公开(公告)号：US11719386B2

公开(公告)日：2023-08-08

申请号：US17450519

申请日：2021-10-11

Applicant: Rolls-Royce plc

Inventor： Eric W Dean

IPC: F17C1/02

CPC classification number: F17C1/02 ,  F17C2201/0109 ,  F17C2203/012 ,  F17C2203/0604 ,  F17C2203/0621 ,  F17C2203/0665 ,  F17C2203/0673 ,  F17C2221/012 ,  F17C2260/036 ,  F17C2270/01

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：US20230242260A1

公开(公告)日：2023-08-03

申请号：US18155351

申请日：2023-01-17

Applicant: ROLLS-ROYCE plc ,  Rolls-Royce Corporation

Inventor： Christopher A. MURRAY ,  Nicholas HOWARTH ,  Daniel SWAIN ,  Ian J. BOUSFIELD

IPC: B64D13/06 ,  F04D25/04 ,  F02C7/32

CPC classification number: B64D13/06 ,  F04D25/04 ,  F02C7/32 ,  B64D2013/0603

Abstract: There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.

公开(公告)号：US20230228232A1

公开(公告)日：2023-07-20

申请号：US18123091

申请日：2023-03-17

Applicant: ROLLS-ROYCE plc

Inventor： Craig W BEMMENT ,  Pascal DUNNING

IPC: F02K3/06

CPC classification number: F02K3/06 ,  F05D2220/36 ,  F05D2200/14 ,  F05D2260/4031 ,  F05D2240/307 ,  F05D2220/323

Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.

公开(公告)号：US20230228218A1

公开(公告)日：2023-07-20

申请号：US18125484

申请日：2023-03-23

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F16H1/28 ,  F16H57/08

CPC classification number: F02C7/36 ,  F16H1/28 ,  F16H57/082 ,  F05D2220/323

Abstract: A gas turbine engine configured with an engine core. A fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a gearbox arranged to receive an input from the core shaft and to output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox comprising a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted, the planet carrier having an effective linear torsional stiffness and the gearbox having a gear mesh stiffness between the planet gears and the ring gear. Additionally, the product of the effective linear torsional stiffness of the planet carrier and the gear mesh stiffness between the planet gears and the ring gear is greater than or equal to 5.0×1018 N2m−2.

公开(公告)号：US11692484B2

公开(公告)日：2023-07-04

申请号：US17484771

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C Wong ,  Thomas S Binnington ,  David A Jones ,  Daniel Blacker

IPC: F02C7/08 ,  F02K3/00 ,  F02C7/04 ,  F02K3/06

CPC classification number: F02C7/08 ,  F02C7/04 ,  F02K3/00 ,  F02K3/06 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/2214

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 fan blades defining a corresponding fan area (AFAN). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and includes radially-extending vanes arranged in a circumferential array with at least one vane including a heat transfer element for heat transfer from a first fluid contained within each element to an airflow passing over a surface of each heat transfer element before entering the fan assembly inlet. Each heat transfer element extends axially along the corresponding vane, with a swept heat transfer element area (AHTE) being the wetted surface area of all heat transfer elements in contact with the airflow. A Fan to Element Area parameter FEA of AHTE/AFAN lies in the range of 47 to 132.

公开(公告)号：US11692482B2

公开(公告)日：2023-07-04

申请号：US17812563

申请日：2022-07-14

Applicant: ROLLS-ROYCE plc

Inventor： Robert W Hicks

IPC: F02C7/06 ,  F02C7/36 ,  F01D21/04

CPC classification number: F02C7/06 ,  F01D21/045 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/54 ,  F05D2260/37 ,  F05D2260/98

Abstract: A roller bearing arrangement for a gas turbine engine. The roller bearing arrangement includes a fan shaft, and a stub shaft connected to the fan shaft. The roller bearing arrangement further includes a plurality of roller bearing elements positioned between a first axial bearing surface created on a radially outer surface of the stub shaft and a second axial bearing surface of a static structure, the roller bearing arrangement further including a first snubber positioned between the radially outer surface of the fan shaft and a radially inner surface of the stub shaft, the first snubber being spaced apart from the radially inner surface of the stub shaft or the radially outer surface of the fan shaft so as to limit a radial movement range of the stub shaft.

公开(公告)号：US20230203954A1

公开(公告)日：2023-06-29

申请号：US18073143

申请日：2022-12-01

Applicant: ROLLS-ROYCE plc

Inventor： Soumyik BHAUMIK

IPC: F01D5/18 ,  F01D5/22

CPC classification number: F01D5/181 ,  F01D5/225 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/20

Abstract: A turbine blade including an aerofoil and a shroud. The shroud includes a first abutment surface configured to face a second abutment surface of a first circumferentially adjacent turbine blade. The shroud further includes a second abutment surface configured to face a first abutment surface of a second circumferentially adjacent turbine blade. The shroud further includes an inner platform surface extending at least circumferentially between the first abutment surface and the second abutment surface. The shroud further includes a first recessed surface extending at least radially and circumferentially from the first abutment surface to the inner platform surface. The first recessed surface defines a first recessed region configured to receive a flow of a cooling fluid from the first circumferentially adjacent turbine blade.

公开(公告)号：US20230193838A1

公开(公告)日：2023-06-22

申请号：US18084083

申请日：2022-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Craig W. BEMMENT ,  Alastair G. HOBDAY ,  Benjamin J. KEELER ,  Christopher P. MADDEN

IPC: F02C9/40 ,  F01D21/00 ,  F02C9/28

CPC classification number: F02C9/40 ,  F01D21/003 ,  F02C9/28 ,  F05D2220/323 ,  F05D2260/83 ,  F05D2270/07 ,  F05D2270/71

Abstract: A method of operating an aircraft that includes a propulsion system. The propulsion system includes a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine. The method includes: determining at least one fuel characteristic of the fuel arranged to be provided to the gas turbine engine; and controlling the propulsion system based on the at least one fuel characteristic.

公开(公告)号：US20230193773A1

公开(公告)日：2023-06-22

申请号：US17560233

申请日：2021-12-22

Applicant: Rolls-Royce plc

Inventor： Daniel Clark ,  Michael J. Whittle ,  Carl Boettcher ,  David C. Wright

IPC: F01D9/06 ,  F01D5/28

CPC classification number: F01D9/065 ,  F01D5/282 ,  F01D5/284 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly. A spar system couples the inner vane support with the outer vane support.

公开(公告)号：US20230192979A1

公开(公告)日：2023-06-22

申请号：US18058912

申请日：2022-11-28

Applicant: ROLLS-ROYCE plc

Inventor： Eduardo SANTANA DE VEGA ,  Giuliano ALLEGRI ,  Stephen HALLETT ,  Ian HAMERTON ,  Bing ZHANG

IPC: C08J5/24 ,  B29C70/82

CPC classification number: C08J5/246 ,  B29C70/82 ,  C08J2363/00 ,  C08J2375/00 ,  C08J2379/08 ,  C08J2367/00 ,  C08J2479/06

Abstract: A Z-pin for increasing a delamination resistance of continuous fibre-reinforced polymer composites, formed of a composite material including a polymer matrix, and a plurality of fibres embedded in the polymer matrix and aligned along the length direction of Z-pin, the fibres having an elongation at break of at least 2% and a tensile strength of at least 5 GPa, the polymer matrix having an elongation at break equal to or greater than the elongation at break of the fibres, and a tensile strength of at least 120 MPa.