Patents Assigned to Rolls-Royce North American Technologies, Inc.
  • GAS TURBINE ENGINE FLOW DUCT HAVING INTEGRATED HEAT EXCHANGER
    Publication number: 20150047315
    Abstract: A gas turbine engine flow duct comprising a flow duct disposed along an engine centerline of the gas turbine engine and defining a stream flow passage, and first and second rows of heat exchangers disposed along the engine centerline of the gas turbine engine and integrated in the flow duct in fluid communication with the stream flow passage of the flow duct.
    Type: Application
    Filed: December 20, 2013
    Publication date: February 19, 2015
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventor: Douglas J. Snyder
  • Turbine vane for gas turbine engine
    Patent number: 8956105
    Abstract: A turbine vane for a gas turbine engine may include a composite airfoil structure. The composite airfoil structure may have an opening. The turbine vane may include a spar. The spar may have a body, which may be disposed within the opening. A standoff structure may be disposed within the opening. In some non-limiting embodiments, a cooling air gap may be defined between the body and an internal surface of the composite airfoil structure.
    Type: Grant
    Filed: December 21, 2009
    Date of Patent: February 17, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Richard C. Uskert, Ted Joseph Freeman, David J. Thomas
  • Integrated compressor vane casing
    Patent number: 8950069
    Abstract: A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system.
    Type: Grant
    Filed: December 21, 2007
    Date of Patent: February 10, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Robert A. Ress, Jr.
  • System and method for measuring radiant energy in gas turbine engines, components and rigs
    Patent number: 8946635
    Abstract: One embodiment of the present invention is a unique system for measuring radiant energy in gas turbine engines, gas turbine engine components and gas turbine engine/component rigs. Another embodiment is a unique method for measuring radiant energy in gas turbine engines, gas turbine engine components and gas turbine engine/component rigs. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for measuring radiant energy. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: December 29, 2010
    Date of Patent: February 3, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: James Carl Loebig, Jefre H. Cockerham, Emil R. Dejulio, James E. McDonald
  • COMPARTMENTALIZATION OF COOLING AIR FLOW IN A STRUCTURE COMPRISING A CMC COMPONENT
    Publication number: 20150016971
    Abstract: A structure in a gas turbine engine comprises a spar and a CMC component adjoining the spar and separated from the spar by a cavity supplied by cooling air. At least one rope seal is installed in the cavity within a groove made in the spar to thus compartmentalize the cavity and control the flow of cooling air.
    Type: Application
    Filed: December 27, 2013
    Publication date: January 15, 2015
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventors: Ted J. Freeman, David J. Thomas
  • VEHICLE RECUPERATOR
    Publication number: 20150014994
    Abstract: An engine may have a recuperator that may be powered by an electrical generator driven by the engine. The recuperator may be disposed within or incorporated into a compressor discharge of the engine, such as in the form of a vane or tube. The engine may be configured to operate in a variety of modes at least some of which may use thermal energy from the recuperator to heat a fluid flow stream of the engine. An energy storage device may be used with an electrical generator to provide power to a load.
    Type: Application
    Filed: December 27, 2013
    Publication date: January 15, 2015
    Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Carl D. Nordstrom, Rigoberto J. Rodriguez
  • GAS TURBINE ENGINE COMBUSTOR LINER
    Publication number: 20150013340
    Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.
    Type: Application
    Filed: December 27, 2013
    Publication date: January 15, 2015
    Applicants: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney, James C. Loebig, Todd Taylor
  • GAS TURBINE ENGINE HAVING CONFIGURABLE BYPASS PASSAGE
    Publication number: 20150003959
    Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.
    Type: Application
    Filed: December 26, 2013
    Publication date: January 1, 2015
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventor: Robert T. DUGE
  • PROPULSION, ELECTRICAL, AND THERMAL MANAGEMENT DEVICE FOR A SMALL UNMANNED AERIAL VEHICLE
    Publication number: 20150001339
    Abstract: An aircraft is provided with a gas turbine engine having a plurality of shafts. A first shaft provides power to an electrical generator and a propeller, while a second shaft provides power to a refrigeration system. The refrigeration system may be integrated to the propeller, like a ducted fan, or on the outer skin of the aircraft.
    Type: Application
    Filed: December 18, 2013
    Publication date: January 1, 2015
    Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Steven Gagne, William L. Siegel, Jerry L. Wouters, Thomas Dannenhoffer
  • METHODS AND SYSTEMS FOR OPERATING A GAS TURBINE ENGINE
    Publication number: 20150001856
    Abstract: A method of operating a gas turbine engine may include operating a starter motor to rotate a spool of the gas turbine engine; determining a torque of the starter motor during rotation of the spool; and controlling the rotation of the spool based on the torque.
    Type: Application
    Filed: December 18, 2013
    Publication date: January 1, 2015
    Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Peter H. Argo, Thomas J. Ronan
  • ADAPTIVE TRANS-CRITICAL CO2 COOLING SYSTEMS FOR AEROSPACE APPLICATIONS
    Publication number: 20140366563
    Abstract: A cooling system includes a heat exchanger through which a refrigerant flows, and which rejects heat to a fluid, an evaporator, a first circuit having an expansion device, a second circuit having an expansion machine coupled to a compressor, and a set of valves arranged to direct the refrigerant through the first circuit, the second circuit, or both the first and second circuits based on ambient conditions.
    Type: Application
    Filed: December 17, 2013
    Publication date: December 18, 2014
    Applicants: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Igor Vaisman, Patrick C. Sweeney, Douglas J. Snyder
  • Gas turbine engine and heat exchange system
    Patent number: 8910465
    Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine heat exchange system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and heat exchange systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: December 27, 2010
    Date of Patent: December 16, 2014
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Douglas J. Snyder
  • GAS TURBINE ENGINE AND ELECTRICAL SYSTEM
    Publication number: 20140360205
    Abstract: One embodiment of the present disclosure is a unique gas turbine engine. Another embodiment of the present disclosure is a unique machine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and electrical systems.
    Type: Application
    Filed: December 19, 2013
    Publication date: December 11, 2014
    Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Mat French, John T. Alt, Mark J. Blackwelder
  • ULTRA HIGH BYPASS RATIO TURBOFAN ENGINE
    Publication number: 20140363276
    Abstract: An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24.
    Type: Application
    Filed: December 10, 2013
    Publication date: December 11, 2014
    Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Daniel K. Vetters, Michael Karam, Roy D. Fulayter
  • INTERCOOLED GAS TURBINE WITH CLOSED COMBINED POWER CYCLE
    Publication number: 20140352317
    Abstract: A turbine engine includes a fan that provides an air flow to the turbine engine as compressor intake air and as compressor bypass air, a first stage compressor positioned to receive the compressor intake air and output a first stage compressed air, and a boiler positioned to cool the first stage compressed air using a fluid. A second stage compressor is positioned to receive the cooled first stage compressed air. A pump is configured to pump the fluid as a liquid into the boiler, extract energy from the first stage compressed air, and cause the cooling of the first stage compressed air.
    Type: Application
    Filed: December 19, 2013
    Publication date: December 4, 2014
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventors: James C. Loebig, Robert Manning
  • TURBINE SEGMENTED COVER PLATE RETENTION METHOD
    Publication number: 20140356177
    Abstract: An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assembly also avoids cover plate loading slots in the disc which can cause high stress features. The improved system also includes a method to axially retain segmented cover plates in relation to a turbine disc using a segmented retainer ring.
    Type: Application
    Filed: December 11, 2013
    Publication date: December 4, 2014
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventor: Brandon R. Snyder
  • GAS TURBINE ENGINE HEAT EXCHANGER SYSTEM
    Publication number: 20140356125
    Abstract: An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid.
    Type: Application
    Filed: December 12, 2013
    Publication date: December 4, 2014
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventors: Eric S. Donovan, Daniel J. Vonderwell, Craig Heathco
  • Three spool gas turbine engine having a clutch and compressor bypass
    Patent number: 8887485
    Abstract: An adaptive cycle gas turbine engine is disclosed having a number of features. A fan arrangement is provided having counter-rotating fan stages, one fan stage is operable to be clutched and decoupled from the other stage. A high pressure compressor bypass is also provided. A clutch is provided to at least partially drive an intermediate pressure compressor with a high pressure turbine when the high pressure compressor is bypassed. A partial bypass of the high pressure turbine may be provided.
    Type: Grant
    Filed: October 20, 2009
    Date of Patent: November 18, 2014
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Robert A. Ress, Jr.
  • RETENTION PIN AND METHOD OF FORMING
    Publication number: 20140327213
    Abstract: A retention pin assembly may include a stud having a head, a shaft, and a deformable end. The shaft may include a stepped surface having a greater diameter than the deformable end. The assembly may include a support member having an opening for receiving the deformable end. The support member may include a pocket. The stepped surface of the shaft may position the stud in relation to the support member. The deformable end of the stud may be operable to be melted to form a mechanical retainer within the pocket without forming a metallurgical joint between the stud and the pocket.
    Type: Application
    Filed: March 11, 2014
    Publication date: November 6, 2014
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventor: James C. Muskat
  • Gas turbine engine device
    Patent number: 8875520
    Abstract: A gas turbine engine adapter is provided. In one form the adapter is segmented and may be attached to a gas turbine engine support ring. The adapter can provide a channel that may receive part of a gas turbine engine component such as, but not limited to, a plug nozzle. The adapter can include a load bearing support to counteract axial forces experienced by the plug nozzle during operation of the gas turbine engine. A compressible seal can be provided between the plug nozzle and the adapter. A leaf seal can also be provided to seal between segments of the adapter. The plug nozzle can be discouraged from rotating relative to the adapter.
    Type: Grant
    Filed: December 9, 2009
    Date of Patent: November 4, 2014
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Gregory W. P. Zeaton, David L. Sutterfield, Sean F. Sullivan