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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



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
12014031457810/23/14 new patent  Securing segment for the vibration damping of turbine blades and rotor device
22014023803008/28/14Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes
32014024186008/28/14Flight gas turbine with a first rotatable shaft
42014023408008/21/14Device and method for bleeding compressor air in a turbofan engine
52014023409608/21/14Turbomachine component with an erosion and corrosion resistant coating system and method for manufacturing such a component
62014016159106/12/14Lubricant system
72014015044206/05/14Gas turbine centripetal annular combustion chamber and method for flow guidance
82014014414505/29/14Gas turbine combustion chamber
92014014414605/29/14Tile fastening arrangement of a gas-turbine combustion chamber
102014014082005/22/14Aeroengine sealing arrangement
112014014189405/22/14Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
122014014082005/22/14Aeroengine sealing arrangement
132014014189405/22/14Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
142014013050105/15/14Combustion chamber tile of a gas turbine
152014013096405/15/14Method 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
162014013050105/15/14Combustion chamber tile of a gas turbine
172014013096405/15/14Method 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
182014012428905/08/14Nozzle with guiding devices
192014012700105/08/14Gas-turbine engine with a telescopic air inlet in the engine lining
202014012700305/08/14Stator vane adjusting device of a gas turbine
212014012701005/08/14Nozzle with guiding devices
222014012700505/08/14Method for producing a component, component and turbomachine having a component
232014012428905/08/14Nozzle with guiding devices
242014012700105/08/14Gas-turbine engine with a telescopic air inlet in the engine lining
252014012700305/08/14Stator vane adjusting device of a gas turbine
262014012701005/08/14Nozzle with guiding devices
272014012700505/08/14Method for producing a component, component and turbomachine having a component
282014011602505/01/14Aeroengine thrust reverser arrangement
292014011602605/01/14Aeroengine thrust reverser arrangement
302014011988305/01/14Bleed flow passage
312014011994205/01/14Turbine rotor blade of a gas turbine
322014011602505/01/14Aeroengine thrust reverser arrangement
332014011602605/01/14Aeroengine thrust reverser arrangement
342014011988305/01/14Bleed flow passage
352014011994205/01/14Turbine rotor blade of a gas turbine
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
382014009653304/10/14Bearing 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
392014007953903/20/14Turbine blade of a gas turbine with swirl-generating element and method for its manufacture
402014007953903/20/14Turbine blade of a gas turbine with swirl-generating element and method for its manufacture
412014006492803/06/14Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
422014006495203/06/14Assembly of an axial turbomachine and method for manufacturing an assembly of this type
432014006492803/06/14Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
442014006495203/06/14Assembly of an axial turbomachine and method for manufacturing an assembly of this type
452014005056102/20/14Oil supply system and method for supplying oil for a turboprop engine
462014003372302/06/14Unknown
472014003373102/06/14Method for fuel temperature control of a gas turbine
482014002653401/30/14Oil supply system for an aircraft engine
492014002659201/30/14Assembly for a jet engine of an aircraft
502014002670001/30/14Accessory gearbox device for a jet engine
512014003010601/30/14Compressor blade of a gas turbine as well as method for manufacturing said blade
522014003010701/30/14Decoupled compressor blade of a gas turbine
532014003010901/30/14Low-modulus gas-turbine compressor blade
542013032687612/12/13Method for repairing compressor or turbine drums
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 method for 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
662013021998208/29/13Rolling tool device
672013021639108/22/13Method for the production of a one-piece rotor area and one-piece rotor area
682013021639108/22/13Method for the production of a one-piece rotor area and one-piece rotor area
692013020575308/15/13Aircraft gas turbine thrust-reversing device
702013020578808/15/13Unknown
712013020667608/15/13Measuring device having a pressure sensor
722013020575308/15/13Aircraft gas turbine thrust-reversing device
732013020578808/15/13Unknown
742013020667608/15/13Measuring device having a pressure sensor
752013019904008/08/13Device and method for treatment of high-pressure turbine blades of a gas turbine
762013019918708/08/13Gas-turbine combustion chamber having non-symmetrical fuel nozzles
772013020208808/08/13Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
782013019904008/08/13Device and method for treatment of high-pressure turbine blades of a gas turbine
792013019918708/08/13Gas-turbine combustion chamber having non-symmetrical fuel nozzles
802013020208808/08/13Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
812013019223208/01/13Annular combustion chamber of a gas turbine
822013019561008/01/13Noise-reduced turbomachine
832013019223208/01/13Annular combustion chamber of a gas turbine
842013019561008/01/13Noise-reduced turbomachine
852013018670707/25/13Unknown
862013018670707/25/13Unknown
872013018022707/18/13Fastening element and de-icing device of an aircraft gas-turbine engine
882013018022707/18/13Fastening element and de-icing device of an aircraft gas-turbine engine
892013016045906/27/13Accessory mounting for a gas turbine
902013016605606/27/13Method for selecting a geometry of a blade
912013016045906/27/13Accessory mounting for a gas turbine
922013016605606/27/13Method for selecting a geometry of a blade
932013015662606/20/13Method for manufacturing a part by metal injection moulding
942013015700006/20/13Component and turbomachine having a component
952013015662606/20/13Method for manufacturing a part by metal injection moulding
962013015700006/20/13Component and turbomachine having a component
972013013957806/06/13Pressure-measuring device and pressure-measuring method for a turbomachine
982013014246706/06/13Method and device for adjusting the bearing play in a ceramic hybrid bearing
992013013957806/06/13Pressure-measuring device and pressure-measuring method for a turbomachine
1002013014246706/06/13Method and device for adjusting the bearing play in a ceramic hybrid bearing
1012013012950405/23/13Bearing device and turbomachine having a bearing device
1022013012950505/23/13Bearing device and turbomachine having a bearing device
1032013012950405/23/13Bearing device and turbomachine having a bearing device
1042013012950505/23/13Bearing device and turbomachine having a bearing device
1052013012411405/16/13Method for determining a flow behaviour of a medium
1062013012411405/16/13Method for determining a flow behaviour of a medium
1072013009817904/25/13Accessory gearbox device for a jet engine
1082013009170404/18/13Method for repairing rotor blades
1092013008690804/11/13Gas turbine combustion chamber arrangement of axial type of construction
1102013005571603/07/13Gas-turbine combustion chamber with a holding means of a seal for an attachment
1112013005709303/07/13Generator and accessory gearbox device with a generator
1122013004262702/21/13Combustion chamber head of a gas turbine with cooling and damping functions
1132013004509302/21/13Method for the manufacture of a component for high thermal loads, a component producible by this method and an aircraft engine provided with the component
1142013002596201/31/13Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element
1152013000814701/10/13Aircraft gas turbine with variable bypass nozzle
1162013001124601/10/13Gas-turbine aircraft engine with structural surface cooler
1172012032535412/27/12Apparatus and method for the creation of an impingement jet generating annular swirls as well as turbomachine with an apparatus of this type
1182012032147712/20/12Rotor device for a jet engine with a disk wheel and several rotor blades
1192012030465812/06/12Segment 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
1202012029880211/29/12De-icing device of an aircraft gas-turbine engine
1212012028513811/15/12Aircraft gas-turbine engine with oil cooler in the engine cowling
1222012028835911/15/12Gas-turbine engine with bleed-air tapping device
1232012028208211/08/12Gas-turbine balancing device
1242012026642610/25/12Method and apparatus for surface strengthening and/or smoothing of an integrally bladed rotor area of a jet engine
1252012026961910/25/12Fluid-flow machine
1262012024711010/04/12Device for mixing fuel and air of a jet engine
1272012025131210/04/12Stator of an axial compressor stage of a turbomachine
1282012025132410/04/12Rotor of an axial compressor stage of a turbomachine
1292012024058309/27/12Segmented combustion chamber head
1302012024059509/27/12Combustion chamber head with holding means for seals on burners in gas turbines
1312012022239609/06/12Jet engine device with a bypass duct
1322012020472308/16/12Centrifugal oil separator for an aircraft engine
1332012017458807/12/12Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
1342012014839606/14/12Fluid-flow machine - blade with hybrid profile configuration
1352012012552305/24/12Repair method for a sandwich-like component
1362012011797305/17/12Gas-turbine combustion chamber with a cooling-air supply device
1372012009477704/19/12Drive shaft, in particular radial shaft for a gas-turbine engine
1382012007666503/29/12Cooled turbine blades for a gas-turbine engine
1392012006702503/22/12Bloom mixer for a turbofan engine
1402012006710103/22/12Forging tool
1412012004503202/23/12Method for filmless radiographoc inspection of components
1422012003378702/09/12Method for radiographic inspection of components
1432012003433302/09/12Injection moulding tool for the manufacture of a hybrid component
1442012001766301/26/12Method for the manufacture of a workpiece with defined surface
1452012002080201/26/12Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
1462012001182701/19/12Bleed air outlet in the bypass duct of a turbofan engine
1472012001478001/19/12Fan downstream guide vanes of a turbofan engine
1482012000661401/12/12Gas-turbine exhaust cone
1492011030896612/22/11Method for manufacturing blisks
1502011028874011/24/11Engine synchronization method
1512011027168011/10/11Lean premix burner of a gas-turbine engine provided with a concentric annular central body
1522011027168111/10/11Lean premix burner of a gas-turbine engine provided with a flow-guiding element
1532011027176511/10/11Method and apparatus for the detection of defects in the raceways of bearing shells and in the rolling elements of ceramic hybrid bearings
1542011027183711/10/11Centrifugal oil separator for an aircraft engine
1552011025596410/20/11Bypass duct of a turbofan engine
1562011021978209/15/11Aerodynamically shaped supporting and/or fairing element in the bypass duct of a gas-turbine engine
1572011021517209/08/11Aircraft engine with optimized oil heat exchanger
1582011020945809/01/11Aircraft gas turbine engine
1592011021194709/01/11Bypass duct of a turbo engine
1602011017984407/28/11Method and apparatus for surface strengthening of blisk blades
1612011018249907/28/11Method for determining the surface coverage obtained by shot peening
1622011017399007/21/11Intermediate casing for a gas-turbine engine
1632011014622306/23/11Arrangement for the discharge of exhaust air separated from the lubricating oil de-aeration system of a gas-turbine engine
1642011014622406/23/11Arrangement for the discharge of oil-venting air on a gas-turbine engine
1652011013992506/16/11Arrangement for the suspension of a jet engine to a supporting structure
1662011012772806/02/11Sealing rings for a labyrinth seal
1672011012113605/26/11Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device
1682011011690805/19/11Gas turbine engine with an arrangement for measuring the shaft rotation speed
1692011007007403/24/11Gas turbine with a shroud and labyrinth-type sealing arrangement
1702011003866602/17/11Engine shaft of hybrid design
1712011002709102/03/11Axial-flow compressor, more particularly one for an aircraft gas-turbine engine
1722011001688301/27/11Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine
1732011001105801/20/11Turbofan engine
1742011001109301/20/11Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall
1752011001403701/20/11Axial-flow compressor with a flow pulse generator
1762011001404001/20/11Fluid flow machine with blade row group
1772011001405701/20/11Engine blade with excessive leading edge loading
1782011001405801/20/11Propeller
1792011000523301/13/11Combustion chamber head of a gas turbine
1802011000585801/13/11Noise-reduced aircraft engine and method for reducing noise emissions of an aircraft engine
1812010030362912/02/10Fluid flow machine with a blade row group featuring a meridional edge distance
1822010028777211/18/10Method for surface strengthening and smoothening of metallic components
1832010028864811/18/10Method and apparatus for etching the surfaces of integrally bladed rotors
1842010025819910/14/10Intake cone in a fiber compound material for a gas-turbine engine
1852010025901310/14/10Abradable labyrinth seal for a fluid-flow machine
1862010023295409/16/10Bypass duct of a turbofan engine
1872010022390509/09/10Scoop of a running-gap control system of an aircraft gas turbine
1882010022434809/09/10Method for the manufacture of an ejector nozzle tube
1892010021228508/26/10Turboprop propulsion unit with pusher propeller
1902010021548108/26/10Running-gap control system of an aircraft gas turbine
1912010019258808/05/10Method 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
1922010017525607/15/10Method for the manufacture of the blade tips of rotor wheels made in blisk design
1932010017609707/15/10Arrangement for the repair of the blades of blisk drums by means of laser deposition welding
1942010015552606/24/10Aircraft with tail propeller-engine layout
1952010016110706/24/10Machine control for a numerically controlled machine tool
1962010014802706/17/10Sensor bracket for at least one sensor on a gas turbine
1972010014844906/17/10Segmented sealing lips for labyrinth sealing rings
1982010015069606/17/10Fan casing for a jet engine
1992010013924106/10/10Flow divider for a fan engine
2002010013927806/10/10Method and apparatus for the operation of a turboprop aircraft engine provided with pusher propellers
2012010014023006/10/10Method for the manufacture of a welded rotor for a gas-turbine engine
2022010014314006/10/10Fluid flow machine with sidewall boundary layer barrier
2032010012658905/27/10Device for the prevention of high oil tank pressures under negative g conditions
2042010012666205/27/10Method for the manufacture of hybrid components for aircraft gas turbines
2052010012965105/27/10Hybrid component for a gas-turbine engine
2062010012251805/20/10Oil system heating for aircraft gas turbines
2072010012448705/20/10Multi-vane variable stator unit of a fluid flow machine
2082010010918405/06/10Method for the manufacture of an engine shaft
2092010011170205/06/10Hub cone for an aircraft engine
2102010011317005/06/10Engine shaft for a gas-turbine engine
2112010011317105/06/10Engine shaft in the form of a fiber-composite plastic tube with metallic driving and driven protrusions
2122010009852704/22/10Fluid flow machine with peripheral energization near the suction side
2132010009853004/22/10Compressor for a gas turbine
2142010009853604/22/10Fluid flow machine with running gap retraction
2152010005111203/04/10Intake cone for a gas-turbine engine
2162010003463702/11/10Fluid flow machine
2172010002421402/04/10Method for the manufacture of metallic components
2182010002131001/28/10Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
2192010001495601/21/10Fluid flow machine featuring a groove on a running gap of a blade end
2202010001496001/21/10Gas-turbine engine with variable stator vanes
2212010000577601/14/10Fuel supply system for a gas-turbine engine
2222010000019801/07/10Gas turbine with at least one multi-stage compressor unit including several compressor modules
2232010000022601/07/10Turbofan engine with at least one apparatus for driving at least one generator
2242009031400412/24/09Turboprop engine with an apparatus for the generation of a cooling airflow
2252009031723212/24/09Blade shroud with aperture
2262013032687612/12/13Method for repairing compressor or turbine drums
2272010002131001/28/10Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
2282010001496001/21/10Gas-turbine engine with variable stator vanes
2292010000577601/14/10Fuel supply system for a gas-turbine engine
2302010000022601/07/10Turbofan 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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