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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




Count Application # Date Rolls royce Deutschland Ltd & Co Kg patents (updated weekly) - BOOKMARK this page
12015024064308/27/15  new patent  Group of blade rows
22015024064608/27/15  new patent  Group of blade rows
32015024064708/27/15  new patent  Group of blade rows
42015024064808/27/15  new patent  Group of blade rows
52015024083608/27/15  new patent  Group of blade rows
62015024093108/27/15  new patent  Gearing arrangement
72015020991507/30/15 Method for repairing an abradable coating of a compressor of a gas turbine
82015017643006/25/15 Cooled flange connection of a gas-turbine engine
92015017643406/25/15 Washer of a combustion chamber tile of a gas turbine
102015017644706/25/15 Jet engine device with at least one component that is arranged in a casing and that is rotatable to the casing
112015017652706/25/15 Aircraft gas turbine comprising an engine cowling with a thrust-reverser device
122015017652906/25/15 Aircraft gas turbine comprising a thrust-reverser device with cascade elements and an integrated rack and pinion drive
132015016749806/18/15 Joint between components
142015015948806/11/15 Turbine rotor blade of a gas turbine and cooling a blade tip of a turbine rotor blade of a gas turbine
152015014715905/28/15 Housing arrangement for a gas turbine
162015013566005/21/15 Jet engine comprising a device for spraying oil into an air-oil volume flow
172015013571905/21/15 Gas turbine combustor with tile having access hole for spark plug
182015013566305/21/15 Jet engine comprising a device for spraying oil
192015012860205/14/15 Heat shield for a gas turbine combustion chamber
202015012860305/14/15 Gas-turbine combustion chamber and its manufacture
212015012368005/07/15 Inductive sensor and manufacturing an inductive sensor
222015010779804/23/15 Unknown
232015008634403/26/15 Assembly for a fluid flow machine
242015006826203/12/15 Apparatus and shot peening of blade mounting areas on a rotor arrangement disc
252015007177703/12/15 Turbine guide wheel
262015005931503/05/15 Apparatus and bleeding off compressor air in a jet engine
272015006019403/05/15 Sound absorber, sound absorber assembly and an engine with a sound absorber assembly
282015005290802/26/15 Bleed duct assembly for a gas turbine engine
292015004719102/19/15 Method for balancing and assembling a turbine rotor
302015002712701/29/15 Combustion chamber tile of a gas turbine
312015003078701/29/15 Laser depositioning device and producing a component by direct laser depositioning
322015001330701/15/15 Turbofan jet engine
332015001695001/15/15 Device and discharging sealing air in a turbofan engine
342015001699401/15/15 Aircraft engine
352015000753101/08/15 Jet engine with at least one oil separator, through which an air-oil-volume flow can be guided
362015001038501/08/15 Gas turbine with high-pressure turbine cooling system
372015000024601/01/15 Jet engine with at least one oil separator
382014037355512/25/14 Accessory mounting for a gas turbine engine
392014036655512/18/14 Accessory mounting for a gas turbine engine
402014036327712/11/14 Assembly for a fluid flow machine
412014036328312/11/14 Shroud arrangement for a fluid flow machine
422014035614312/04/14 Assembly for a fluid flow machine
432014035614412/04/14 Assembly for a fluid flow machine
442014035245012/04/14 Method for determining a machining result during surface machining of components
452014031814810/30/14 Burner seal for gas-turbine combustion chamber head and heat shield
462014031815010/30/14 Removable swirler assembly for a combustion liner
472014031457810/23/14 Securing segment for the vibration damping of turbine blades and rotor device
482014023803008/28/14 Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes
492014024186008/28/14 Flight gas turbine with a first rotatable shaft
502014023408008/21/14 Device and bleeding compressor air in a turbofan engine
512014023409608/21/14 Turbomachine component with an erosion and corrosion resistant coating manufacturing such a component
522014016159106/12/14 Lubricant system
532014015044206/05/14 Gas turbine centripetal annular combustion chamber and flow guidance
542014014414505/29/14 Gas turbine combustion chamber
552014014414605/29/14 Tile fastening arrangement of a gas-turbine combustion chamber
562014014082005/22/14 Aeroengine sealing arrangement
572014014189405/22/14 Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
582014013050105/15/14 Combustion chamber tile of a gas turbine
592014013096405/15/14 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
602014012428905/08/14 Nozzle with guiding devices
612014012700105/08/14 Gas-turbine engine with a telescopic air inlet in the engine lining
622014012700305/08/14 Stator vane adjusting device of a gas turbine
632014012701005/08/14 Nozzle with guiding devices
642014012700505/08/14 Method for producing a component, component and turbomachine having a component
652014011602505/01/14 Aeroengine thrust reverser arrangement
662014011602605/01/14 Aeroengine thrust reverser arrangement
672014011988305/01/14 Bleed flow passage
682014011994205/01/14 Turbine rotor blade of a gas turbine
692014009653304/10/14 Bearing chamber venting system for an aircraft engine and providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber
702014007953903/20/14 Turbine blade of a gas turbine with swirl-generating element and its manufacture
712014006492803/06/14 Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
722014006495203/06/14 Assembly of an axial turbomachine and manufacturing an assembly of this type
732014005056102/20/14 Oil supply supplying oil for a turboprop engine
742014003372302/06/14 Unknown
752014003373102/06/14 Method for fuel temperature control of a gas turbine
762014002653401/30/14 Oil supply system for an aircraft engine
772014002659201/30/14 Assembly for a jet engine of an aircraft
782014002670001/30/14 Accessory gearbox device for a jet engine
792014003010601/30/14 Compressor blade of a gas turbine as well as manufacturing said blade
802014003010701/30/14 Decoupled compressor blade of a gas turbine
812014003010901/30/14 Low-modulus gas-turbine compressor blade
822013032687612/12/13 Method for repairing compressor or turbine drums
832013031894512/05/13 Aviation gas turbine thrust reversing device
842013030640111/21/13 Sound absorber for a gas turbine exhaust cone, and the production thereof
852013030640211/21/13 Method for the production of a sound absorber, especially for a gas turbine exhaust cone
862013030640311/21/13 Method for the production of a sound absorber, especially for a gas turbine exhaust cone
872013030909111/21/13 Oil supply system for a propeller turbine engine
882013030214311/14/13 Cooling device for a jet engine
892013026642410/10/13 Stator vane adjusting device of a gas turbine
902013025973210/03/13 Method for producing engine components with a geometrically complex structure
912013023038309/05/13 Aircraft gas turbine with adjustable fan
922013021998208/29/13 Rolling tool device
932013021639108/22/13 Method for the production of a one-piece rotor area and one-piece rotor area
942013020575308/15/13 Aircraft gas turbine thrust-reversing device
952013020578808/15/13 Unknown
962013020667608/15/13 Measuring device having a pressure sensor
972013019904008/08/13 Device and treatment of high-pressure turbine blades of a gas turbine
982013019918708/08/13 Gas-turbine combustion chamber having non-symmetrical fuel nozzles
992013020208808/08/13 Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
1002013019223208/01/13 Annular combustion chamber of a gas turbine
1012013019561008/01/13 Noise-reduced turbomachine
1022013018670707/25/13 Unknown
1032013018022707/18/13 Fastening element and de-icing device of an aircraft gas-turbine engine
1042013016045906/27/13 Accessory mounting for a gas turbine
1052013016605606/27/13 Method for selecting a geometry of a blade
1062013015662606/20/13 Method for manufacturing a part by metal injection moulding
1072013015700006/20/13 Component and turbomachine having a component
1082013013957806/06/13 Pressure-measuring device and pressure-measuring a turbomachine
1092013014246706/06/13 Method and device for adjusting the bearing play in a ceramic hybrid bearing
1102013012950405/23/13 Bearing device and turbomachine having a bearing device
1112013012950505/23/13 Bearing device and turbomachine having a bearing device
1122013012411405/16/13 Method for determining a flow behaviour of a medium
1132013009817904/25/13 Accessory gearbox device for a jet engine
1142013009170404/18/13 Method for repairing rotor blades
1152013008690804/11/13 Gas turbine combustion chamber arrangement of axial type of construction
1162013005571603/07/13 Gas-turbine combustion chamber with a holding means of a seal for an attachment
1172013005709303/07/13 Generator and accessory gearbox device with a generator
1182013004262702/21/13 Combustion chamber head of a gas turbine with cooling and damping functions
1192013004509302/21/13 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
1202013002596201/31/13 Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element
1212013000814701/10/13 Aircraft gas turbine with variable bypass nozzle
1222013001124601/10/13 Gas-turbine aircraft engine with structural surface cooler
1232012032535412/27/12 Apparatus and the creation of an impingement jet generating annular swirls as well as turbomachine with an apparatus of this type
1242012032147712/20/12 Rotor device for a jet engine with a disk wheel and several rotor blades
1252012030465812/06/12 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
1262012029880211/29/12 De-icing device of an aircraft gas-turbine engine
1272012028513811/15/12 Aircraft gas-turbine engine with oil cooler in the engine cowling
1282012028835911/15/12 Gas-turbine engine with bleed-air tapping device
1292012028208211/08/12 Gas-turbine balancing device
1302012026642610/25/12 Method and surface strengthening and/or smoothing of an integrally bladed rotor area of a jet engine
1312012026961910/25/12 Fluid-flow machine
1322012024711010/04/12 Device for mixing fuel and air of a jet engine
1332012025131210/04/12 Stator of an axial compressor stage of a turbomachine
1342012025132410/04/12 Rotor of an axial compressor stage of a turbomachine
1352012024058309/27/12 Segmented combustion chamber head
1362012024059509/27/12 Combustion chamber head with holding means for seals on burners in gas turbines
1372012022239609/06/12 Jet engine device with a bypass duct
1382012020472308/16/12 Centrifugal oil separator for an aircraft engine
1392012017458807/12/12 Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
1402012014839606/14/12 Fluid-flow machine - blade with hybrid profile configuration
1412012012552305/24/12 Repair a sandwich-like component
1422012011797305/17/12 Gas-turbine combustion chamber with a cooling-air supply device
1432012009477704/19/12 Drive shaft, in particular radial shaft for a gas-turbine engine
1442012007666503/29/12 Cooled turbine blades for a gas-turbine engine
1452012006702503/22/12 Bloom mixer for a turbofan engine
1462012006710103/22/12 Forging tool
1472012004503202/23/12 Method for filmless radiographoc inspection of components
1482012003378702/09/12 Method for radiographic inspection of components
1492012003433302/09/12 Injection moulding tool for the manufacture of a hybrid component
1502012001766301/26/12 Method for the manufacture of a workpiece with defined surface
1512012002080201/26/12 Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
1522012001182701/19/12 Bleed air outlet in the bypass duct of a turbofan engine
1532012001478001/19/12 Fan downstream guide vanes of a turbofan engine
1542012000661401/12/12 Gas-turbine exhaust cone
1552011030896612/22/11 Method for manufacturing blisks
1562011028874011/24/11 Engine synchronization method
1572011027168011/10/11 Lean premix burner of a gas-turbine engine provided with a concentric annular central body
1582011027168111/10/11 Lean premix burner of a gas-turbine engine provided with a flow-guiding element
1592011027176511/10/11 Method and the detection of defects in the raceways of bearing shells and in the rolling elements of ceramic hybrid bearings
1602011027183711/10/11 Centrifugal oil separator for an aircraft engine
1612011025596410/20/11 Bypass duct of a turbofan engine
1622011021978209/15/11 Aerodynamically shaped supporting and/or fairing element in the bypass duct of a gas-turbine engine
1632011021517209/08/11 Aircraft engine with optimized oil heat exchanger
1642011020945809/01/11 Aircraft gas turbine engine
1652011021194709/01/11 Bypass duct of a turbo engine
1662011017984407/28/11 Method and surface strengthening of blisk blades
1672011018249907/28/11 Method for determining the surface coverage obtained by shot peening
1682011017399007/21/11 Intermediate casing for a gas-turbine engine
1692011014622306/23/11 Arrangement for the discharge of exhaust air separated from the lubricating oil de-aeration system of a gas-turbine engine
1702011014622406/23/11 Arrangement for the discharge of oil-venting air on a gas-turbine engine
1712011013992506/16/11 Arrangement for the suspension of a jet engine to a supporting structure
1722011012772806/02/11 Sealing rings for a labyrinth seal
1732011012113605/26/11 Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device
1742011011690805/19/11 Gas turbine engine with an arrangement for measuring the shaft rotation speed
1752011007007403/24/11 Gas turbine with a shroud and labyrinth-type sealing arrangement
1762011003866602/17/11 Engine shaft of hybrid design
1772011002709102/03/11 Axial-flow compressor, more particularly one for an aircraft gas-turbine engine
1782011001688301/27/11 Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine
1792011001105801/20/11 Turbofan engine
1802011001109301/20/11 Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall
1812011001403701/20/11 Axial-flow compressor with a flow pulse generator
1822011001404001/20/11 Fluid flow machine with blade row group
1832011001405701/20/11 Engine blade with excessive leading edge loading
1842011001405801/20/11 Propeller
1852011000523301/13/11 Combustion chamber head of a gas turbine
1862011000585801/13/11 Noise-reduced aircraft engine and reducing noise emissions of an aircraft engine
1872010030362912/02/10 Fluid flow machine with a blade row group featuring a meridional edge distance
1882010028777211/18/10 Method for surface strengthening and smoothening of metallic components
1892010028864811/18/10 Method and etching the surfaces of integrally bladed rotors
1902010025819910/14/10 Intake cone in a fiber compound material for a gas-turbine engine
1912010025901310/14/10 Abradable labyrinth seal for a fluid-flow machine
1922010023295409/16/10 Bypass duct of a turbofan engine
1932010022390509/09/10 Scoop of a running-gap control system of an aircraft gas turbine
1942010022434809/09/10 Method for the manufacture of an ejector nozzle tube
1952010021228508/26/10 Turboprop propulsion unit with pusher propeller
1962010021548108/26/10 Running-gap control system of an aircraft gas turbine
1972010019258808/05/10 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
1982010017525607/15/10 Method for the manufacture of the blade tips of rotor wheels made in blisk design
1992010017609707/15/10 Arrangement for the repair of the blades of blisk drums by means of laser deposition welding
2002010015552606/24/10 Aircraft with tail propeller-engine layout
2012010016110706/24/10 Machine control for a numerically controlled machine tool
2022010014802706/17/10 Sensor bracket for at least one sensor on a gas turbine
2032010014844906/17/10 Segmented sealing lips for labyrinth sealing rings
2042010015069606/17/10 Fan casing for a jet engine
2052010013924106/10/10 Flow divider for a fan engine
2062010013927806/10/10 Method and the operation of a turboprop aircraft engine provided with pusher propellers
2072010014023006/10/10 Method for the manufacture of a welded rotor for a gas-turbine engine
2082010014314006/10/10 Fluid flow machine with sidewall boundary layer barrier
2092010012658905/27/10 Device for the prevention of high oil tank pressures under negative g conditions
2102010012666205/27/10 Method for the manufacture of hybrid components for aircraft gas turbines
2112010012965105/27/10 Hybrid component for a gas-turbine engine
2122010012251805/20/10 Oil system heating for aircraft gas turbines
2132010012448705/20/10 Multi-vane variable stator unit of a fluid flow machine
2142010010918405/06/10 Method for the manufacture of an engine shaft
2152010011170205/06/10 Hub cone for an aircraft engine
2162010011317005/06/10 Engine shaft for a gas-turbine engine
2172010011317105/06/10 Engine shaft in the form of a fiber-composite plastic tube with metallic driving and driven protrusions
2182010009852704/22/10 Fluid flow machine with peripheral energization near the suction side
2192010009853004/22/10 Compressor for a gas turbine
2202010009853604/22/10 Fluid flow machine with running gap retraction
2212010005111203/04/10 Intake cone for a gas-turbine engine
2222010003463702/11/10 Fluid flow machine
2232010002421402/04/10 Method for the manufacture of metallic components
2242010002131001/28/10 Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
2252010001495601/21/10 Fluid flow machine featuring a groove on a running gap of a blade end
2262010001496001/21/10 Gas-turbine engine with variable stator vanes
2272010000577601/14/10 Fuel supply system for a gas-turbine engine
2282010000019801/07/10 Gas turbine with at least one multi-stage compressor unit including several compressor modules
2292010000022601/07/10 Turbofan engine with at least one driving at least one generator
2302009031400412/24/09 Turboprop engine with an the generation of a cooling airflow
2312009031723212/24/09 Blade shroud with aperture
2322013032687612/12/13 Method for repairing compressor or turbine drums
2332010002131001/28/10 Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
2342010001496001/21/10 Gas-turbine engine with variable stator vanes
2352010000577601/14/10 Fuel supply system for a gas-turbine engine
2362010000022601/07/10 Turbofan engine with at least one driving at least one generator



ARCHIVE: New 2015 2014 2013 2012 2011 2010 2009



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