公开(公告)号：US20200049070A1

公开(公告)日：2020-02-13

申请号：US16411862

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M. TOWNES ,  Michael J. WHITTLE ,  Pascal DUNNING

IPC: F02C7/08 ,  F02K3/06 ,  F02C9/16

Abstract: A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is 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：US20200049064A1

公开(公告)日：2020-02-13

申请号：US16411224

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Pascal DUNNING ,  Michael J. WHITTLE ,  Roderick M. TOWNES

IPC: F02C3/073 ,  F02C7/36

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：US20230272752A1

公开(公告)日：2023-08-31

申请号：US18137123

申请日：2023-04-20

Applicant: ROLLS-ROYCE plc

Inventor： Pascal DUNNING ,  Roderick M. TOWNES ,  Michael J. WHITTLE

IPC: F02C7/36 ,  F02C3/073 ,  F01D5/28 ,  F01D5/30

CPC classification number: F02C7/36 ,  F02C3/073 ,  F01D5/284 ,  F01D5/3084 ,  F05D2240/30 ,  F05D2240/12

Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is 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：US20200284154A1

公开(公告)日：2020-09-10

申请号：US16797414

申请日：2020-02-21

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M. TOWNES ,  Neal CARTER ,  Thomas W. MARTIN

IPC: F01D5/22 ,  F01D11/08

Abstract: A turbomachine for a gas turbine engine, comprising: a rotor disc arranged to rotate about a fixed central axis. A plurality of rotor blades connected to the rotor disc, wherein the rotor blades extend within a gas flow path. A rotating annulus is arranged to rotate in a fixed rotational alignment relative to the rotor disc. An outer surface of the rotating annulus is arranged to define part of the boundary of the gas flow path. A gas turbine engine for an aircraft and a method of defining the boundary of a gas flow path within a turbomachine is also disclosed.

公开(公告)号：US20200049066A1

公开(公告)日：2020-02-13

申请号：US16411341

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Pascal DUNNING ,  Roderick M. TOWNES ,  Michael J WHITTLE

IPC: F02C3/073 ,  F02C7/36

Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is 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：US20200049021A1

公开(公告)日：2020-02-13

申请号：US16423343

申请日：2019-05-28

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M. TOWNES ,  Pascal DUNNING ,  Michael J. WHITTLE

IPC: F01D9/04 ,  F02C3/073 ,  F02C7/36 ,  F01D11/12 ,  F01D5/14

Abstract: A highly efficient gas turbine engine includes a fan 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：US20180230836A1

公开(公告)日：2018-08-16

申请号：US15895068

申请日：2018-02-13

Applicant: ROLLS-ROYCE plc

Inventor： Ian TIBBOTT ,  Roderick M. TOWNES ,  Andrew KING

IPC: F01D9/04 ,  F01D25/12

CPC classification number: F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205

Abstract: There is disclosed a stator vane section for a gas turbine engine. The stator vane comprises an aerofoil, a first platform at a radial end of the aerofoil, a cooling chamber within the aerofoil and a guide duct within the cooling chamber. An impingement chamber is defined between the first platform and a perforated impingement plate provided on the first platform to receive cooling air through the impingement plate. The guide duct is coupled to the first platform so that a collecting chamber extending around the guide duct is defined between the guide duct and the first platform and the collecting chamber is configured to receive cooling air from the impingement chamber via a plurality of collecting channels, and is configured to direct cooling air to the cooling chamber.