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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 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "R" | Rolls royce Deutschland Ltd & Co Kg-related inventors




Count Application # Date Rolls royce Deutschland Ltd & Co Kg patents (updated weekly) - BOOKMARK this page
12016017772706/23/16  new patent  Vibration damper
22016017778006/23/16  new patent  Blade arrangement of a jet engine or an aircraft propeller
32016017782506/23/16  new patent  Aircraft engine having a device for separating oil
42016017785606/23/16  new patent  Equipment health monitoring method and system and engine
52016017796906/23/16  new patent  Compressor blade of a gas turbine
62016017819806/23/16  new patent  Gas turbine combustion chamber with modified wall thickness
72016017847106/23/16  new patent  Method for detecting a fuel leak in a fuel system of an aircraft having at least two engines
82016015867906/09/16 Aircraft engine with an separating oil and a device for increasing pressure
92016016075706/09/16 Air intake arrangement
102016016099306/09/16 Device with a torque-proof first structural component and a second structural component that is connected at least in certain parts in a rotatable manner to the first structural component
112016016099406/09/16 Device with a torque-proof first structural component and a second structural component that is connected at least in certain parts in a rotatable manner to the first structural component
122016015628506/02/16 Turbo engine with an energy harvesting device, energy harvesting device and a energy harvesting
132016013841105/19/16 Fully integrated air guide element
142016013847105/19/16 Air guiding device and turbo engine with air guiding device
152016013847805/19/16 Gas turbine engine
162016013880805/19/16 Device for determining a fuel split, as gas turbine or an aircraft engine comprising such a device and application of the same
172016013107905/12/16 Engine cowling of a gas turbine with thrust-reversing device and adjustable outlet nozzle
182016012323505/05/16 Arrangement and blowing-off compressor air in a jet engine
192016011590304/28/16 Aircraft gas turbine thrust-reversing device having a guide rail
202016009729204/07/16 Gas turbine having at least two shafts designed as hollow shafts at least in some areas and arranged coaxially relative to one another
212016009733004/07/16 Gas turbine architecture
222016009733104/07/16 Gas turbine architecture
232016009730104/07/16 Aircraft gas turbine engine with shock-absorbing element for fan blade loss
242016009085603/31/16 Stator vane adjusting device of a gas turbine
252016009098803/31/16 Aircraft engine with a compressor device
262016008256003/24/16 Method and device for machining the blade tips of a compressor rotor of a gas turbine
272016007639903/17/16 Tank device of an aero engine with an appliance for introducing oil
282016007644903/17/16 Aero engine with a bearing chamber and an appliance for introducing oil
292016007645303/17/16 Sound-damping arrangement for an engine nacelle and engine nacelle comprising such an arrangement
302016006921603/10/16 Shroud device of a jet engine
312016006921703/10/16 Panels of a fan of a gas turbine
322016006926503/10/16 Air guiding device and aircraft engine with air guiding device
332016006927203/10/16 Device for the extraction of bleed air and aircraft engine with at least one device for the extraction of bleed air
342016006927303/10/16 Device for the extraction of bleed air and aircraft engine with at least one device for the extraction of bleed air
352016006935503/10/16 Panels of a fan of a gas turbine
362016006510603/03/16 Aircraft engine and operating an aircraft engine
372016004724802/18/16 Blade
382016004733302/18/16 Thrust reverser cascade element of an aircraft gas turbine
392016003296802/04/16 Slide bearing device
402016002503701/28/16 Thrust reverser unit
412016002522101/28/16 Aircraft gas turbine with a seal for sealing an igniter plug on the combustion chamber wall of a gas turbine
422016001086901/14/16 Combustion chamber of a gas turbine with bolted combustion chamber head
432015036745812/24/15 Rolling tool device
442015036745912/24/15 Rolling tool device
452015036935512/24/15 Accessory gearbox device
462015034532312/03/15 Variable stator vane arrangement
472015029235710/15/15 Aircraft gas turbine having a core engine casing with cooling-air tubes
482015028514410/08/15 Gas turbine inlet
492015027575910/01/15 Flow guiding system, turbo engine with a flow guiding manufacturing a flow guiding system
502015027664110/01/15 Measuring detecting ferromagnetic particles
512015026754809/24/15 Group of blade rows
522015026812009/24/15 Pressure-measuring device for measuring dynamic pressure and gas-turbine combustion chamber having pressure-measuring device
532015026754609/24/15 Group of blade rows
542015026754709/24/15 Group of blade rows
552015026010109/17/15 Flow guiding system and rotary combustion engine
562015026040009/17/15 Combustion chamber shingle of a gas turbine
572015026040109/17/15 Combustion chamber of a gas turbine
582015026040209/17/15 Combustion chamber of a gas turbine
592015026040309/17/15 Combustion chamber of a gas turbine
602015026040509/17/15 Combustion chamber of a gas turbine
612015026040909/17/15 Gas turbine combustion chamber and manufacturing the same
622015026056309/17/15 Structural unit for arrangement on a hydraulic fluid tank of a jet engine
632015025267409/10/15 Method for producing a tandem blade wheel for a jet engine and tandem blade wheel
642015024064308/27/15 Group of blade rows
652015024064608/27/15 Group of blade rows
662015024064708/27/15 Group of blade rows
672015024064808/27/15 Group of blade rows
682015024083608/27/15 Group of blade rows
692015024093108/27/15 Gearing arrangement
702015020991507/30/15 Method for repairing an abradable coating of a compressor of a gas turbine
712015017643006/25/15 Cooled flange connection of a gas-turbine engine
722015017643406/25/15 Washer of a combustion chamber tile of a gas turbine
732015017644706/25/15 Jet engine device with at least one component that is arranged in a casing and that is rotatable to the casing
742015017652706/25/15 Aircraft gas turbine comprising an engine cowling with a thrust-reverser device
752015017652906/25/15 Aircraft gas turbine comprising a thrust-reverser device with cascade elements and an integrated rack and pinion drive
762015016749806/18/15 Joint between components
772015015948806/11/15 Turbine rotor blade of a gas turbine and cooling a blade tip of a turbine rotor blade of a gas turbine
782015014715905/28/15 Housing arrangement for a gas turbine
792015013566005/21/15 Jet engine comprising a device for spraying oil into an air-oil volume flow
802015013571905/21/15 Gas turbine combustor with tile having access hole for spark plug
812015013566305/21/15 Jet engine comprising a device for spraying oil
822015012860205/14/15 Heat shield for a gas turbine combustion chamber
832015012860305/14/15 Gas-turbine combustion chamber and its manufacture
842015012368005/07/15 Inductive sensor and manufacturing an inductive sensor
852015010779804/23/15 Unknown
862015008634403/26/15 Assembly for a fluid flow machine
872015006826203/12/15 Apparatus and shot peening of blade mounting areas on a rotor arrangement disc
882015007177703/12/15 Turbine guide wheel
892015005931503/05/15 Apparatus and bleeding off compressor air in a jet engine
902015006019403/05/15 Sound absorber, sound absorber assembly and an engine with a sound absorber assembly
912015005290802/26/15 Bleed duct assembly for a gas turbine engine
922015004719102/19/15 Method for balancing and assembling a turbine rotor
932015002712701/29/15 Combustion chamber tile of a gas turbine
942015003078701/29/15 Laser depositioning device and producing a component by direct laser depositioning
952015001330701/15/15 Turbofan jet engine
962015001695001/15/15 Device and discharging sealing air in a turbofan engine
972015001699401/15/15 Aircraft engine
982015000753101/08/15 Jet engine with at least one oil separator, through which an air-oil-volume flow can be guided
992015001038501/08/15 Gas turbine with high-pressure turbine cooling system
1002015000024601/01/15 Jet engine with at least one oil separator
1012014037355512/25/14 Accessory mounting for a gas turbine engine
1022014036655512/18/14 Accessory mounting for a gas turbine engine
1032014036327712/11/14 Assembly for a fluid flow machine
1042014036328312/11/14 Shroud arrangement for a fluid flow machine
1052014035614312/04/14 Assembly for a fluid flow machine
1062014035614412/04/14 Assembly for a fluid flow machine
1072014035245012/04/14 Method for determining a machining result during surface machining of components
1082014031814810/30/14 Burner seal for gas-turbine combustion chamber head and heat shield
1092014031815010/30/14 Removable swirler assembly for a combustion liner
1102014031457810/23/14 Securing segment for the vibration damping of turbine blades and rotor device
1112014023803008/28/14 Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes
1122014024186008/28/14 Flight gas turbine with a first rotatable shaft
1132014023408008/21/14 Device and bleeding compressor air in a turbofan engine
1142014023409608/21/14 Turbomachine component with an erosion and corrosion resistant coating manufacturing such a component
1152014016159106/12/14 Lubricant system
1162014015044206/05/14 Gas turbine centripetal annular combustion chamber and flow guidance
1172014014414505/29/14 Gas turbine combustion chamber
1182014014414605/29/14 Tile fastening arrangement of a gas-turbine combustion chamber
1192014014082005/22/14 Aeroengine sealing arrangement
1202014014189405/22/14 Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
1212014013050105/15/14 Combustion chamber tile of a gas turbine
1222014013096405/15/14 Method 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
1232014012428905/08/14 Nozzle with guiding devices
1242014012700105/08/14 Gas-turbine engine with a telescopic air inlet in the engine lining
1252014012700305/08/14 Stator vane adjusting device of a gas turbine
1262014012701005/08/14 Nozzle with guiding devices
1272014012700505/08/14 Method for producing a component, component and turbomachine having a component
1282014011602505/01/14 Aeroengine thrust reverser arrangement
1292014011602605/01/14 Aeroengine thrust reverser arrangement
1302014011988305/01/14 Bleed flow passage
1312014011994205/01/14 Turbine rotor blade of a gas turbine
1322014009653304/10/14 Bearing chamber venting system for an aircraft engine and providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber
1332014007953903/20/14 Turbine blade of a gas turbine with swirl-generating element and its manufacture
1342014006492803/06/14 Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
1352014006495203/06/14 Assembly of an axial turbomachine and manufacturing an assembly of this type
1362014005056102/20/14 Oil supply supplying oil for a turboprop engine
1372014003372302/06/14 Unknown
1382014003373102/06/14 Method for fuel temperature control of a gas turbine
1392014002653401/30/14 Oil supply system for an aircraft engine
1402014002659201/30/14 Assembly for a jet engine of an aircraft
1412014002670001/30/14 Accessory gearbox device for a jet engine
1422014003010601/30/14 Compressor blade of a gas turbine as well as manufacturing said blade
1432014003010701/30/14 Decoupled compressor blade of a gas turbine
1442014003010901/30/14 Low-modulus gas-turbine compressor blade
1452013032687612/12/13 Method for repairing compressor or turbine drums
1462013031894512/05/13 Aviation gas turbine thrust reversing device
1472013030640111/21/13 Sound absorber for a gas turbine exhaust cone, and the production thereof
1482013030640211/21/13 Method for the production of a sound absorber, especially for a gas turbine exhaust cone
1492013030640311/21/13 Method for the production of a sound absorber, especially for a gas turbine exhaust cone
1502013030909111/21/13 Oil supply system for a propeller turbine engine
1512013030214311/14/13 Cooling device for a jet engine
1522013026642410/10/13 Stator vane adjusting device of a gas turbine
1532013025973210/03/13 Method for producing engine components with a geometrically complex structure
1542013023038309/05/13 Aircraft gas turbine with adjustable fan
1552013021998208/29/13 Rolling tool device
1562013021639108/22/13 Method for the production of a one-piece rotor area and one-piece rotor area
1572013020575308/15/13 Aircraft gas turbine thrust-reversing device
1582013020578808/15/13 Unknown
1592013020667608/15/13 Measuring device having a pressure sensor
1602013019904008/08/13 Device and treatment of high-pressure turbine blades of a gas turbine
1612013019918708/08/13 Gas-turbine combustion chamber having non-symmetrical fuel nozzles
1622013020208808/08/13 Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
1632013019223208/01/13 Annular combustion chamber of a gas turbine
1642013019561008/01/13 Noise-reduced turbomachine
1652013018670707/25/13 Unknown
1662013018022707/18/13 Fastening element and de-icing device of an aircraft gas-turbine engine
1672013016045906/27/13 Accessory mounting for a gas turbine
1682013016605606/27/13 Method for selecting a geometry of a blade
1692013015662606/20/13 Method for manufacturing a part by metal injection moulding
1702013015700006/20/13 Component and turbomachine having a component
1712013013957806/06/13 Pressure-measuring device and pressure-measuring a turbomachine
1722013014246706/06/13 Method and device for adjusting the bearing play in a ceramic hybrid bearing
1732013012950405/23/13 Bearing device and turbomachine having a bearing device
1742013012950505/23/13 Bearing device and turbomachine having a bearing device
1752013012411405/16/13 Method for determining a flow behaviour of a medium
1762013009817904/25/13 Accessory gearbox device for a jet engine
1772013009170404/18/13 Method for repairing rotor blades
1782013008690804/11/13 Gas turbine combustion chamber arrangement of axial type of construction
1792013005571603/07/13 Gas-turbine combustion chamber with a holding means of a seal for an attachment
1802013005709303/07/13 Generator and accessory gearbox device with a generator
1812013004262702/21/13 Combustion chamber head of a gas turbine with cooling and damping functions
1822013004509302/21/13 Method for the manufacture of a component for high thermal loads, a component producible by this method and an aircraft engine provided with the component
1832013002596201/31/13 Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element
1842013000814701/10/13 Aircraft gas turbine with variable bypass nozzle
1852013001124601/10/13 Gas-turbine aircraft engine with structural surface cooler
1862012032535412/27/12 Apparatus and the creation of an impingement jet generating annular swirls as well as turbomachine with an apparatus of this type
1872012032147712/20/12 Rotor device for a jet engine with a disk wheel and several rotor blades
1882012030465812/06/12 Segment 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
1892012029880211/29/12 De-icing device of an aircraft gas-turbine engine
1902012028513811/15/12 Aircraft gas-turbine engine with oil cooler in the engine cowling
1912012028835911/15/12 Gas-turbine engine with bleed-air tapping device
1922012028208211/08/12 Gas-turbine balancing device
1932012026642610/25/12 Method and surface strengthening and/or smoothing of an integrally bladed rotor area of a jet engine
1942012026961910/25/12 Fluid-flow machine
1952012024711010/04/12 Device for mixing fuel and air of a jet engine
1962012025131210/04/12 Stator of an axial compressor stage of a turbomachine
1972012025132410/04/12 Rotor of an axial compressor stage of a turbomachine
1982012024058309/27/12 Segmented combustion chamber head
1992012024059509/27/12 Combustion chamber head with holding means for seals on burners in gas turbines
2002012022239609/06/12 Jet engine device with a bypass duct
2012012020472308/16/12 Centrifugal oil separator for an aircraft engine
2022012017458807/12/12 Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
2032012014839606/14/12 Fluid-flow machine - blade with hybrid profile configuration
2042012012552305/24/12 Repair a sandwich-like component
2052012011797305/17/12 Gas-turbine combustion chamber with a cooling-air supply device
2062012009477704/19/12 Drive shaft, in particular radial shaft for a gas-turbine engine
2072012007666503/29/12 Cooled turbine blades for a gas-turbine engine
2082012006702503/22/12 Bloom mixer for a turbofan engine
2092012006710103/22/12 Forging tool
2102012004503202/23/12 Method for filmless radiographoc inspection of components
2112012003378702/09/12 Method for radiographic inspection of components
2122012003433302/09/12 Injection moulding tool for the manufacture of a hybrid component
2132012001766301/26/12 Method for the manufacture of a workpiece with defined surface
2142012002080201/26/12 Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
2152012001182701/19/12 Bleed air outlet in the bypass duct of a turbofan engine
2162012001478001/19/12 Fan downstream guide vanes of a turbofan engine
2172012000661401/12/12 Gas-turbine exhaust cone
2182011030896612/22/11 Method for manufacturing blisks
2192011028874011/24/11 Engine synchronization method
2202011027168011/10/11 Lean premix burner of a gas-turbine engine provided with a concentric annular central body
2212011027168111/10/11 Lean premix burner of a gas-turbine engine provided with a flow-guiding element
2222011027176511/10/11 Method and the detection of defects in the raceways of bearing shells and in the rolling elements of ceramic hybrid bearings
2232011027183711/10/11 Centrifugal oil separator for an aircraft engine
2242011025596410/20/11 Bypass duct of a turbofan engine
2252011021978209/15/11 Aerodynamically shaped supporting and/or fairing element in the bypass duct of a gas-turbine engine
2262011021517209/08/11 Aircraft engine with optimized oil heat exchanger
2272011020945809/01/11 Aircraft gas turbine engine
2282011021194709/01/11 Bypass duct of a turbo engine
2292011017984407/28/11 Method and surface strengthening of blisk blades
2302011018249907/28/11 Method for determining the surface coverage obtained by shot peening
2312011017399007/21/11 Intermediate casing for a gas-turbine engine
2322011014622306/23/11 Arrangement for the discharge of exhaust air separated from the lubricating oil de-aeration system of a gas-turbine engine
2332011014622406/23/11 Arrangement for the discharge of oil-venting air on a gas-turbine engine
2342011013992506/16/11 Arrangement for the suspension of a jet engine to a supporting structure
2352011012772806/02/11 Sealing rings for a labyrinth seal
2362011012113605/26/11 Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device
2372011011690805/19/11 Gas turbine engine with an arrangement for measuring the shaft rotation speed
2382011007007403/24/11 Gas turbine with a shroud and labyrinth-type sealing arrangement
2392011003866602/17/11 Engine shaft of hybrid design
2402011002709102/03/11 Axial-flow compressor, more particularly one for an aircraft gas-turbine engine
2412011001688301/27/11 Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine
2422011001105801/20/11 Turbofan engine
2432011001109301/20/11 Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall
2442011001403701/20/11 Axial-flow compressor with a flow pulse generator
2452011001404001/20/11 Fluid flow machine with blade row group
2462011001405701/20/11 Engine blade with excessive leading edge loading
2472011001405801/20/11 Propeller
2482011000523301/13/11 Combustion chamber head of a gas turbine
2492011000585801/13/11 Noise-reduced aircraft engine and reducing noise emissions of an aircraft engine



ARCHIVE: New 2016 2015 2014 2013 2012 2011 2010 2009



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