公开(公告)号：US20230167768A1

公开(公告)日：2023-06-01

申请号：US17940055

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C. WONG ,  Jonathan A. CHERRY ,  Paul R. DAVIES ,  David A. JONES ,  Andrew J. NEWMAN ,  Benjamin J. SELLERS ,  Stephen J. BRADBROOK

IPC: F02C7/12 ,  F02C6/20 ,  F02C7/32

CPC classification number: F02C7/12 ,  F02C6/20 ,  F02C7/32 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2260/213

Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.

公开(公告)号：US20220112817A1

公开(公告)日：2022-04-14

申请号：US17495418

申请日：2021-10-06

Applicant: ROLLS-ROYCE PLC

Inventor： Stephen J. BRADBROOK ,  Martin N. GOODHAND ,  Paul M. HIELD ,  Andrew PARSLEY ,  Natalie C. WONG ,  Robert J. CORIN ,  Thomas S. BINNINGTON

IPC: F01D25/10 ,  F02K3/06 ,  F02C7/141 ,  B64D33/10 ,  F01D5/18

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module including 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. Each heat transfer element may be individually and independently fluidly isolated from the remaining heat transfer elements.

公开(公告)号：US20240369000A1

公开(公告)日：2024-11-07

申请号：US18625842

申请日：2024-04-03

Applicant: ROLLS-ROYCE plc

Inventor： Andrew PARSLEY ,  Natalie C. WONG

IPC: F01D21/14

Abstract: An apparatus and method for reducing a pressure differential across a turbine 19 of a gas turbine engine 10 during a shaft break event, comprises a pressure equalization apparatus 300, 400, 500, 600, 700 configured to introduce a pressurised fluid into a core airflow A at a region downstream of the turbine 19, wherein a rearward movement of the turbine 19 or a shaft 26 in a shaft break event directly actuates the pressure equalisation apparatus 300, 400, 500, 600, 700 to directly increase a local pressure at the downstream region 29 of the turbine 19 and thereby reduce the pressure differential across the turbine 19. The reduction in the pressure differential may result in a reduction in the acceleration of the turbine 19.

公开(公告)号：US20240368999A1

公开(公告)日：2024-11-07

申请号：US18625769

申请日：2024-04-03

Applicant: ROLLS-ROYCE plc

Inventor： Andrew PARSLEY ,  Natalie C. WONG

IPC: F01D21/14 ,  F01D21/00

Abstract: An apparatus and method for reducing a pressure differential across a turbine 19 of a gas turbine engine 10 during a shaft break event, comprises a pressure equalization apparatus 200 configured to introduce a pressurised fluid into a core airflow A at a region downstream of the turbine 19 in the event of a shaft break to directly increase a local pressure at the downstream region 29 of the turbine 19 and thereby reduce the pressure differential across the turbine 19. The pressure equalization apparatus comprises a sensor 216 configured to directly detect a shaft break event. The reduction in the pressure differential may result in a reduction in the acceleration of the turbine 19.

公开(公告)号：US20200248582A1

公开(公告)日：2020-08-06

申请号：US16744622

申请日：2020-01-16

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C. WONG

IPC: F01D21/14 ,  F01D21/00 ,  F02C9/20

Abstract: A method of controlling a gas turbine engine includes the steps of: detecting a shaft break event in a shaft connecting a compressor of the gas turbine engine to a turbine of the gas turbine engine; and in response to this detection, activating a shaft break mitigation system which introduces a fluid into a gas flow of the gas turbine engine downstream of the turbine, or increases an amount of a fluid being provided into the gas flow of the gas turbine engine downstream of the turbine, whereby the fluid reduces an effective area of a nozzle for the gas flow so as to reduce the mass flow rate of the gas flow through the turbine.

公开(公告)号：US20250092823A1

公开(公告)日：2025-03-20

申请号：US18969412

申请日：2024-12-05

Applicant: ROLLS-ROYCE PLC

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

IPC: F02C7/04 ,  B64D27/10 ,  B64D27/20 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D33/10 ,  F01D9/06 ,  F02C7/08 ,  F02C7/12 ,  F02C7/14 ,  F02C7/18 ,  F02K3/06 ,  F02K3/075 ,  F02K3/115

Abstract: An aircraft comprises a machine body which encloses a turbofan gas turbine engine. The turbofan gas turbine engine includes a heat exchanger module, fan assembly, compressor module, turbine module, and exhaust module. The heat exchanger module communicates with the fan assembly by an inlet duct. The heat exchanger module includes first heat transfer elements that transfer heat energy from a first fluid within the transfer elements to an airflow passing over a surface of the transfer elements before entry of the airflow into a fan assembly inlet. The first fluid contained within transfer elements has a temperature, and the airflow passing over the transfer element surface has a temperature. The turbofan gas turbine engine further includes at least one second heat transfer element, with the or each second heat transfer element transfers heat energy from the first fluid to a second fluid.

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：US20200248581A1

公开(公告)日：2020-08-06

申请号：US16749109

申请日：2020-01-22

Applicant: ROLLS-ROYCE plc

Inventor： Gareth L. JONES ,  Daniel J. WILLIAMS ,  Natalie C. WONG

IPC: F01D21/02 ,  F02K3/10

Abstract: A method is provided of controlling a gas turbine having a shaft connecting a compressor to a turbine, as well as having a reheat system, and a gas turbine. The method includes the steps of: operating the engine using the reheat system to provide a mass flow rate of reheat fuel into a gas flow of the gas turbine engine downstream of an exit of the turbine; detecting a shaft break event in the shaft; and in response to this detection, maintaining the mass flow rate of the reheat fuel being provided into the gas flow downstream of the turbine exit, whereby the maintained mass flow rate of reheat fuel raises a back pressure downstream of the turbine and thereby reduces a rotational speed of the turbine.