公开(公告)号：US20220112845A1

公开(公告)日：2022-04-14

申请号：US17484371

申请日：2021-09-24

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: F02C7/18 ,  F02C6/08 ,  F28D9/00

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 (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module includes a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes and a set of channel airflows through each of the channels.

公开(公告)号：US20220112840A1

公开(公告)日：2022-04-14

申请号：US17494523

申请日：2021-10-05

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: F02C7/12 ,  F25B11/00

Abstract: A turbofan gas turbine engine includes heat exchanger module, fan assembly, compressor, turbine and exhaust modules. The fan includes a plurality of fan blades. The heat exchanger in fluid communicates with the fan assembly by an inlet duct, and the heat exchanger includes a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger is divided between a set of vane airflows and a set of channel airflows. Each vane airflow has a vane mass flow rate FlowVane, and each channel air flow has a channel mass flow rate FlowChan. Each hollow vane includes, an inlet, heat transfer, and exhaust portions, with the inlet portion comprising a diffuser element and the heat transfer portion including at least one heat transfer element. The diffuser element causes FlowVane to be lower than FlowChan.

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：US20220112813A1

公开(公告)日：2022-04-14

申请号：US17496193

申请日：2021-10-07

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: F01D5/18 ,  F28D7/16 ,  F02C7/12 ,  F01D5/02

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 fan blades defining a fan diameter. The heat exchanger module is in communication with the fan assembly by an inlet duct, and the heat exchanger module further includes radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between hollow vanes. Each hollow vane accommodates at least one heat transfer element to transfer heat from a first fluid contained within the or each heat transfer element to a corresponding vane airflow passing through the hollow vane and over a surface of the or each heat transfer element. Each hollow vane further includes a flow modulator configured to regulate airflow in proportion to total airflow entering the heat exchanger module in response to a user requirement.

公开(公告)号：US20240369023A1

公开(公告)日：2024-11-07

申请号：US18625743

申请日：2024-04-03

Applicant: ROLLS-ROYCE plc

Inventor： Andrew PARSLEY ,  Natalie C WONG

IPC: F02C9/18

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, 300, 400, 500, 600, 700 configured to introduce a pressurised fluid into a core airflow A at a region directly 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 reduction in the pressure differential may result in a reduction in the acceleration of the turbine 19.

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.