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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
12016003296802/04/16 Slide bearing device
22016002503701/28/16 Thrust reverser unit
32016002522101/28/16 Aircraft gas turbine with a seal for sealing an igniter plug on the combustion chamber wall of a gas turbine
42016001086901/14/16 Combustion chamber of a gas turbine with bolted combustion chamber head
52015036745812/24/15 Rolling tool device
62015036745912/24/15 Rolling tool device
72015036935512/24/15 Accessory gearbox device
82015034532312/03/15 Variable stator vane arrangement
92015029235710/15/15 Aircraft gas turbine having a core engine casing with cooling-air tubes
102015028514410/08/15 Gas turbine inlet
112015027575910/01/15 Flow guiding system, turbo engine with a flow guiding manufacturing a flow guiding system
122015027664110/01/15 Measuring detecting ferromagnetic particles
132015026754809/24/15 Group of blade rows
142015026812009/24/15 Pressure-measuring device for measuring dynamic pressure and gas-turbine combustion chamber having pressure-measuring device
152015026754609/24/15 Group of blade rows
162015026754709/24/15 Group of blade rows
172015026010109/17/15 Flow guiding system and rotary combustion engine
182015026040009/17/15 Combustion chamber shingle of a gas turbine
192015026040109/17/15 Combustion chamber of a gas turbine
202015026040209/17/15 Combustion chamber of a gas turbine
212015026040309/17/15 Combustion chamber of a gas turbine
222015026040509/17/15 Combustion chamber of a gas turbine
232015026040909/17/15 Gas turbine combustion chamber and manufacturing the same
242015026056309/17/15 Structural unit for arrangement on a hydraulic fluid tank of a jet engine
252015025267409/10/15 Method for producing a tandem blade wheel for a jet engine and tandem blade wheel
262015024064308/27/15 Group of blade rows
272015024064608/27/15 Group of blade rows
282015024064708/27/15 Group of blade rows
292015024064808/27/15 Group of blade rows
302015024083608/27/15 Group of blade rows
312015024093108/27/15 Gearing arrangement
322015020991507/30/15 Method for repairing an abradable coating of a compressor of a gas turbine
332015017643006/25/15 Cooled flange connection of a gas-turbine engine
342015017643406/25/15 Washer of a combustion chamber tile of a gas turbine
352015017644706/25/15 Jet engine device with at least one component that is arranged in a casing and that is rotatable to the casing
362015017652706/25/15 Aircraft gas turbine comprising an engine cowling with a thrust-reverser device
372015017652906/25/15 Aircraft gas turbine comprising a thrust-reverser device with cascade elements and an integrated rack and pinion drive
382015016749806/18/15 Joint between components
392015015948806/11/15 Turbine rotor blade of a gas turbine and cooling a blade tip of a turbine rotor blade of a gas turbine
402015014715905/28/15 Housing arrangement for a gas turbine
412015013566005/21/15 Jet engine comprising a device for spraying oil into an air-oil volume flow
422015013571905/21/15 Gas turbine combustor with tile having access hole for spark plug
432015013566305/21/15 Jet engine comprising a device for spraying oil
442015012860205/14/15 Heat shield for a gas turbine combustion chamber
452015012860305/14/15 Gas-turbine combustion chamber and its manufacture
462015012368005/07/15 Inductive sensor and manufacturing an inductive sensor
472015010779804/23/15 Unknown
482015008634403/26/15 Assembly for a fluid flow machine
492015006826203/12/15 Apparatus and shot peening of blade mounting areas on a rotor arrangement disc
502015007177703/12/15 Turbine guide wheel
512015005931503/05/15 Apparatus and bleeding off compressor air in a jet engine
522015006019403/05/15 Sound absorber, sound absorber assembly and an engine with a sound absorber assembly
532015005290802/26/15 Bleed duct assembly for a gas turbine engine
542015004719102/19/15 Method for balancing and assembling a turbine rotor
552015002712701/29/15 Combustion chamber tile of a gas turbine
562015003078701/29/15 Laser depositioning device and producing a component by direct laser depositioning
572015001330701/15/15 Turbofan jet engine
582015001695001/15/15 Device and discharging sealing air in a turbofan engine
592015001699401/15/15 Aircraft engine
602015000753101/08/15 Jet engine with at least one oil separator, through which an air-oil-volume flow can be guided
612015001038501/08/15 Gas turbine with high-pressure turbine cooling system
622015000024601/01/15 Jet engine with at least one oil separator
632014037355512/25/14 Accessory mounting for a gas turbine engine
642014036655512/18/14 Accessory mounting for a gas turbine engine
652014036327712/11/14 Assembly for a fluid flow machine
662014036328312/11/14 Shroud arrangement for a fluid flow machine
672014035614312/04/14 Assembly for a fluid flow machine
682014035614412/04/14 Assembly for a fluid flow machine
692014035245012/04/14 Method for determining a machining result during surface machining of components
702014031814810/30/14 Burner seal for gas-turbine combustion chamber head and heat shield
712014031815010/30/14 Removable swirler assembly for a combustion liner
722014031457810/23/14 Securing segment for the vibration damping of turbine blades and rotor device
732014023803008/28/14 Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes
742014024186008/28/14 Flight gas turbine with a first rotatable shaft
752014023408008/21/14 Device and bleeding compressor air in a turbofan engine
762014023409608/21/14 Turbomachine component with an erosion and corrosion resistant coating manufacturing such a component
772014016159106/12/14 Lubricant system
782014015044206/05/14 Gas turbine centripetal annular combustion chamber and flow guidance
792014014414505/29/14 Gas turbine combustion chamber
802014014414605/29/14 Tile fastening arrangement of a gas-turbine combustion chamber
812014014082005/22/14 Aeroengine sealing arrangement
822014014189405/22/14 Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
832014013050105/15/14 Combustion chamber tile of a gas turbine
842014013096405/15/14 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
852014012428905/08/14 Nozzle with guiding devices
862014012700105/08/14 Gas-turbine engine with a telescopic air inlet in the engine lining
872014012700305/08/14 Stator vane adjusting device of a gas turbine
882014012701005/08/14 Nozzle with guiding devices
892014012700505/08/14 Method for producing a component, component and turbomachine having a component
902014011602505/01/14 Aeroengine thrust reverser arrangement
912014011602605/01/14 Aeroengine thrust reverser arrangement
922014011988305/01/14 Bleed flow passage
932014011994205/01/14 Turbine rotor blade of a gas turbine
942014009653304/10/14 Bearing chamber venting system for an aircraft engine and providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber
952014007953903/20/14 Turbine blade of a gas turbine with swirl-generating element and its manufacture
962014006492803/06/14 Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
972014006495203/06/14 Assembly of an axial turbomachine and manufacturing an assembly of this type
982014005056102/20/14 Oil supply supplying oil for a turboprop engine
992014003372302/06/14 Unknown
1002014003373102/06/14 Method for fuel temperature control of a gas turbine
1012014002653401/30/14 Oil supply system for an aircraft engine
1022014002659201/30/14 Assembly for a jet engine of an aircraft
1032014002670001/30/14 Accessory gearbox device for a jet engine
1042014003010601/30/14 Compressor blade of a gas turbine as well as manufacturing said blade
1052014003010701/30/14 Decoupled compressor blade of a gas turbine
1062014003010901/30/14 Low-modulus gas-turbine compressor blade
1072013032687612/12/13 Method for repairing compressor or turbine drums
1082013031894512/05/13 Aviation gas turbine thrust reversing device
1092013030640111/21/13 Sound absorber for a gas turbine exhaust cone, and the production thereof
1102013030640211/21/13 Method for the production of a sound absorber, especially for a gas turbine exhaust cone
1112013030640311/21/13 Method for the production of a sound absorber, especially for a gas turbine exhaust cone
1122013030909111/21/13 Oil supply system for a propeller turbine engine
1132013030214311/14/13 Cooling device for a jet engine
1142013026642410/10/13 Stator vane adjusting device of a gas turbine
1152013025973210/03/13 Method for producing engine components with a geometrically complex structure
1162013023038309/05/13 Aircraft gas turbine with adjustable fan
1172013021998208/29/13 Rolling tool device
1182013021639108/22/13 Method for the production of a one-piece rotor area and one-piece rotor area
1192013020575308/15/13 Aircraft gas turbine thrust-reversing device
1202013020578808/15/13 Unknown
1212013020667608/15/13 Measuring device having a pressure sensor
1222013019904008/08/13 Device and treatment of high-pressure turbine blades of a gas turbine
1232013019918708/08/13 Gas-turbine combustion chamber having non-symmetrical fuel nozzles
1242013020208808/08/13 Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
1252013019223208/01/13 Annular combustion chamber of a gas turbine
1262013019561008/01/13 Noise-reduced turbomachine
1272013018670707/25/13 Unknown
1282013018022707/18/13 Fastening element and de-icing device of an aircraft gas-turbine engine
1292013016045906/27/13 Accessory mounting for a gas turbine
1302013016605606/27/13 Method for selecting a geometry of a blade
1312013015662606/20/13 Method for manufacturing a part by metal injection moulding
1322013015700006/20/13 Component and turbomachine having a component
1332013013957806/06/13 Pressure-measuring device and pressure-measuring a turbomachine
1342013014246706/06/13 Method and device for adjusting the bearing play in a ceramic hybrid bearing
1352013012950405/23/13 Bearing device and turbomachine having a bearing device
1362013012950505/23/13 Bearing device and turbomachine having a bearing device
1372013012411405/16/13 Method for determining a flow behaviour of a medium
1382013009817904/25/13 Accessory gearbox device for a jet engine
1392013009170404/18/13 Method for repairing rotor blades
1402013008690804/11/13 Gas turbine combustion chamber arrangement of axial type of construction
1412013005571603/07/13 Gas-turbine combustion chamber with a holding means of a seal for an attachment
1422013005709303/07/13 Generator and accessory gearbox device with a generator
1432013004262702/21/13 Combustion chamber head of a gas turbine with cooling and damping functions
1442013004509302/21/13 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
1452013002596201/31/13 Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element
1462013000814701/10/13 Aircraft gas turbine with variable bypass nozzle
1472013001124601/10/13 Gas-turbine aircraft engine with structural surface cooler
1482012032535412/27/12 Apparatus and the creation of an impingement jet generating annular swirls as well as turbomachine with an apparatus of this type
1492012032147712/20/12 Rotor device for a jet engine with a disk wheel and several rotor blades
1502012030465812/06/12 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
1512012029880211/29/12 De-icing device of an aircraft gas-turbine engine
1522012028513811/15/12 Aircraft gas-turbine engine with oil cooler in the engine cowling
1532012028835911/15/12 Gas-turbine engine with bleed-air tapping device
1542012028208211/08/12 Gas-turbine balancing device
1552012026642610/25/12 Method and surface strengthening and/or smoothing of an integrally bladed rotor area of a jet engine
1562012026961910/25/12 Fluid-flow machine
1572012024711010/04/12 Device for mixing fuel and air of a jet engine
1582012025131210/04/12 Stator of an axial compressor stage of a turbomachine
1592012025132410/04/12 Rotor of an axial compressor stage of a turbomachine
1602012024058309/27/12 Segmented combustion chamber head
1612012024059509/27/12 Combustion chamber head with holding means for seals on burners in gas turbines
1622012022239609/06/12 Jet engine device with a bypass duct
1632012020472308/16/12 Centrifugal oil separator for an aircraft engine
1642012017458807/12/12 Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
1652012014839606/14/12 Fluid-flow machine - blade with hybrid profile configuration
1662012012552305/24/12 Repair a sandwich-like component
1672012011797305/17/12 Gas-turbine combustion chamber with a cooling-air supply device
1682012009477704/19/12 Drive shaft, in particular radial shaft for a gas-turbine engine
1692012007666503/29/12 Cooled turbine blades for a gas-turbine engine
1702012006702503/22/12 Bloom mixer for a turbofan engine
1712012006710103/22/12 Forging tool
1722012004503202/23/12 Method for filmless radiographoc inspection of components
1732012003378702/09/12 Method for radiographic inspection of components
1742012003433302/09/12 Injection moulding tool for the manufacture of a hybrid component
1752012001766301/26/12 Method for the manufacture of a workpiece with defined surface
1762012002080201/26/12 Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
1772012001182701/19/12 Bleed air outlet in the bypass duct of a turbofan engine
1782012001478001/19/12 Fan downstream guide vanes of a turbofan engine
1792012000661401/12/12 Gas-turbine exhaust cone
1802011030896612/22/11 Method for manufacturing blisks
1812011028874011/24/11 Engine synchronization method
1822011027168011/10/11 Lean premix burner of a gas-turbine engine provided with a concentric annular central body
1832011027168111/10/11 Lean premix burner of a gas-turbine engine provided with a flow-guiding element
1842011027176511/10/11 Method and the detection of defects in the raceways of bearing shells and in the rolling elements of ceramic hybrid bearings
1852011027183711/10/11 Centrifugal oil separator for an aircraft engine
1862011025596410/20/11 Bypass duct of a turbofan engine
1872011021978209/15/11 Aerodynamically shaped supporting and/or fairing element in the bypass duct of a gas-turbine engine
1882011021517209/08/11 Aircraft engine with optimized oil heat exchanger
1892011020945809/01/11 Aircraft gas turbine engine
1902011021194709/01/11 Bypass duct of a turbo engine
1912011017984407/28/11 Method and surface strengthening of blisk blades
1922011018249907/28/11 Method for determining the surface coverage obtained by shot peening
1932011017399007/21/11 Intermediate casing for a gas-turbine engine
1942011014622306/23/11 Arrangement for the discharge of exhaust air separated from the lubricating oil de-aeration system of a gas-turbine engine
1952011014622406/23/11 Arrangement for the discharge of oil-venting air on a gas-turbine engine
1962011013992506/16/11 Arrangement for the suspension of a jet engine to a supporting structure
1972011012772806/02/11 Sealing rings for a labyrinth seal
1982011012113605/26/11 Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device
1992011011690805/19/11 Gas turbine engine with an arrangement for measuring the shaft rotation speed
2002011007007403/24/11 Gas turbine with a shroud and labyrinth-type sealing arrangement
2012011003866602/17/11 Engine shaft of hybrid design
2022011002709102/03/11 Axial-flow compressor, more particularly one for an aircraft gas-turbine engine
2032011001688301/27/11 Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine
2042011001105801/20/11 Turbofan engine
2052011001109301/20/11 Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall
2062011001403701/20/11 Axial-flow compressor with a flow pulse generator
2072011001404001/20/11 Fluid flow machine with blade row group
2082011001405701/20/11 Engine blade with excessive leading edge loading
2092011001405801/20/11 Propeller
2102011000523301/13/11 Combustion chamber head of a gas turbine
2112011000585801/13/11 Noise-reduced aircraft engine and reducing noise emissions of an aircraft engine
2122010030362912/02/10 Fluid flow machine with a blade row group featuring a meridional edge distance
2132010028777211/18/10 Method for surface strengthening and smoothening of metallic components
2142010028864811/18/10 Method and etching the surfaces of integrally bladed rotors
2152010025819910/14/10 Intake cone in a fiber compound material for a gas-turbine engine
2162010025901310/14/10 Abradable labyrinth seal for a fluid-flow machine
2172010023295409/16/10 Bypass duct of a turbofan engine
2182010022390509/09/10 Scoop of a running-gap control system of an aircraft gas turbine
2192010022434809/09/10 Method for the manufacture of an ejector nozzle tube
2202010021228508/26/10 Turboprop propulsion unit with pusher propeller
2212010021548108/26/10 Running-gap control system of an aircraft gas turbine
2222010019258808/05/10 Method 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
2232010017525607/15/10 Method for the manufacture of the blade tips of rotor wheels made in blisk design
2242010017609707/15/10 Arrangement for the repair of the blades of blisk drums by means of laser deposition welding
2252010015552606/24/10 Aircraft with tail propeller-engine layout
2262010016110706/24/10 Machine control for a numerically controlled machine tool
2272010014802706/17/10 Sensor bracket for at least one sensor on a gas turbine
2282010014844906/17/10 Segmented sealing lips for labyrinth sealing rings
2292010015069606/17/10 Fan casing for a jet engine
2302010013924106/10/10 Flow divider for a fan engine
2312010013927806/10/10 Method and the operation of a turboprop aircraft engine provided with pusher propellers
2322010014023006/10/10 Method for the manufacture of a welded rotor for a gas-turbine engine
2332010014314006/10/10 Fluid flow machine with sidewall boundary layer barrier
2342010012658905/27/10 Device for the prevention of high oil tank pressures under negative g conditions
2352010012666205/27/10 Method for the manufacture of hybrid components for aircraft gas turbines
2362010012965105/27/10 Hybrid component for a gas-turbine engine
2372010012251805/20/10 Oil system heating for aircraft gas turbines
2382010012448705/20/10 Multi-vane variable stator unit of a fluid flow machine
2392010010918405/06/10 Method for the manufacture of an engine shaft
2402010011170205/06/10 Hub cone for an aircraft engine
2412010011317005/06/10 Engine shaft for a gas-turbine engine
2422010011317105/06/10 Engine shaft in the form of a fiber-composite plastic tube with metallic driving and driven protrusions
2432010009852704/22/10 Fluid flow machine with peripheral energization near the suction side
2442010009853004/22/10 Compressor for a gas turbine
2452010009853604/22/10 Fluid flow machine with running gap retraction
2462010005111203/04/10 Intake cone for a gas-turbine engine
2472010003463702/11/10 Fluid flow machine
2482010002421402/04/10 Method for the manufacture of metallic components
2492010002131001/28/10 Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone



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