公开(公告)号：US10797574B2

公开(公告)日：2020-10-06

申请号：US15990391

申请日：2018-05-25

Applicant: ROLLS-ROYCE plc

Inventor： Simon Turvey ,  Keir Wilkie

IPC: H02P9/00 ,  H02K21/02 ,  F02C7/268 ,  H02K1/27 ,  H02K7/116 ,  H02K7/18 ,  H02K11/04 ,  H02K16/02 ,  H02P27/08 ,  F02C7/32

Abstract: An electrical machine has a stator with windings, first and second rotors, and an electrical output regulator. The first rotor carries alternating polarity first field magnets, such that, on drive mechanism rotation, the windings interact with the magnetic flux produced by the first magnets to create an EMF. The second rotor carries alternating polarity second field magnets, and has first and second rotational positions to reduce and increase, respectively, the magnetic flux energy. The electrical output regulator regulates a current from the windings to produce a torque on the rotors, as the drive mechanism increases from zero rotational speed, the torque rises above a threshold level that moves the second rotor from the first to the second rotational position, and, as the drive mechanism further increases the rotational speed, the torque peaks and then drops below the threshold level to move the second rotor back to the first rotational position.

公开(公告)号：US10793279B2

公开(公告)日：2020-10-06

申请号：US16238841

申请日：2019-01-03

Applicant: ROLLS-ROYCE PLC

Inventor： Richard Sharpe ,  Glenn A Knight

IPC: B64D13/02 ,  F02C7/32 ,  B64D41/00 ,  F01D15/10 ,  F02C7/275 ,  F04D13/02 ,  F04D27/00 ,  F04D29/05

Abstract: An aircraft cabin blower system includes: a transmission configured to receive mechanical power from a first part of a gas turbine engine in the form of a first transmission input; and an electrical circuit including a first electrical machine, a second electrical machine, and a power management system, wherein an output of the transmission is configured to drive a cabin blower compressor when operating in a blower mode, the first electrical machine being configured to receive mechanical power from a second part of the gas turbine engine and act as a generator to provide electrical power to the power management system, and the second electrical machine being configured to act as a motor providing mechanical power to the transmission in the form of a second transmission input, the second electrical machine being driven by electrical power from the power management system.

公开(公告)号：US20200309374A1

公开(公告)日：2020-10-01

申请号：US16819354

申请日：2020-03-16

Applicant: ROLLS-ROYCE plc

Inventor： Paul A HUCKER ,  Iain MORGAN ,  Alan P GEARY

IPC: F23R3/28 ,  F23R3/00

Abstract: The present relates to combustor apparatus for a gas turbine engine comprising a bulkhead (34) an inner support ring (70) and an outer support ring (84) at end upstream end thereof. The bulkhead (34) has an inner surface (40), when in use is provided on an internal surface of a combustor (16) and exposed to combustion products and an outer surface (41) provided on an external surface of the combustor when in use; an inner mating feature to cooperate with the inner support ring (70); and an outer mating feature to cooperate with the outer support ring (84). In use, the inner and outer mating features prevent axial motion of the bulkhead relative to the inner (70) and outer (84) support rings.

公开(公告)号：US10788315B2

公开(公告)日：2020-09-29

申请号：US15696823

申请日：2017-09-06

Applicant: ROLLS-ROYCE plc

Inventor： Adriano Pulisciano ,  Mohammad Dabbah ,  Harold M. Uzzell ,  Edward Sparks

IPC: G01B11/14 ,  G06T7/00 ,  G01B21/16 ,  G06T7/13 ,  G06T17/00 ,  H04N13/20 ,  G06T7/593 ,  F01D21/00

Abstract: A computer implemented method of determining a dimension of a gap between an edge of an aerofoil and a surface of an engine casing, the method comprising: receiving data; generating a three dimensional model of the surface of the engine casing from the received data; identifying the edge of the aerofoil in the received data; determining a three dimensional position of a first location along the edge of the aerofoil in the received data using the identified edge; and determining a distance between the determined three dimensional position of the first location and the three dimensional model of the surface of the engine casing using an algorithm.

公开(公告)号：US20200290314A1

公开(公告)日：2020-09-17

申请号：US16816886

申请日：2020-03-12

Applicant: ROLLS-ROYCE plc

Inventor： Daniel CLARK

IPC: B32B15/01 ,  B23K20/02 ,  C23C14/24

Abstract: A method of forming a diffusion bonded joint comprises the steps of: providing a first component having a first faying surface; providing a second component having a second faying surface; applying a lamellar coating to at least one of the first faying surface and the second faying surface; and bringing the first and second faying surfaces into contact in a diffusion bonding operation to form the diffusion bonded joint.

公开(公告)号：US10767497B2

公开(公告)日：2020-09-08

申请号：US16124970

申请日：2018-09-07

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

Inventor： Daniel K. Vetters ,  Michael J. Whittle ,  Eric Koenig ,  Jeffrey A. Walston

IPC: F01D9/02 ,  F01D5/28 ,  F01D11/08 ,  F01D25/00 ,  F01D9/04

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.

公开(公告)号：US20200277898A1

公开(公告)日：2020-09-03

申请号：US16740708

申请日：2020-01-13

Applicant: ROLLS-ROYCE plc

Inventor： Michael R. SMITH

IPC: F02C7/232 ,  F16K35/02 ,  F02C9/46 ,  F01D21/14

Abstract: The disclosure relates to a valve for a fuel system having a body with at least one inlet and one outlet, the inlet fluidly connected to a pressurised fuel source in use. A shuttle is mounted within the body, the shuttle having a cavity of fixed volume and movable between a first position where fluid is permitted to flow through the inlet and is prevented from flowing through the outlet and a second position where fluid is prevented from flowing through the inlet and is permitted to flow through the outlet. A piston is configured to engage the fluid within the shuttle cavity to move the shuttle between the first and second position. A biasing mechanism biases the shuttle towards the first position and where the shuttle moves towards the second position when the fluid within the shuttle reaches a critical pressure.

公开(公告)号：US20200277865A1

公开(公告)日：2020-09-03

申请号：US16737979

申请日：2020-01-09

Applicant: ROLLS-ROYCE plc

Inventor： Daniel J. BLAIR ,  Timothy J. SUMMERS ,  Ewan F. THOMPSON

IPC: F01D5/28 ,  F01D5/14

Abstract: A method of forming a protective sheath for an aerofoil component includes: providing a first sheath portion and a second sheath portion, the first sheath portion and the second sheath portion each comprising an inner surface, an outer surface and an end surface between the inner and outer surfaces and having a sacrificial flange at its distal end; positioning the first sheath portion and second sheath portion so that the inner surface of the first sheath portion abuts against the inner surface of the second sheath portion with the end surfaces of the first and second sheath portions aligned to form a mating edge; and joining the first sheath portion to the second sheath portion by welding along the mating edge, wherein the sacrificial flanges are completely consumed and a curved outer profile is formed.

公开(公告)号：US10746102B2

公开(公告)日：2020-08-18

申请号：US15923183

申请日：2018-03-16

Applicant: ROLLS-ROYCE plc

Inventor： James M. Pointon ,  Stephen J. Bradbrook

IPC: F02C7/36 ,  F01D25/24 ,  F02K3/06 ,  F02C9/18

Abstract: A gas turbine engine (10) includes: a compressor system comprising a low pressure compressor (15) and a high pressure compressor (16) coupled to low pressure and high pressure shafts, respectively (23, 24); an inner core casing (34) provided radially inwardly of compressor blades (42), and an outer core casing provided outwardly of compressor blades, the inner core casing and outer core casing defining a core working gas flow path (B) therebetween; a fan (13) coupled to the low pressure shaft via a gearbox (14); wherein the outer core casing comprises a first outer core casing (48) and a second outer core casing (50) spaced radially outwardly from the first outer core casing, and wherein at an axial plane (E) of an inlet to the high pressure compressor, the second outer core casing has an inner radius at least 1.4 times the inner radius of the first outer core casing.

公开(公告)号：US20200256251A1

公开(公告)日：2020-08-13

申请号：US16782576

申请日：2020-02-05

Applicant: ROLLS-ROYCE plc

Inventor： Zahid M. Hussain

IPC: F02C7/14

Abstract: There is disclosed a gas turbine engine having a thermal management system, the gas turbine engine comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, and a fan located upstream of the engine core. The thermal management system comprises an oil tank; a heat exchanger; an oil coolant circuit that connects the oil tank and the heat exchanger; and an oil pump that pumps oil around the oil coolant circuit. The oil tank is located within the engine core, and the oil pump is electrically driven such that it is operable independently of the core shaft.