公开(公告)号：US11732603B2

公开(公告)日：2023-08-22

申请号：US17969826

申请日：2022-10-20

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J Bousfield ,  Duncan A MacDougall

IPC: F01D25/02 ,  F01D5/14 ,  F04D29/32

CPC classification number: F01D25/02 ,  F01D5/141 ,  F01D5/147 ,  F04D29/324 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/307

Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft, and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein a ratio of a leading edge radius of each of the plurality of first rotor blades at 0% span height to a minimum leading edge radius is comprised between 1 and 1.50.

公开(公告)号：US20230258137A1

公开(公告)日：2023-08-17

申请号：US18162970

申请日：2023-02-01

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN

IPC: F02C9/40 ,  F02C7/22 ,  F02C9/28

CPC classification number: F02C9/40 ,  F02C7/22 ,  F02C9/28 ,  F05D2270/306 ,  F05D2270/3032 ,  F05D2220/32

Abstract: An engine system comprises a first fuel store, a second fuel store, an engine arranged to produce mechanical power by combustion or oxidation of a fuel in an engine, a fuel distribution system arranged to deliver fuel from the first and second fuel stores to the engine, the first fuel delivered at a first mass flow rate, the second fuel delivered at a second mass flow rate, the first and second mass flow rates contributing to a total mass flow rate of fuel to the engine; and a control system arranged to control the relative fractions of the total mass flow rate of fuel to the engine represented by the first mass flow rate and the second mass flow rate, based on an engine temperature.

公开(公告)号：US20230250757A1

公开(公告)日：2023-08-10

申请号：US18149895

申请日：2023-01-04

Applicant: ROLLS-ROYCE PLC

Inventor： Ashley POWELL ,  Andrew WILKINSON ,  Eduardo ROMERO

IPC: F02C7/10 ,  F02C7/22

CPC classification number: F02C7/10 ,  F02C7/22 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213

Abstract: A reheat assembly for a gas turbine engine includes: a jetpipe casing including: a reheat core section configured to convey a core flow of air from a reheat core inlet to a reheat core outlet; and a reheat bypass section configured to convey a bypass flow of air from a reheat bypass inlet to a reheat bypass outlet radially outward of the reheat core section, wherein the reheat core and reheat bypass sections are radially separated at the reheat core and reheat bypass inlets by a support duct within the jetpipe casing; a reheat arrangement including a radially extending flameholder and a plurality of fuel injection ports including a plurality of core fuel injection ports, wherein: the flameholder is configured to promote a formation of a core flow wake-stabilised region within the core flow of air downstream of the flameholder; and each of the plurality of core fuel injection ports are: circumferentially aligned with the flameholder upstream of the core flow wake-stabilised region, configured to discharge a respective flow of fuel into the reheat core section for mixing with the core flow of air, and offset with respect to one another along a radial direction of the jetpipe casing.

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.