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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



Assembly for a fluid flow machine

Rolls-royce Deutschland Ltd & Co Kg

Assembly for a fluid flow machine

Shroud arrangement for a fluid flow machine

Rolls-royce Deutschland Ltd & Co Kg

Shroud arrangement for a fluid flow machine

Shroud arrangement for a fluid flow machine

Rolls-royce Deutschland Ltd & Co Kg

Assembly for a fluid flow machine

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
12014036655512/18/14 new patent  Accessory mounting for a gas turbine engine
22014036327712/11/14Assembly for a fluid flow machine
32014036328312/11/14Shroud arrangement for a fluid flow machine
42014035614312/04/14Assembly for a fluid flow machine
52014035614412/04/14Assembly for a fluid flow machine
62014035245012/04/14Method for determining a machining result during surface machining of components
72014031814810/30/14Burner seal for gas-turbine combustion chamber head and heat shield
82014031815010/30/14Removable swirler assembly for a combustion liner
92014031457810/23/14Securing segment for the vibration damping of turbine blades and rotor device
102014023803008/28/14Impingement-effusion cooled tile of a gas-turbine combustion chamber with elongated effusion holes
112014024186008/28/14Flight gas turbine with a first rotatable shaft
122014023408008/21/14Device and method for bleeding compressor air in a turbofan engine
132014023409608/21/14Turbomachine component with an erosion and corrosion resistant coating system and method for manufacturing such a component
142014016159106/12/14Lubricant system
152014015044206/05/14Gas turbine centripetal annular combustion chamber and method for flow guidance
162014014414505/29/14Gas turbine combustion chamber
172014014414605/29/14Tile fastening arrangement of a gas-turbine combustion chamber
182014014082005/22/14Aeroengine sealing arrangement
192014014189405/22/14Shaft of a gas-turbine engine, in particular a radial shaft or a shaft arranged at an angle to the machine axis
202014013050105/15/14Combustion chamber tile of a gas turbine
212014013096405/15/14Method 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
222014012428905/08/14Nozzle with guiding devices
232014012700105/08/14Gas-turbine engine with a telescopic air inlet in the engine lining
242014012700305/08/14Stator vane adjusting device of a gas turbine
252014012701005/08/14Nozzle with guiding devices
262014012700505/08/14Method for producing a component, component and turbomachine having a component
272014011602505/01/14Aeroengine thrust reverser arrangement
282014011602605/01/14Aeroengine thrust reverser arrangement
292014011988305/01/14Bleed flow passage
302014011994205/01/14Turbine rotor blade of a gas turbine
312014009653304/10/14Bearing 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
322014007953903/20/14Turbine blade of a gas turbine with swirl-generating element and method for its manufacture
332014006492803/06/14Engine casing of an aircraft gas turbine having sound-absorbing elements in the fan inflow region
342014006495203/06/14Assembly of an axial turbomachine and method for manufacturing an assembly of this type
352014005056102/20/14Oil supply system and method for supplying oil for a turboprop engine
362014003372302/06/14Unknown
372014003373102/06/14Method for fuel temperature control of a gas turbine
382014002653401/30/14Oil supply system for an aircraft engine
392014002659201/30/14Assembly for a jet engine of an aircraft
402014002670001/30/14Accessory gearbox device for a jet engine
412014003010601/30/14Compressor blade of a gas turbine as well as method for manufacturing said blade
422014003010701/30/14Decoupled compressor blade of a gas turbine
432014003010901/30/14Low-modulus gas-turbine compressor blade
442013032687612/12/13Method for repairing compressor or turbine drums
452013031894512/05/13Aviation gas turbine thrust reversing device
462013030640111/21/13Sound absorber for a gas turbine exhaust cone, and method for the production thereof
472013030640211/21/13Method for the production of a sound absorber, especially for a gas turbine exhaust cone
482013030640311/21/13Method for the production of a sound absorber, especially for a gas turbine exhaust cone
492013030909111/21/13Oil supply system for a propeller turbine engine
502013030214311/14/13Cooling device for a jet engine
512013026642410/10/13Stator vane adjusting device of a gas turbine
522013025973210/03/13Method for producing engine components with a geometrically complex structure
532013023038309/05/13Aircraft gas turbine with adjustable fan
542013021998208/29/13Rolling tool device
552013021639108/22/13Method for the production of a one-piece rotor area and one-piece rotor area
562013020575308/15/13Aircraft gas turbine thrust-reversing device
572013020578808/15/13Unknown
582013020667608/15/13Measuring device having a pressure sensor
592013019904008/08/13Device and method for treatment of high-pressure turbine blades of a gas turbine
602013019918708/08/13Gas-turbine combustion chamber having non-symmetrical fuel nozzles
612013020208808/08/13Method for radiographically inspection a component by means of x-ray beams using a smoothing agent and smoothing agent for carrying out the method
622013019223208/01/13Annular combustion chamber of a gas turbine
632013019561008/01/13Noise-reduced turbomachine
642013018670707/25/13Unknown
652013018022707/18/13Fastening element and de-icing device of an aircraft gas-turbine engine
662013016045906/27/13Accessory mounting for a gas turbine
672013016605606/27/13Method for selecting a geometry of a blade
682013015662606/20/13Method for manufacturing a part by metal injection moulding
692013015700006/20/13Component and turbomachine having a component
702013013957806/06/13Pressure-measuring device and pressure-measuring method for a turbomachine
712013014246706/06/13Method and device for adjusting the bearing play in a ceramic hybrid bearing
722013012950405/23/13Bearing device and turbomachine having a bearing device
732013012950505/23/13Bearing device and turbomachine having a bearing device
742013012411405/16/13Method for determining a flow behaviour of a medium
752013009817904/25/13Accessory gearbox device for a jet engine
762013009170404/18/13Method for repairing rotor blades
772013008690804/11/13Gas turbine combustion chamber arrangement of axial type of construction
782013005571603/07/13Gas-turbine combustion chamber with a holding means of a seal for an attachment
792013005709303/07/13Generator and accessory gearbox device with a generator
802013004262702/21/13Combustion chamber head of a gas turbine with cooling and damping functions
812013004509302/21/13Method for the manufacture of a component for high thermal loads, a component producible by this method and an aircraft engine provided with the component
822013002596201/31/13Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element
832013000814701/10/13Aircraft gas turbine with variable bypass nozzle
842013001124601/10/13Gas-turbine aircraft engine with structural surface cooler
852012032535412/27/12Apparatus and method for the creation of an impingement jet generating annular swirls as well as turbomachine with an apparatus of this type
862012032147712/20/12Rotor device for a jet engine with a disk wheel and several rotor blades
872012030465812/06/12Segment 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
882012029880211/29/12De-icing device of an aircraft gas-turbine engine
892012028513811/15/12Aircraft gas-turbine engine with oil cooler in the engine cowling
902012028835911/15/12Gas-turbine engine with bleed-air tapping device
912012028208211/08/12Gas-turbine balancing device
922012026642610/25/12Surface strengthening and/or smoothing of an integrally bladed rotor area of a jet engine
932012026961910/25/12Fluid-flow machine
942012024711010/04/12Device for mixing fuel and air of a jet engine
952012025131210/04/12Stator of an axial compressor stage of a turbomachine
962012025132410/04/12Rotor of an axial compressor stage of a turbomachine
972012024058309/27/12Segmented combustion chamber head
982012024059509/27/12Combustion chamber head with holding means for seals on burners in gas turbines
992012022239609/06/12Jet engine device with a bypass duct
1002012020472308/16/12Centrifugal oil separator for an aircraft engine
1012012017458807/12/12Gas-turbine lean combustor with fuel nozzle with controlled fuel inhomogeneity
1022012014839606/14/12Fluid-flow machine - blade with hybrid profile configuration
1032012012552305/24/12Repair method for a sandwich-like component
1042012011797305/17/12Gas-turbine combustion chamber with a cooling-air supply device
1052012009477704/19/12Drive shaft, in particular radial shaft for a gas-turbine engine
1062012007666503/29/12Cooled turbine blades for a gas-turbine engine
1072012006702503/22/12Bloom mixer for a turbofan engine
1082012006710103/22/12Forging tool
1092012004503202/23/12Method for filmless radiographoc inspection of components
1102012003378702/09/12Method for radiographic inspection of components
1112012003433302/09/12Injection moulding tool for the manufacture of a hybrid component
1122012001766301/26/12Method for the manufacture of a workpiece with defined surface
1132012002080201/26/12Compressor blade of a gas-turbine engine with a self-sharpening leading-edge structure
1142012001182701/19/12Bleed air outlet in the bypass duct of a turbofan engine
1152012001478001/19/12Fan downstream guide vanes of a turbofan engine
1162012000661401/12/12Gas-turbine exhaust cone
1172011030896612/22/11Method for manufacturing blisks
1182011028874011/24/11Engine synchronization method
1192011027168011/10/11Lean premix burner of a gas-turbine engine provided with a concentric annular central body
1202011027168111/10/11Lean premix burner of a gas-turbine engine provided with a flow-guiding element
1212011027176511/10/11The detection of defects in the raceways of bearing shells and in the rolling elements of ceramic hybrid bearings
1222011027183711/10/11Centrifugal oil separator for an aircraft engine
1232011025596410/20/11Bypass duct of a turbofan engine
1242011021978209/15/11Aerodynamically shaped supporting and/or fairing element in the bypass duct of a gas-turbine engine
1252011021517209/08/11Aircraft engine with optimized oil heat exchanger
1262011020945809/01/11Aircraft gas turbine engine
1272011021194709/01/11Bypass duct of a turbo engine
1282011017984407/28/11Surface strengthening of blisk blades
1292011018249907/28/11Method for determining the surface coverage obtained by shot peening
1302011017399007/21/11Intermediate casing for a gas-turbine engine
1312011014622306/23/11Arrangement for the discharge of exhaust air separated from the lubricating oil de-aeration system of a gas-turbine engine
1322011014622406/23/11Arrangement for the discharge of oil-venting air on a gas-turbine engine
1332011013992506/16/11Arrangement for the suspension of a jet engine to a supporting structure
1342011012772806/02/11Sealing rings for a labyrinth seal
1352011012113605/26/11Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device
1362011011690805/19/11Gas turbine engine with an arrangement for measuring the shaft rotation speed
1372011007007403/24/11Gas turbine with a shroud and labyrinth-type sealing arrangement
1382011003866602/17/11Engine shaft of hybrid design
1392011002709102/03/11Axial-flow compressor, more particularly one for an aircraft gas-turbine engine
1402011001688301/27/11Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine
1412011001105801/20/11Turbofan engine
1422011001109301/20/11Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall
1432011001403701/20/11Axial-flow compressor with a flow pulse generator
1442011001404001/20/11Fluid flow machine with blade row group
1452011001405701/20/11Engine blade with excessive leading edge loading
1462011001405801/20/11Propeller
1472011000523301/13/11Combustion chamber head of a gas turbine
1482011000585801/13/11Noise-reduced aircraft engine and method for reducing noise emissions of an aircraft engine
1492010030362912/02/10Fluid flow machine with a blade row group featuring a meridional edge distance
1502010028777211/18/10Method for surface strengthening and smoothening of metallic components
1512010028864811/18/10Etching the surfaces of integrally bladed rotors
1522010025819910/14/10Intake cone in a fiber compound material for a gas-turbine engine
1532010025901310/14/10Abradable labyrinth seal for a fluid-flow machine
1542010023295409/16/10Bypass duct of a turbofan engine
1552010022390509/09/10Scoop of a running-gap control system of an aircraft gas turbine
1562010022434809/09/10Method for the manufacture of an ejector nozzle tube
1572010021228508/26/10Turboprop propulsion unit with pusher propeller
1582010021548108/26/10Running-gap control system of an aircraft gas turbine
1592010019258808/05/10Method 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
1602010017525607/15/10Method for the manufacture of the blade tips of rotor wheels made in blisk design
1612010017609707/15/10Arrangement for the repair of the blades of blisk drums by means of laser deposition welding
1622010015552606/24/10Aircraft with tail propeller-engine layout
1632010016110706/24/10Machine control for a numerically controlled machine tool
1642010014802706/17/10Sensor bracket for at least one sensor on a gas turbine
1652010014844906/17/10Segmented sealing lips for labyrinth sealing rings
1662010015069606/17/10Fan casing for a jet engine
1672010013924106/10/10Flow divider for a fan engine
1682010013927806/10/10The operation of a turboprop aircraft engine provided with pusher propellers
1692010014023006/10/10Method for the manufacture of a welded rotor for a gas-turbine engine
1702010014314006/10/10Fluid flow machine with sidewall boundary layer barrier
1712010012658905/27/10Device for the prevention of high oil tank pressures under negative g conditions
1722010012666205/27/10Method for the manufacture of hybrid components for aircraft gas turbines
1732010012965105/27/10Hybrid component for a gas-turbine engine
1742010012251805/20/10Oil system heating for aircraft gas turbines
1752010012448705/20/10Multi-vane variable stator unit of a fluid flow machine
1762010010918405/06/10Method for the manufacture of an engine shaft
1772010011170205/06/10Hub cone for an aircraft engine
1782010011317005/06/10Engine shaft for a gas-turbine engine
1792010011317105/06/10Engine shaft in the form of a fiber-composite plastic tube with metallic driving and driven protrusions
1802010009852704/22/10Fluid flow machine with peripheral energization near the suction side
1812010009853004/22/10Compressor for a gas turbine
1822010009853604/22/10Fluid flow machine with running gap retraction
1832010005111203/04/10Intake cone for a gas-turbine engine
1842010003463702/11/10Fluid flow machine
1852010002421402/04/10Method for the manufacture of metallic components
1862010002131001/28/10Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
1872010001495601/21/10Fluid flow machine featuring a groove on a running gap of a blade end
1882010001496001/21/10Gas-turbine engine with variable stator vanes
1892010000577601/14/10Fuel supply system for a gas-turbine engine
1902010000019801/07/10Gas turbine with at least one multi-stage compressor unit including several compressor modules
1912010000022601/07/10Turbofan engine with at least one apparatus for driving at least one generator
1922009031400412/24/09Turboprop engine with an apparatus for the generation of a cooling airflow
1932009031723212/24/09Blade shroud with aperture
1942013032687612/12/13Method for repairing compressor or turbine drums
1952010002131001/28/10Method for improving the flow conditions on the propeller or fan of an aircraft engine and accordingly designed hub cone
1962010001496001/21/10Gas-turbine engine with variable stator vanes
1972010000577601/14/10Fuel supply system for a gas-turbine engine
1982010000022601/07/10Turbofan 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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