
1122012017458807/12/12Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
1132012014839606/14/12Fluid-flow machine - blade with hybrid profile configuration
1142012012552305/24/12Repair a sandwich-like component
1152012011797305/17/12Gas-turbine combustion chamber with a cooling-air supply device
1162012009477704/19/12Drive shaft, in particular radial shaft for a gas-turbine engine
1172012007666503/29/12Cooled turbine blades for a gas-turbine engine
1182012006702503/22/12Bloom mixer for a turbofan engine
1192012006710103/22/12Forging tool
1202012004503202/23/12Method for filmless radiographoc inspection of components
1212012003378702/09/12Method for radiographic inspection of components
1222012003433302/09/12Injection moulding tool for the manufacture of a hybrid component
1232012001766301/26/12Method for the manufacture of a workpiece with defined surface
1242012002080201/26/12Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
1252012001182701/19/12Bleed air outlet in the bypass duct of a turbofan engine
1262012001478001/19/12Fan downstream guide vanes of a turbofan engine
1272012000661401/12/12Gas-turbine exhaust cone
1282011030896612/22/11Method for manufacturing blisks
1292011028874011/24/11Engine synchronization method
1302011027168011/10/11Lean premix burner of a gas-turbine engine provided with a concentric annular central body
1312011027168111/10/11Lean premix burner of a gas-turbine engine provided with a flow-guiding element
1322011027176511/10/11Method and the detection of defects in the raceways of bearing shells and in the rolling elements of ceramic hybrid bearings
1332011027183711/10/11Centrifugal oil separator for an aircraft engine
1342011025596410/20/11Bypass duct of a turbofan engine
1352011021978209/15/11Aerodynamically shaped supporting and/or fairing element in the bypass duct of a gas-turbine engine
1362011021517209/08/11Aircraft engine with optimized oil heat exchanger
1372011020945809/01/11Aircraft gas turbine engine
1382011021194709/01/11Bypass duct of a turbo engine
1392011017984407/28/11Method and surface strengthening of blisk blades
1402011018249907/28/11Method for determining the surface coverage obtained by shot peening
1412011017399007/21/11Intermediate casing for a gas-turbine engine
1422011014622306/23/11Arrangement for the discharge of exhaust air separated from the lubricating oil de-aeration system of a gas-turbine engine
1432011014622406/23/11Arrangement for the discharge of oil-venting air on a gas-turbine engine
1442011013992506/16/11Arrangement for the suspension of a jet engine to a supporting structure
1452011012772806/02/11Sealing rings for a labyrinth seal
1462011012113605/26/11Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device
1472011011690805/19/11Gas turbine engine with an arrangement for measuring the shaft rotation speed
1482011007007403/24/11Gas turbine with a shroud and labyrinth-type sealing arrangement
1492011003866602/17/11Engine shaft of hybrid design
1502011002709102/03/11Axial-flow compressor, more particularly one for an aircraft gas-turbine engine
1512011001688301/27/11Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine
1522011001105801/20/11Turbofan engine
1532011001109301/20/11Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall
1542011001403701/20/11Axial-flow compressor with a flow pulse generator
1552011001404001/20/11Fluid flow machine with blade row group
1562011001405701/20/11Engine blade with excessive leading edge loading
1572011001405801/20/11Propeller
1582011000523301/13/11Combustion chamber head of a gas turbine
1592011000585801/13/11Noise-reduced aircraft engine and reducing noise emissions of an aircraft engine
1602010030362912/02/10Fluid flow machine with a blade row group featuring a meridional edge distance
1612010028777211/18/10Method for surface strengthening and smoothening of metallic components
1622010028864811/18/10Method and etching the surfaces of integrally bladed rotors
1632010025819910/14/10Intake cone in a fiber compound material for a gas-turbine engine
1642010025901310/14/10Abradable labyrinth seal for a fluid-flow machine
1652010023295409/16/10Bypass duct of a turbofan engine
1662010022390509/09/10Scoop of a running-gap control system of an aircraft gas turbine
1672010022434809/09/10Method for the manufacture of an ejector nozzle tube
1682010021228508/26/10Turboprop propulsion unit with pusher propeller
1692010021548108/26/10Running-gap control system of an aircraft gas turbine
1702010019258808/05/10Method for the provision of a cooling-air opening in a wall of a gas-turbine combustion chamber as well as a combustion-chamber wall produced in accordance with this method
1712010017525607/15/10Method for the manufacture of the blade tips of rotor wheels made in blisk design
1722010017609707/15/10Arrangement for the repair of the blades of blisk drums by means of laser deposition welding
1732010015552606/24/10Aircraft with tail propeller-engine layout
1742010016110706/24/10Machine control for a numerically controlled machine tool
1752010014802706/17/10Sensor bracket for at least one sensor on a gas turbine
1762010014844906/17/10Segmented sealing lips for labyrinth sealing rings
1772010015069606/17/10Fan casing for a jet engine
1782010013924106/10/10Flow divider for a fan engine
1792010013927806/10/10Method and the operation of a turboprop aircraft engine provided with pusher propellers
1802010014023006/10/10Method for the manufacture of a welded rotor for a gas-turbine engine
1812010014314006/10/10Fluid flow machine with sidewall boundary layer barrier
1822010012658905/27/10Device for the prevention of high oil tank pressures under negative g conditions
1832010012666205/27/10Method for the manufacture of hybrid components for aircraft gas turbines
1842010012965105/27/10Hybrid component for a gas-turbine engine
1852010012251805/20/10Oil system heating for aircraft gas turbines
1862010012448705/20/10Multi-vane variable stator unit of a fluid flow machine
1872010010918405/06/10Method for the manufacture of an engine shaft
1882010011170205/06/10Hub cone for an aircraft engine
1892010011317005/06/10Engine shaft for a gas-turbine engine
1902010011317105/06/10Engine shaft in the form of a fiber-composite plastic tube with metallic driving and driven protrusions
1912010009852704/22/10Fluid flow machine with peripheral energization near the suction side
1922010009853004/22/10Compressor for a gas turbine
1932010009853604/22/10Fluid flow machine with running gap retraction
1942010005111203/04/10Intake cone for a gas-turbine engine
1952010003463702/11/10Fluid flow machine
1962010002421402/04/10Method for the manufacture of metallic components
1972010002131001/28/10Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
1982010001495601/21/10Fluid flow machine featuring a groove on a running gap of a blade end
1992010001496001/21/10Gas-turbine engine with variable stator vanes
2002010000577601/14/10Fuel supply system for a gas-turbine engine
2012010000019801/07/10Gas turbine with at least one multi-stage compressor unit including several compressor modules
2022010000022601/07/10Turbofan engine with at least one driving at least one generator
2032009031400412/24/09Turboprop engine with an the generation of a cooling airflow
2042009031723212/24/09Blade shroud with aperture
2052013032687612/12/13Method for repairing compressor or turbine drums
2062010002131001/28/10Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
2072010001496001/21/10Gas-turbine engine with variable stator vanes
2082010000577601/14/10Fuel supply system for a gas-turbine engine
2092010000022601/07/10Turbofan engine with at least one driving at least one generator



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