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公开(公告)号：US20200378274A1
公开(公告)日：2020-12-03
申请号：US16941754
申请日：2020-07-29
Applicant: ROLLS-ROYCE plc
Inventor： Christopher Richard HALLAM , Jonathan Paul TAYLOR
Abstract: A method of reassembling a gas turbine engine including steps to support a core engine on a core stand and support a fan case on a fan stand that includes a base frame coupled a fan case frame by a hinge. The fan case frame is arranged to (i) rotate about an axis of the hinge between abutting the base frame and being perpendicular to the base frame, and (ii) tilt about a yaw axis perpendicular to the hinge, which is located in a plane of the fan case frame. The method includes rotating and tilting the fan case frame to align the fan case and core engine, translating at least one of the core engine and the fan case into axial abutment, coupling the fan case and the core engine to reassemble the gas turbine engine, and decoupling the fan case from the fan stand.
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公开(公告)号：US10830444B2
公开(公告)日：2020-11-10
申请号：US16012054
申请日：2018-06-19
Applicant: ROLLS-ROYCE PLC
Inventor： Daniel J Bickley
IPC: F23R3/34 , F23R3/28 , F23K5/14 , F23K5/06 , F02C9/34 , F02C7/228 , F02C7/232 , F02C9/26 , F02C7/14 , F02C7/22
Abstract: A combustion staging system is provided for fuel injectors of a multi-stage combustor of a gas turbine engine. The system has a splitting unit which receives a metered total fuel flow and controllably splits the metered total fuel flow into out-going pilot and mains fuel flows to perform pilot-only and pilot-and-mains staging control of the combustor. The system further has pilot and mains fuel manifolds which respectively receive the pilot and mains fuel flows, the mains fuel manifold being split into a primary line and a servo line such that each line receives a respective portion of the mains fuel flow. The system further has a plurality of mains flow control valves which distribute the mains fuel flow from the mains fuel manifold to mains discharge orifices of respective injectors of the combustor, both the primary line and the servo line extending to the mains flow control valves before reuniting. The system further has a servo pump operable to change the pressure in the servo line relative to the pressure in the primary line. Each mains flow control valve has a chamber containing a movable piston, the chamber to a primary side of the piston being fed by the primary line, and the chamber to a servo side of the piston being fed by the servo line. The piston is biased towards a closed pilot-only position which prevents flow out of the primary side of the chamber to the mains discharge orifice of the respective injector. The piston is movable under an increase in pressure in the servo line relative to the primary line to an open pilot-and-mains position which allows flow out of the primary side of the chamber to the mains discharge orifice of the respective injector.
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公开(公告)号：US20200347748A1
公开(公告)日：2020-11-05
申请号：US16451537
申请日：2019-06-25
Applicant: ROLLS-ROYCE plc
Inventor： Chathura K. KANNANGARA , Jillian C. GASKELL , Stewart T. THORNTON , Timothy PHILP
Abstract: A gas turbine engine for an aircraft and an engine core including: a compressor system, a first lower pressure compressor, a second, higher pressure compressor; an outer core casing surrounding the compressor system. The outer core casing includes a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection, the first flange connection having a first flange radius, wherein the first flange connection is the connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor, and a front mount arranged to be connected to a pylon. A front mount position ratio of: axial distance between the first flange connection and the front mount first flange radius is equal to or less than 1.18.
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公开(公告)号：US20200347731A1
公开(公告)日：2020-11-05
申请号：US16778795
申请日：2020-01-31
Applicant: ROLLS-ROYCE plc
Inventor： Chathura K. KANNANGARA , Jillian C. GASKELL , Stewart T. THORNTON , Timothy PHILP
Abstract: A gas turbine engine includes an engine core including: a compressor system including first, lower pressure compressor, and second, higher pressure compressor; and an outer core casing. The engine includes a front mount arranged for connection to a pylon; and a fan located upstream of the engine core. The outer core casing includes a first flange connection that: is arranged to allow separation of the outer core casing at an axial position thereof, and is the first flange connection downstream of an axial position defined by the axial midpoint between the mid-span axial location on trailing edge of the most downstream aerofoil of first compressor and mid-span axial location on leading edge of the most upstream aerofoil of the second compressor. A front mount position ratio of: axial distance between the first flange connection and the front mount first flange radius is equal to or less than 1.18.
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公开(公告)号：US10822960B2
公开(公告)日：2020-11-03
申请号：US15686737
申请日：2017-08-25
Applicant: ROLLS-ROYCE plc
Inventor： Martin Mottram , Paul A Sellers
Abstract: A blade has a root portion and elongate portion extending from the root portion to a tip. The elongate portion has an aerofoil-shaped cross section having leading and trailing edges and suction and pressure sides. The tip may include a gutter defining squealer. The squealer has a wall extending from the trailing edge and along a substantial portion of the tip perimeter. A main trailing edge cooling channel extends within the elongate portion in a direction from root to tip adjacent the trailing edge and exiting into the gutter. A gallery channel is arranged just behind the gutter and extends from an open end intersecting the main trailing edge cooling channel to a closed end located just behind a trailing edge apogee. Cooling channels extend from the gallery channel and through the squealer wall. The gallery channel diameter is greater at the open end than the closed end.
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Patent Agency Ranking
公开(公告)号：US20200340370A1
公开(公告)日：2020-10-29
申请号：US16391827
申请日：2019-04-23
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Anthony G. Razzell , Roderick M. Townes , David J. Shepherd , Duncan Forbes
Abstract: A turbine assembly adapted for use in a gas turbine engine with a turbine vane comprising ceramic matrix composite materials. The turbine vane is configured to redirect air moving through a primary gas path of the gas turbine engine. The turbine assembly includes a vane-stage support for holding the turbine vane in place relative to a turbine case.
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公开(公告)号：US20200338844A1
公开(公告)日：2020-10-29
申请号：US16859362
申请日：2020-04-27
Applicant: ROLLS-ROYCE PLC
Inventor： Jack J LINDLEY-START
IPC: B29C73/02
Abstract: A method of repairing a composite material, the composite material comprising fibres embedded in a matrix, comprises the steps of: identifying a damaged portion of a composite material; applying thermal energy directly to a section of the composite material including the damaged portion, so as to remove the matrix material whilst retaining the fibres; filling the section of the composite material with replacement matrix material.
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公开(公告)号：US10808626B1
公开(公告)日：2020-10-20
申请号：US16807956
申请日：2020-03-03
Applicant: ROLLS-ROYCE plc
Inventor： Mark Spruce
Abstract: An engine for an aircraft includes an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from a core shaft and to output drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and includes a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. A ratio of radial bending stiffness of the planet carrier to torsional stiffness of the planet carrier is within a specified range.
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公开(公告)号：US10808553B2
公开(公告)日：2020-10-20
申请号：US16189690
申请日：2018-11-13
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Anthony Razzell
Abstract: Turbine vane assemblies incorporating both metallic and ceramic matrix composite materials are provided in the present disclosure. The turbine vane assemblies further include interface components that allow for differing rates of thermal expansion in the ceramic matrix composite components and the metallic components.
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公开(公告)号：US20200318493A1
公开(公告)日：2020-10-08
申请号：US16828102
申请日：2020-03-24
Applicant: ROLLS-ROYCE plc
Inventor： Michael BOOTH , Andrew SMITH , Ajay PATEL
Abstract: An oil pipe assembly for a gas turbine engine. The oil pipe assembly includes a first pipe that defines a first fluid passage between an oil supply and a bearing chamber, and a second pipe that houses the first pipe and defines a second fluid passage between the first pipe and the second pipe that is supplied with cooling air. The oil pipe assembly also includes a restrictor that extends from the second pipe and restricts the passage of fluid from the second fluid passage before it flows into a breather. Pressure and temperature sensors) are located adjacent the restrictor to detect and measure changes in air pressure and air temperature adjacent the restrictor from which a controller identifies whether a leak has occurred in the first pipe or the second pipe. A method for detecting a leak in the oil pipe assembly, and a gas turbine are also described.
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