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Rolls royce Deutschland Ltd x26 Co Kg
Rolls royce Deutschland Ltd x26 Co Kg_20100107
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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
12015017643006/25/15 Cooled flange connection of a gas-turbine engine
22015017643406/25/15 Washer of a combustion chamber tile of a gas turbine
32015017644706/25/15 Jet engine device with at least one component that is arranged in a casing and that is rotatable to the casing
42015017652706/25/15 Aircraft gas turbine comprising an engine cowling with a thrust-reverser device
52015017652906/25/15 Aircraft gas turbine comprising a thrust-reverser device with cascade elements and an integrated rack and pinion drive
62015016749806/18/15 Joint between components
72015015948806/11/15 Turbine rotor blade of a gas turbine and cooling a blade tip of a turbine rotor blade of a gas turbine
82015014715905/28/15 Housing arrangement for a gas turbine
92015013566005/21/15 Jet engine comprising a device for spraying oil into an air-oil volume flow
102015013571905/21/15 Gas turbine combustor with tile having access hole for spark plug
112015013566305/21/15 Jet engine comprising a device for spraying oil
122015012860205/14/15 Heat shield for a gas turbine combustion chamber
132015012860305/14/15 Gas-turbine combustion chamber and its manufacture
142015012368005/07/15 Inductive sensor and manufacturing an inductive sensor
152015010779804/23/15 Unknown
162015008634403/26/15 Assembly for a fluid flow machine
172015006826203/12/15 Apparatus and shot peening of blade mounting areas on a rotor arrangement disc
182015007177703/12/15 Turbine guide wheel
192015005931503/05/15 Apparatus and bleeding off compressor air in a jet engine
202015006019403/05/15 Sound absorber, sound absorber assembly and an engine with a sound absorber assembly
212015005290802/26/15 Bleed duct assembly for a gas turbine engine
222015004719102/19/15 Method for balancing and assembling a turbine rotor
232015002712701/29/15 Combustion chamber tile of a gas turbine
242015003078701/29/15 Laser depositioning device and producing a component by direct laser depositioning
252015001330701/15/15 Turbofan jet engine
262015001695001/15/15 Device and discharging sealing air in a turbofan engine
272015001699401/15/15 Aircraft engine
282015000753101/08/15 Jet engine with at least one oil separator, through which an air-oil-volume flow can be guided
292015001038501/08/15 Gas turbine with high-pressure turbine cooling system
302015000024601/01/15 Jet engine with at least one oil separator
312014037355512/25/14 Accessory mounting for a gas turbine engine
322014036655512/18/14 Accessory mounting for a gas turbine engine
332014036327712/11/14 Assembly for a fluid flow machine
342014036328312/11/14 Shroud arrangement for a fluid flow machine
352014035614312/04/14 Assembly for a fluid flow machine
362014035614412/04/14 Assembly for a fluid flow machine
372014035245012/04/14 Method for determining a machining result during surface machining of components
382014031814810/30/14 Burner seal for gas-turbine combustion chamber head and heat shield
392014031815010/30/14 Removable swirler assembly for a combustion liner
402014031457810/23/14 Securing segment for the vibration damping of turbine blades and rotor device
412014023803008/28/14 Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes
422014024186008/28/14 Flight gas turbine with a first rotatable shaft
432014023408008/21/14 Device and bleeding compressor air in a turbofan engine
442014023409608/21/14 Turbomachine component with an erosion and corrosion resistant coating manufacturing such a component
452014016159106/12/14 Lubricant system
462014015044206/05/14 Gas turbine centripetal annular combustion chamber and flow guidance
472014014414505/29/14 Gas turbine combustion chamber
482014014414605/29/14 Tile fastening arrangement of a gas-turbine combustion chamber
492014014082005/22/14 Aeroengine sealing arrangement
502014014189405/22/14 Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
512014013050105/15/14 Combustion chamber tile of a gas turbine
522014013096405/15/14 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
532014012428905/08/14 Nozzle with guiding devices
542014012700105/08/14 Gas-turbine engine with a telescopic air inlet in the engine lining
552014012700305/08/14 Stator vane adjusting device of a gas turbine
562014012701005/08/14 Nozzle with guiding devices
572014012700505/08/14 Method for producing a component, component and turbomachine having a component
582014011602505/01/14 Aeroengine thrust reverser arrangement
592014011602605/01/14 Aeroengine thrust reverser arrangement
602014011988305/01/14 Bleed flow passage
612014011994205/01/14 Turbine rotor blade of a gas turbine
622014009653304/10/14 Bearing chamber venting system for an aircraft engine and providing a required pressure ratio at bearing chamber seals of an air-sealed bearing chamber
632014007953903/20/14 Turbine blade of a gas turbine with swirl-generating element and its manufacture
642014006492803/06/14 Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
652014006495203/06/14 Assembly of an axial turbomachine and manufacturing an assembly of this type
662014005056102/20/14 Oil supply supplying oil for a turboprop engine
672014003372302/06/14 Unknown
682014003373102/06/14 Method for fuel temperature control of a gas turbine
692014002653401/30/14 Oil supply system for an aircraft engine
702014002659201/30/14 Assembly for a jet engine of an aircraft
712014002670001/30/14 Accessory gearbox device for a jet engine
722014003010601/30/14 Compressor blade of a gas turbine as well as manufacturing said blade
732014003010701/30/14 Decoupled compressor blade of a gas turbine
742014003010901/30/14 Low-modulus gas-turbine compressor blade
752013032687612/12/13 Method for repairing compressor or turbine drums
762013031894512/05/13 Aviation gas turbine thrust reversing device
772013030640111/21/13 Sound absorber for a gas turbine exhaust cone, and the production thereof
782013030640211/21/13 Method for the production of a sound absorber, especially for a gas turbine exhaust cone
792013030640311/21/13 Method for the production of a sound absorber, especially for a gas turbine exhaust cone
802013030909111/21/13 Oil supply system for a propeller turbine engine
812013030214311/14/13 Cooling device for a jet engine
822013026642410/10/13 Stator vane adjusting device of a gas turbine
832013025973210/03/13 Method for producing engine components with a geometrically complex structure
842013023038309/05/13 Aircraft gas turbine with adjustable fan
852013021998208/29/13 Rolling tool device
862013021639108/22/13 Method for the production of a one-piece rotor area and one-piece rotor area
872013020575308/15/13 Aircraft gas turbine thrust-reversing device
882013020578808/15/13 Unknown
892013020667608/15/13 Measuring device having a pressure sensor
902013019904008/08/13 Device and treatment of high-pressure turbine blades of a gas turbine
912013019918708/08/13 Gas-turbine combustion chamber having non-symmetrical fuel nozzles
922013020208808/08/13 Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
932013019223208/01/13 Annular combustion chamber of a gas turbine
942013019561008/01/13 Noise-reduced turbomachine
952013018670707/25/13 Unknown
962013018022707/18/13 Fastening element and de-icing device of an aircraft gas-turbine engine
972013016045906/27/13 Accessory mounting for a gas turbine
982013016605606/27/13 Method for selecting a geometry of a blade
992013015662606/20/13 Method for manufacturing a part by metal injection moulding
1002013015700006/20/13 Component and turbomachine having a component
1012013013957806/06/13 Pressure-measuring device and pressure-measuring a turbomachine
1022013014246706/06/13 Method and device for adjusting the bearing play in a ceramic hybrid bearing
1032013012950405/23/13 Bearing device and turbomachine having a bearing device
1042013012950505/23/13 Bearing device and turbomachine having a bearing device
1052013012411405/16/13 Method for determining a flow behaviour of a medium
1062013009817904/25/13 Accessory gearbox device for a jet engine
1072013009170404/18/13 Method for repairing rotor blades
1082013008690804/11/13 Gas turbine combustion chamber arrangement of axial type of construction
1092013005571603/07/13 Gas-turbine combustion chamber with a holding means of a seal for an attachment
1102013005709303/07/13 Generator and accessory gearbox device with a generator
1112013004262702/21/13 Combustion chamber head of a gas turbine with cooling and damping functions
1122013004509302/21/13 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
1132013002596201/31/13 Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element
1142013000814701/10/13 Aircraft gas turbine with variable bypass nozzle
1152013001124601/10/13 Gas-turbine aircraft engine with structural surface cooler
1162012032535412/27/12 Apparatus and the creation of an impingement jet generating annular swirls as well as turbomachine with an apparatus of this type
1172012032147712/20/12 Rotor device for a jet engine with a disk wheel and several rotor blades
1182012030465812/06/12 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
1192012029880211/29/12 De-icing device of an aircraft gas-turbine engine
1202012028513811/15/12 Aircraft gas-turbine engine with oil cooler in the engine cowling
1212012028835911/15/12 Gas-turbine engine with bleed-air tapping device
1222012028208211/08/12 Gas-turbine balancing device
1232012026642610/25/12 Method and surface strengthening and/or smoothing of an integrally bladed rotor area of a jet engine
1242012026961910/25/12 Fluid-flow machine
1252012024711010/04/12 Device for mixing fuel and air of a jet engine
1262012025131210/04/12 Stator of an axial compressor stage of a turbomachine
1272012025132410/04/12 Rotor of an axial compressor stage of a turbomachine
1282012024058309/27/12 Segmented combustion chamber head
1292012024059509/27/12 Combustion chamber head with holding means for seals on burners in gas turbines
1302012022239609/06/12 Jet engine device with a bypass duct
1312012020472308/16/12 Centrifugal oil separator for an aircraft engine
1322012017458807/12/12 Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
1332012014839606/14/12 Fluid-flow machine - blade with hybrid profile configuration
1342012012552305/24/12 Repair a sandwich-like component
1352012011797305/17/12 Gas-turbine combustion chamber with a cooling-air supply device
1362012009477704/19/12 Drive shaft, in particular radial shaft for a gas-turbine engine
1372012007666503/29/12 Cooled turbine blades for a gas-turbine engine
1382012006702503/22/12 Bloom mixer for a turbofan engine
1392012006710103/22/12 Forging tool
1402012004503202/23/12 Method for filmless radiographoc inspection of components
1412012003378702/09/12 Method for radiographic inspection of components
1422012003433302/09/12 Injection moulding tool for the manufacture of a hybrid component
1432012001766301/26/12 Method for the manufacture of a workpiece with defined surface
1442012002080201/26/12 Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
1452012001182701/19/12 Bleed air outlet in the bypass duct of a turbofan engine
1462012001478001/19/12 Fan downstream guide vanes of a turbofan engine
1472012000661401/12/12 Gas-turbine exhaust cone
1482011030896612/22/11 Method for manufacturing blisks
1492011028874011/24/11 Engine synchronization method
1502011027168011/10/11 Lean premix burner of a gas-turbine engine provided with a concentric annular central body
1512011027168111/10/11 Lean premix burner of a gas-turbine engine provided with a flow-guiding element
1522011027176511/10/11 Method and the detection of defects in the raceways of bearing shells and in the rolling elements of ceramic hybrid bearings
1532011027183711/10/11 Centrifugal oil separator for an aircraft engine
1542011025596410/20/11 Bypass duct of a turbofan engine
1552011021978209/15/11 Aerodynamically shaped supporting and/or fairing element in the bypass duct of a gas-turbine engine
1562011021517209/08/11 Aircraft engine with optimized oil heat exchanger
1572011020945809/01/11 Aircraft gas turbine engine
1582011021194709/01/11 Bypass duct of a turbo engine
1592011017984407/28/11 Method and surface strengthening of blisk blades
1602011018249907/28/11 Method for determining the surface coverage obtained by shot peening
1612011017399007/21/11 Intermediate casing for a gas-turbine engine
1622011014622306/23/11 Arrangement for the discharge of exhaust air separated from the lubricating oil de-aeration system of a gas-turbine engine
1632011014622406/23/11 Arrangement for the discharge of oil-venting air on a gas-turbine engine
1642011013992506/16/11 Arrangement for the suspension of a jet engine to a supporting structure
1652011012772806/02/11 Sealing rings for a labyrinth seal
1662011012113605/26/11 Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device
1672011011690805/19/11 Gas turbine engine with an arrangement for measuring the shaft rotation speed
1682011007007403/24/11 Gas turbine with a shroud and labyrinth-type sealing arrangement
1692011003866602/17/11 Engine shaft of hybrid design
1702011002709102/03/11 Axial-flow compressor, more particularly one for an aircraft gas-turbine engine
1712011001688301/27/11 Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine
1722011001105801/20/11 Turbofan engine
1732011001109301/20/11 Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall
1742011001403701/20/11 Axial-flow compressor with a flow pulse generator
1752011001404001/20/11 Fluid flow machine with blade row group
1762011001405701/20/11 Engine blade with excessive leading edge loading
1772011001405801/20/11 Propeller
1782011000523301/13/11 Combustion chamber head of a gas turbine
1792011000585801/13/11 Noise-reduced aircraft engine and reducing noise emissions of an aircraft engine
1802010030362912/02/10 Fluid flow machine with a blade row group featuring a meridional edge distance
1812010028777211/18/10 Method for surface strengthening and smoothening of metallic components
1822010028864811/18/10 Method and etching the surfaces of integrally bladed rotors
1832010025819910/14/10 Intake cone in a fiber compound material for a gas-turbine engine
1842010025901310/14/10 Abradable labyrinth seal for a fluid-flow machine
1852010023295409/16/10 Bypass duct of a turbofan engine
1862010022390509/09/10 Scoop of a running-gap control system of an aircraft gas turbine
1872010022434809/09/10 Method for the manufacture of an ejector nozzle tube
1882010021228508/26/10 Turboprop propulsion unit with pusher propeller
1892010021548108/26/10 Running-gap control system of an aircraft gas turbine
1902010019258808/05/10 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
1912010017525607/15/10 Method for the manufacture of the blade tips of rotor wheels made in blisk design
1922010017609707/15/10 Arrangement for the repair of the blades of blisk drums by means of laser deposition welding
1932010015552606/24/10 Aircraft with tail propeller-engine layout
1942010016110706/24/10 Machine control for a numerically controlled machine tool
1952010014802706/17/10 Sensor bracket for at least one sensor on a gas turbine
1962010014844906/17/10 Segmented sealing lips for labyrinth sealing rings
1972010015069606/17/10 Fan casing for a jet engine
1982010013924106/10/10 Flow divider for a fan engine
1992010013927806/10/10 Method and the operation of a turboprop aircraft engine provided with pusher propellers
2002010014023006/10/10 Method for the manufacture of a welded rotor for a gas-turbine engine
2012010014314006/10/10 Fluid flow machine with sidewall boundary layer barrier
2022010012658905/27/10 Device for the prevention of high oil tank pressures under negative g conditions
2032010012666205/27/10 Method for the manufacture of hybrid components for aircraft gas turbines
2042010012965105/27/10 Hybrid component for a gas-turbine engine
2052010012251805/20/10 Oil system heating for aircraft gas turbines
2062010012448705/20/10 Multi-vane variable stator unit of a fluid flow machine
2072010010918405/06/10 Method for the manufacture of an engine shaft
2082010011170205/06/10 Hub cone for an aircraft engine
2092010011317005/06/10 Engine shaft for a gas-turbine engine
2102010011317105/06/10 Engine shaft in the form of a fiber-composite plastic tube with metallic driving and driven protrusions
2112010009852704/22/10 Fluid flow machine with peripheral energization near the suction side
2122010009853004/22/10 Compressor for a gas turbine
2132010009853604/22/10 Fluid flow machine with running gap retraction
2142010005111203/04/10 Intake cone for a gas-turbine engine
2152010003463702/11/10 Fluid flow machine
2162010002421402/04/10 Method for the manufacture of metallic components
2172010002131001/28/10 Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
2182010001495601/21/10 Fluid flow machine featuring a groove on a running gap of a blade end
2192010001496001/21/10 Gas-turbine engine with variable stator vanes
2202010000577601/14/10 Fuel supply system for a gas-turbine engine
2212010000019801/07/10 Gas turbine with at least one multi-stage compressor unit including several compressor modules
2222010000022601/07/10 Turbofan engine with at least one driving at least one generator
2232009031400412/24/09 Turboprop engine with an the generation of a cooling airflow
2242009031723212/24/09 Blade shroud with aperture
2252013032687612/12/13 Method for repairing compressor or turbine drums
2262010002131001/28/10 Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
2272010001496001/21/10 Gas-turbine engine with variable stator vanes
2282010000577601/14/10 Fuel supply system for a gas-turbine engine
2292010000022601/07/10 Turbofan engine with at least one driving at least one generator



ARCHIVE: New 2015 2014 2013 2012 2011 2010 2009



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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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