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



Rolls-royce Deutschland Ltd & Co Kg

Flight gas turbine with a first rotatable shaft

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
12014023803008/28/14Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes
22014024186008/28/14Flight gas turbine with a first rotatable shaft
32014023408008/21/14Device and method for bleeding compressor air in a turbofan engine
42014023409608/21/14Turbomachine component with an erosion and corrosion resistant coating system and method for manufacturing such a component
52014016159106/12/14Lubricant system
62014015044206/05/14Gas turbine centripetal annular combustion chamber and method for flow guidance
72014014414505/29/14Gas turbine combustion chamber
82014014414605/29/14Tile fastening arrangement of a gas-turbine combustion chamber
92014014082005/22/14Aeroengine sealing arrangement
102014014189405/22/14Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
112014014082005/22/14Aeroengine sealing arrangement
122014014189405/22/14Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
132014013050105/15/14Combustion chamber tile of a gas turbine
142014013096405/15/14Method 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
152014013050105/15/14Combustion chamber tile of a gas turbine
162014013096405/15/14Method 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
172014012428905/08/14Nozzle with guiding devices
182014012700105/08/14Gas-turbine engine with a telescopic air inlet in the engine lining
192014012700305/08/14Stator vane adjusting device of a gas turbine
202014012701005/08/14Nozzle with guiding devices
212014012700505/08/14Method for producing a component, component and turbomachine having a component
222014012428905/08/14Nozzle with guiding devices
232014012700105/08/14Gas-turbine engine with a telescopic air inlet in the engine lining
242014012700305/08/14Stator vane adjusting device of a gas turbine
252014012701005/08/14Nozzle with guiding devices
262014012700505/08/14Method for producing a component, component and turbomachine having a component
272014011602505/01/14Aeroengine thrust reverser arrangement
282014011602605/01/14Aeroengine thrust reverser arrangement
292014011988305/01/14Bleed flow passage
302014011994205/01/14Turbine rotor blade of a gas turbine
312014011602505/01/14Aeroengine thrust reverser arrangement
322014011602605/01/14Aeroengine thrust reverser arrangement
332014011988305/01/14Bleed flow passage
342014011994205/01/14Turbine rotor blade of a gas turbine
352014009653304/10/14Bearing chamber venting system for an aircraft engine and method for providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber
362014009653304/10/14Bearing chamber venting system for an aircraft engine and method for providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber
372014009653304/10/14Bearing chamber venting system for an aircraft engine and method for providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber
382014007953903/20/14Turbine blade of a gas turbine with swirl-generating element and method for its manufacture
392014007953903/20/14Turbine blade of a gas turbine with swirl-generating element and method for its manufacture
402014006492803/06/14Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
412014006495203/06/14Assembly of an axial turbomachine and method for manufacturing an assembly of this type
422014006492803/06/14Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
432014006495203/06/14Assembly of an axial turbomachine and method for manufacturing an assembly of this type
442014005056102/20/14Oil supply system and method for supplying oil for a turboprop engine
452014003372302/06/14Unknown
462014003373102/06/14Method for fuel temperature control of a gas turbine
472014002653401/30/14Oil supply system for an aircraft engine
482014002659201/30/14Assembly for a jet engine of an aircraft
492014002670001/30/14Accessory gearbox device for a jet engine
502014003010601/30/14Compressor blade of a gas turbine as well as method for manufacturing said blade
512014003010701/30/14Decoupled compressor blade of a gas turbine
522014003010901/30/14Low-modulus gas-turbine compressor blade
532013032687612/12/13Method for repairing compressor or turbine drums
542013032687612/12/13Method for repairing compressor or turbine drums
552013031894512/05/13Aviation gas turbine thrust reversing device
562013030640111/21/13Sound absorber for a gas turbine exhaust cone, and method for the production thereof
572013030640211/21/13Method for the production of a sound absorber, especially for a gas turbine exhaust cone
582013030640311/21/13Method for the production of a sound absorber, especially for a gas turbine exhaust cone
592013030909111/21/13Oil supply system for a propeller turbine engine
602013030214311/14/13Cooling device for a jet engine
612013026642410/10/13Stator vane adjusting device of a gas turbine
622013025973210/03/13Method for producing engine components with a geometrically complex structure
632013023038309/05/13Aircraft gas turbine with adjustable fan
642013021998208/29/13Rolling tool device
652013021998208/29/13Rolling tool device
662013021639108/22/13Method for the production of a one-piece rotor area and one-piece rotor area
672013021639108/22/13Method for the production of a one-piece rotor area and one-piece rotor area
682013020575308/15/13Aircraft gas turbine thrust-reversing device
692013020578808/15/13Unknown
702013020667608/15/13Measuring device having a pressure sensor
712013020575308/15/13Aircraft gas turbine thrust-reversing device
722013020578808/15/13Unknown
732013020667608/15/13Measuring device having a pressure sensor
742013019904008/08/13Device and method for treatment of high-pressure turbine blades of a gas turbine
752013019918708/08/13Gas-turbine combustion chamber having non-symmetrical fuel nozzles
762013020208808/08/13Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
772013019904008/08/13Device and method for treatment of high-pressure turbine blades of a gas turbine
782013019918708/08/13Gas-turbine combustion chamber having non-symmetrical fuel nozzles
792013020208808/08/13Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
802013019223208/01/13Annular combustion chamber of a gas turbine
812013019561008/01/13Noise-reduced turbomachine
822013019223208/01/13Annular combustion chamber of a gas turbine
832013019561008/01/13Noise-reduced turbomachine
842013018670707/25/13Unknown
852013018670707/25/13Unknown
862013018022707/18/13Fastening element and de-icing device of an aircraft gas-turbine engine
872013018022707/18/13Fastening element and de-icing device of an aircraft gas-turbine engine
882013016045906/27/13Accessory mounting for a gas turbine
892013016605606/27/13Method for selecting a geometry of a blade
902013016045906/27/13Accessory mounting for a gas turbine
912013016605606/27/13Method for selecting a geometry of a blade
922013015662606/20/13Method for manufacturing a part by metal injection moulding
932013015700006/20/13Component and turbomachine having a component
942013015662606/20/13Method for manufacturing a part by metal injection moulding
952013015700006/20/13Component and turbomachine having a component
962013013957806/06/13Pressure-measuring device and pressure-measuring method for a turbomachine
972013014246706/06/13Method and device for adjusting the bearing play in a ceramic hybrid bearing
982013013957806/06/13Pressure-measuring device and pressure-measuring method for a turbomachine
992013014246706/06/13Method and device for adjusting the bearing play in a ceramic hybrid bearing
1002013012950405/23/13Bearing device and turbomachine having a bearing device
1012013012950505/23/13Bearing device and turbomachine having a bearing device
1022013012950405/23/13Bearing device and turbomachine having a bearing device
1032013012950505/23/13Bearing device and turbomachine having a bearing device
1042013012411405/16/13Method for determining a flow behaviour of a medium
1052013012411405/16/13Method for determining a flow behaviour of a medium
1062013009817904/25/13Accessory gearbox device for a jet engine
1072013009170404/18/13Method for repairing rotor blades
1082013008690804/11/13Gas turbine combustion chamber arrangement of axial type of construction
1092013005571603/07/13Gas-turbine combustion chamber with a holding means of a seal for an attachment
1102013005709303/07/13Generator and accessory gearbox device with a generator
1112013004262702/21/13Combustion chamber head of a gas turbine with cooling and damping functions
1122013004509302/21/13Method for the manufacture of a component for high thermal loads, a component producible by this method and an aircraft engine provided with the component
1132013002596201/31/13Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element
1142013000814701/10/13Aircraft gas turbine with variable bypass nozzle
1152013001124601/10/13Gas-turbine aircraft engine with structural surface cooler
1162012032535412/27/12Apparatus and method for the creation of an impingement jet generating annular swirls as well as turbomachine with an apparatus of this type
1172012032147712/20/12Rotor device for a jet engine with a disk wheel and several rotor blades
1182012030465812/06/12Segment component in high-temperature casting material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for the manufacture of an annular combustion chamber
1192012029880211/29/12De-icing device of an aircraft gas-turbine engine
1202012028513811/15/12Aircraft gas-turbine engine with oil cooler in the engine cowling
1212012028835911/15/12Gas-turbine engine with bleed-air tapping device
1222012028208211/08/12Gas-turbine balancing device
1232012026642610/25/12Method and apparatus for surface strengthening and/or smoothing of an integrally bladed rotor area of a jet engine
1242012026961910/25/12Fluid-flow machine
1252012024711010/04/12Device for mixing fuel and air of a jet engine
1262012025131210/04/12Stator of an axial compressor stage of a turbomachine
1272012025132410/04/12Rotor of an axial compressor stage of a turbomachine
1282012024058309/27/12Segmented combustion chamber head
1292012024059509/27/12Combustion chamber head with holding means for seals on burners in gas turbines
1302012022239609/06/12Jet engine device with a bypass duct
1312012020472308/16/12Centrifugal oil separator for an aircraft engine
1322012017458807/12/12Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
1332012014839606/14/12Fluid-flow machine - blade with hybrid profile configuration
1342012012552305/24/12Repair method for a sandwich-like component
1352012011797305/17/12Gas-turbine combustion chamber with a cooling-air supply device
1362012009477704/19/12Drive shaft, in particular radial shaft for a gas-turbine engine
1372012007666503/29/12Cooled turbine blades for a gas-turbine engine
1382012006702503/22/12Bloom mixer for a turbofan engine
1392012006710103/22/12Forging tool
1402012004503202/23/12Method for filmless radiographoc inspection of components
1412012003378702/09/12Method for radiographic inspection of components
1422012003433302/09/12Injection moulding tool for the manufacture of a hybrid component
1432012001766301/26/12Method for the manufacture of a workpiece with defined surface
1442012002080201/26/12Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
1452012001182701/19/12Bleed air outlet in the bypass duct of a turbofan engine
1462012001478001/19/12Fan downstream guide vanes of a turbofan engine
1472012000661401/12/12Gas-turbine exhaust cone
1482011030896612/22/11Method for manufacturing blisks
1492011028874011/24/11Engine synchronization method
1502011027168011/10/11Lean premix burner of a gas-turbine engine provided with a concentric annular central body
1512011027168111/10/11Lean premix burner of a gas-turbine engine provided with a flow-guiding element
1522011027176511/10/11Method and apparatus for the detection of defects in the raceways of bearing shells and in the rolling elements of ceramic hybrid bearings
1532011027183711/10/11Centrifugal oil separator for an aircraft engine
1542011025596410/20/11Bypass duct of a turbofan engine
1552011021978209/15/11Aerodynamically shaped supporting and/or fairing element in the bypass duct of a gas-turbine engine
1562011021517209/08/11Aircraft engine with optimized oil heat exchanger
1572011020945809/01/11Aircraft gas turbine engine
1582011021194709/01/11Bypass duct of a turbo engine
1592011017984407/28/11Method and apparatus for surface strengthening of blisk blades
1602011018249907/28/11Method for determining the surface coverage obtained by shot peening
1612011017399007/21/11Intermediate casing for a gas-turbine engine
1622011014622306/23/11Arrangement for the discharge of exhaust air separated from the lubricating oil de-aeration system of a gas-turbine engine
1632011014622406/23/11Arrangement for the discharge of oil-venting air on a gas-turbine engine
1642011013992506/16/11Arrangement for the suspension of a jet engine to a supporting structure
1652011012772806/02/11Sealing rings for a labyrinth seal
1662011012113605/26/11Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device
1672011011690805/19/11Gas turbine engine with an arrangement for measuring the shaft rotation speed
1682011007007403/24/11Gas turbine with a shroud and labyrinth-type sealing arrangement
1692011003866602/17/11Engine shaft of hybrid design
1702011002709102/03/11Axial-flow compressor, more particularly one for an aircraft gas-turbine engine
1712011001688301/27/11Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine
1722011001105801/20/11Turbofan engine
1732011001109301/20/11Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall
1742011001403701/20/11Axial-flow compressor with a flow pulse generator
1752011001404001/20/11Fluid flow machine with blade row group
1762011001405701/20/11Engine blade with excessive leading edge loading
1772011001405801/20/11Propeller
1782011000523301/13/11Combustion chamber head of a gas turbine
1792011000585801/13/11Noise-reduced aircraft engine and method for reducing noise emissions of an aircraft engine
1802010030362912/02/10Fluid flow machine with a blade row group featuring a meridional edge distance
1812010028777211/18/10Method for surface strengthening and smoothening of metallic components
1822010028864811/18/10Method and apparatus for etching the surfaces of integrally bladed rotors
1832010025819910/14/10Intake cone in a fiber compound material for a gas-turbine engine
1842010025901310/14/10Abradable labyrinth seal for a fluid-flow machine
1852010023295409/16/10Bypass duct of a turbofan engine
1862010022390509/09/10Scoop of a running-gap control system of an aircraft gas turbine
1872010022434809/09/10Method for the manufacture of an ejector nozzle tube
1882010021228508/26/10Turboprop propulsion unit with pusher propeller
1892010021548108/26/10Running-gap control system of an aircraft gas turbine
1902010019258808/05/10Method 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
1912010017525607/15/10Method for the manufacture of the blade tips of rotor wheels made in blisk design
1922010017609707/15/10Arrangement for the repair of the blades of blisk drums by means of laser deposition welding
1932010015552606/24/10Aircraft with tail propeller-engine layout
1942010016110706/24/10Machine control for a numerically controlled machine tool
1952010014802706/17/10Sensor bracket for at least one sensor on a gas turbine
1962010014844906/17/10Segmented sealing lips for labyrinth sealing rings
1972010015069606/17/10Fan casing for a jet engine
1982010013924106/10/10Flow divider for a fan engine
1992010013927806/10/10Method and apparatus for the operation of a turboprop aircraft engine provided with pusher propellers
2002010014023006/10/10Method for the manufacture of a welded rotor for a gas-turbine engine
2012010014314006/10/10Fluid flow machine with sidewall boundary layer barrier
2022010012658905/27/10Device for the prevention of high oil tank pressures under negative g conditions
2032010012666205/27/10Method for the manufacture of hybrid components for aircraft gas turbines
2042010012965105/27/10Hybrid component for a gas-turbine engine
2052010012251805/20/10Oil system heating for aircraft gas turbines
2062010012448705/20/10Multi-vane variable stator unit of a fluid flow machine
2072010010918405/06/10Method for the manufacture of an engine shaft
2082010011170205/06/10Hub cone for an aircraft engine
2092010011317005/06/10Engine shaft for a gas-turbine engine
2102010011317105/06/10Engine shaft in the form of a fiber-composite plastic tube with metallic driving and driven protrusions
2112010009852704/22/10Fluid flow machine with peripheral energization near the suction side
2122010009853004/22/10Compressor for a gas turbine
2132010009853604/22/10Fluid flow machine with running gap retraction
2142010005111203/04/10Intake cone for a gas-turbine engine
2152010003463702/11/10Fluid flow machine
2162010002421402/04/10Method for the manufacture of metallic components
2172010002131001/28/10Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
2182010001495601/21/10Fluid flow machine featuring a groove on a running gap of a blade end
2192010001496001/21/10Gas-turbine engine with variable stator vanes
2202010000577601/14/10Fuel supply system for a gas-turbine engine
2212010000019801/07/10Gas turbine with at least one multi-stage compressor unit including several compressor modules
2222010000022601/07/10Turbofan engine with at least one apparatus for driving at least one generator
2232009031400412/24/09Turboprop engine with an apparatus for the generation of a cooling airflow
2242009031723212/24/09Blade shroud with aperture
2252013032687612/12/13Method for repairing compressor or turbine drums
2262010002131001/28/10Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
2272010001496001/21/10Gas-turbine engine with variable stator vanes
2282010000577601/14/10Fuel supply system for a gas-turbine engine
2292010000022601/07/10Turbofan engine with at least one apparatus for driving at least one generator


ARCHIVE: New 2014 2013 2012 2011 2010 2009



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This listing is an abstract for educational and research purposes is only meant as a recent sample of applications filed, not a comprehensive history. Freshpatents.com is not affiliated or associated with Rolls royce Deutschland Ltd & Co Kg in any way and there may be associated servicemarks. This data is also published to the public by the USPTO and available for free on their website. Note that there may be alternative spellings for Rolls royce Deutschland Ltd & Co Kg with additional patents listed. Browse our Agent directory for other possible listings. Page by FreshPatents.com

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