公开(公告)号：US11306680B2

公开(公告)日：2022-04-19

申请号：US17072492

申请日：2020-10-16

Applicant: ROLLS-ROYCE plc

Inventor： Jack F. Colebrooke

IPC: F02K1/08 ,  F02K1/12

Abstract: There is disclosed an exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a frame extending along a longitudinal axis, and a convergent petal pivotably attached at a convergent pivot point to the frame and extending axially downstream and radially inward from the frame. The exhaust nozzle comprises a follower roller fixed to the convergent petal on a radially outer side of the convergent petal, and a cam defining a working surface configured to engage the follower roller to react a force from the convergent petal. The cam is movable along a travel in an axial direction to actuate radial movement of the follower roller to pivot the convergent petal. The cam defines a convex working surface such that a contact angle between the follower roller and the cam varies along the travel to thereby vary an axial component of the force reacted by the cam.

公开(公告)号：US20220112982A1

公开(公告)日：2022-04-14

申请号：US17450519

申请日：2021-10-11

Applicant: Rolls-Royce plc

Inventor： Eric W. DEAN

IPC: F17C1/02

Abstract: An organic composite gas storage tank 100 comprises a hollow central portion 106 which is substantially cylindrical and formed integrally with first and second end portions 102, 104, and which defines a longitudinal tank axis 301. The first end portion comprises a hollow truncated conical region which meets the hollow central portion at a first end thereof, the outer and inner radii of the hollow truncated conical region decreasing in a direction along the longitudinal tank axis away from the hollow central portion. An organic fibre winding 107 extends at least between axial positions which coincide with the hollow truncated conical region of the first end portion and the hollow central portion respectively. The first end portion has a higher axial strength than that achievable for hemispherical end portion of a tank of the prior art.

公开(公告)号：US20220112843A1

公开(公告)日：2022-04-14

申请号：US17484897

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C. WONG ,  Thomas S BINNINGTON ,  David A. JONES ,  Daniel BLACKER

IPC: F02C7/18 ,  F02C7/04

Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D), and the heat exchanger module comprises a plurality of heat exchanger elements.
The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, with the heat exchanger module having an axial length along a central axis between an upstream-most face of the heat exchanger elements and a downstream-most face of the heat exchanger elements. The axial length is in the range of 0.1*D to 5.0*D.

公开(公告)号：US20220112842A1

公开(公告)日：2022-04-14

申请号：US17484622

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C. WONG ,  Thomas S. BINNINGTON ,  David A. JONES ,  Daniel BLACKER

IPC: F02C7/18 ,  B64D27/10 ,  B64D33/08 ,  B64D33/02 ,  B64D33/04

Abstract: An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid cooling flow prior to an entry of the entire fluid cooling flow into the fan module.

公开(公告)号：US20220112841A1

公开(公告)日：2022-04-14

申请号：US17484873

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C. WONG ,  Thomas S. BINNINGTON ,  David A. JONES ,  Daniel BLACKER

IPC: F02C7/14

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter PEX (W/N) defined as PEX=H/T is 0.4 to 6.0.

公开(公告)号：US11300293B2

公开(公告)日：2022-04-12

申请号：US16903456

申请日：2020-06-17

Applicant: ROLLS-ROYCE plc

Inventor： Luca Tentorio ,  Juan Carlos Roman Casado ,  Giacomo Di Chiaro ,  Jonathan Knapton ,  Filippo Zambon ,  Radu Irimia

IPC: F23R3/28 ,  F23R3/14 ,  F23R3/34

Abstract: A fuel injector comprising a first air swirler passage and a second air swirler passage extending axially through the fuel injector and arranged to direct air through the fuel injector, a splitter arranged between the first air swirler passage and the second air swirler passage and comprising a first splitter surface having a first divergent portion which is divergent in the downstream direction, a second splitter surface located radially inward of the first splitter surface and having a second divergent portion which is divergent in the downstream direction, a third splitter surface located radially inward of the first and second splitter surface, and a first connecting surface extending between the second and third splitter surfaces, wherein a first cavity is formed between the first and second splitter surfaces, and the second divergent portion comprises at least one opening in fluid communication with the first cavity.

公开(公告)号：US11292605B2

公开(公告)日：2022-04-05

申请号：US16396923

申请日：2019-04-29

Applicant: ROLLS-ROYCE plc

Inventor： Joseph B. Cooper

IPC: B64D27/26 ,  F01D25/28 ,  F02C7/20 ,  F02C7/268

Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. A temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link are each adapted to resist tension and compression, to maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.

公开(公告)号：US20220099035A1

公开(公告)日：2022-03-31

申请号：US17466086

申请日：2021-09-03

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W BEMMENT ,  Pascal DUNNING

IPC: F02C9/28 ,  F01D11/14 ,  F01D13/00 ,  F01D25/24

Abstract: A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A turbine to fan tip temperature change ratio of a low pressure turbine temperature change to a fan tip temperature rise is in the range from 1.46 to 2.0.

公开(公告)号：US11286798B2

公开(公告)日：2022-03-29

申请号：US16545791

申请日：2019-08-20

Applicant: Rolls-Royce plc ,  Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc.

Inventor： Michael J. Whittle ,  Daniel K. Vetters ,  Ted J. Freeman ,  Eric Koenig ,  Jeff Crutchfield ,  Jeffrey A. Walston ,  David J. Thomas

IPC: F01D9/04 ,  F01D25/00

Abstract: An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly.

公开(公告)号：US11286792B2

公开(公告)日：2022-03-29

申请号：US16526274

申请日：2019-07-30

Applicant: Rolls-Royce plc

Inventor： Anthony Razzell ,  Michael J. Whittle ,  Ian M. Edmonds

IPC: F01D5/18 ,  C04B35/80 ,  F01D5/28

Abstract: An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a hollow tube that extends through the body to define a cooling passage that extends from the cooling cavity through the airfoil to provide fluid communication between the cooling cavity and a gas path environment surrounding the airfoil.