公开(公告)号：US11053806B2

公开(公告)日：2021-07-06

申请号：US16661572

申请日：2019-10-23

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

Inventor： Aaron D. Sippel ,  Daniel K. Vetters ,  Jun Shi ,  David J. Thomas ,  Andrew J. Eifert ,  Peter Broadhead

IPC: F01D9/04 ,  F01D9/02 ,  F01D25/24

Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.

公开(公告)号：US11047301B2

公开(公告)日：2021-06-29

申请号：US16411224

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Pascal Dunning ,  Michael J Whittle ,  Roderick M Townes

IPC: F02C3/107 ,  F02C3/073 ,  F02C7/36 ,  F01D5/28

Abstract: A highly efficient gas turbine engine includes the fan of the gas turbine engine driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US11047258B2

公开(公告)日：2021-06-29

申请号：US16164312

申请日：2018-10-18

Applicant: Rolls-Royce plc

Inventor： Jade L. Whittle ,  Michael J. Whittle

IPC: F01D9/04 ,  F01D25/12 ,  F01D11/16 ,  F01D17/08

Abstract: A turbine assembly according to the present disclosure includes ceramic matrix composite vanes mounted to a metallic case. The turbine assembly includes a turbine case cooling system with a vane case cooling unit configured to manage the temperature and diameter of the metallic case at the location where the ceramic matrix composite vanes are mounted so as to control circumferential movement of the vanes relative to one another during heating and cooling of the turbine assembly when used in a gas turbine engine.

公开(公告)号：US20210190010A1

公开(公告)日：2021-06-24

申请号：US17193317

申请日：2021-03-05

Applicant: ROLLS-ROYCE PLC

Inventor： Alastair D MOORE ,  Robert J TELLING

IPC: F02K3/06 ,  F02C7/24

Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine that has high efficiency provides low noise, in particular from the fan and the turbine that drives the fan. Values are defined for a noise parameter NP that results in a gas turbine engine having reduced combined fan and turbine noise.

公开(公告)号：US20210189963A1

公开(公告)日：2021-06-24

申请号：US16824270

申请日：2020-03-19

Applicant: ROLLS-ROYCE plc

Inventor： Chathura K KANNANGARA ,  Punitha KAMESH ,  Jillian C GASKELL

IPC: F02C7/06 ,  F02C7/36 ,  F02K3/06

Abstract: An aircraft gas turbine engine has an engine core having a turbine, compressor, and core shaft connecting the turbine to the compressor, the turbine being the lowest pressure turbine and having a turbine length being the distance between the roots of the most upstream turbine blade at its leading edge and of the most downstream turbine blade trailing edge, and the compressor being the lowest pressure compressor of the engine; a fan located upstream of the engine; and a gearbox receiving an input from the core shaft and outputting drive to the fan. The engine core has three bearings to support the core shaft, the three bearings having a forward bearing and two rearward bearings, with a minor span defined as the distance between the two rearward bearings, and wherein further a minor span to turbine length ratio of: minor   span tu   rbine   length is equal to or less than 1.05.

公开(公告)号：US20210189908A1

公开(公告)日：2021-06-24

申请号：US16796055

申请日：2020-02-20

Applicant: ROLLS-ROYCE plc

Inventor： Jillian C GASKELL ,  Chathura K KANNANGARA ,  Punitha KAMESH

IPC: F01D25/16 ,  F16C19/52 ,  F16C19/04

Abstract: A gas turbine engine for an aircraft has an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor, the turbine being the lowest pressure turbine of the engine and the compressor being the lowest pressure compressor of the engine; a fan located upstream of the engine core; and a gearbox that receives an input from the core shaft and outputs drive to the fan. The engine core further has three bearings arranged to support the core shaft, and two rearward bearings, and wherein the forward most rearward bearing has a bearing stiffness defined by the radial displacement caused by the application of a radial force at the axial centerpoint of the bearing, and wherein a stiffness ratio of the bearing stiffness at the forward most rearward bearing to the minor span is in the range from 0.08 to 0.5 kN/mm2.

公开(公告)号：US11041626B2

公开(公告)日：2021-06-22

申请号：US15457456

申请日：2017-03-13

Applicant: ROLLS-ROYCE plc

Inventor： Hua Wei Huang ,  Jochen Rupp ,  Michael Whiteman

IPC: F23R3/00 ,  F23R3/34 ,  F02C9/28 ,  F02C9/32 ,  F23N1/00 ,  F02C9/26 ,  F23R3/50

Abstract: A combustion chamber system has pilot and main fuel manifolds, and pilot and main fuel nozzles. Each pilot nozzle is connected to the pilot manifold. Each main nozzle is connected to the main manifold. A greater total amount of fuel is supplied to the pilot nozzles than to the main nozzles. A greater amount of fuel is supplied to pilot nozzles at, or in, a first region of the combustion chamber than to pilot fuel nozzles at, or in, a second region. A greater amount of fuel is supplied to the main nozzles at, or in, the first region than to the main nozzles at, or in, the second to improve combustion efficiency, weak extinction and relight of the combustion chamber in a first mode of operation. A greater total amount of fuel is supplied to the main nozzles than to the pilot nozzles in a second mode of operation.

公开(公告)号：US20210175815A1

公开(公告)日：2021-06-10

申请号：US17108476

申请日：2020-12-01

Applicant: ROLLS-ROYCE plc

Inventor： Graham P. Bruce

IPC: H02M3/335 ,  H02M7/219 ,  H02P9/02 ,  H02J1/00

Abstract: Electrical systems for connecting rotary electric machines to dc networks operating at different voltages V and W where V>W are provided, along with gas turbine engine arrangements incorporating such systems.

公开(公告)号：US20210172379A1

公开(公告)日：2021-06-10

申请号：US16820963

申请日：2020-03-17

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

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

Abstract: An engine core including a turbine, compressor, and a core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from the core shaft and to output drive to the 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, ring gear, and planet carrier to the mounted planet gears. The planet carrier has an effective linear torsional stiffness and the gearbox has a gear mesh stiffness between the planet gears and the ring gear. A carrier to ring mesh ratio of: the   effective   linear   torsional   stiffness   of   the   planet   carrier gear   mesh   stiffness   between   the   planet   gears   and   the   ring   gear is greater than or equal to 0.2.

公开(公告)号：US11028782B2

公开(公告)日：2021-06-08

申请号：US16124559

申请日：2018-09-07

Applicant: ROLLS-ROYCE plc

Inventor： Simon M. Ruston ,  Rong Yang ,  Matthew Fox ,  Aniket Anand Kulkarni

IPC: F01D25/24 ,  F02C9/18 ,  B64D29/08 ,  F02K3/06 ,  F02K3/075

Abstract: A pressure relief arrangement for a gas turbine engine comprises a hinged door and a mount. A plastically deformable member is provided between and coupled to the hinged door and the mount. The deformable member is configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position.