公开(公告)号：US20180171819A1

公开(公告)日：2018-06-21

申请号：US15818968

申请日：2017-11-21

Applicant: ROLLS-ROYCE plc

Inventor： Paul M. HIELD

IPC: F01D17/16

CPC classification number: F01D17/162 ,  F01D5/145 ,  F01D5/146 ,  F04D29/563 ,  F05D2240/123 ,  F05D2240/124 ,  Y02T50/673

Abstract: There is disclosed a variable guide vane device for a gas turbine engine comprising first and second vanes arranged in axial flow series. The first and second vanes are spaced apart so as to define a radially extending slot for fluid flow therebetween.

公开(公告)号：US20220205389A1

公开(公告)日：2022-06-30

申请号：US17494738

申请日：2021-10-05

Applicant: ROLLS-ROYCE plc

Inventor： Paul M. HIELD ,  Jonathan A. CHERRY ,  Thomas S. BINNINGTON

IPC: F02C7/12 ,  F01D5/18 ,  B64D33/08 ,  B64D31/00

Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly comprises 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 comprises a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. The heat exchanger module has a square axial cross-sectional profile, where a side length of the square cross-section is D.

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：US20250163852A1

公开(公告)日：2025-05-22

申请号：US19023732

申请日：2025-01-16

Applicant: ROLLS-ROYCE plc

Inventor： Paul M. HIELD ,  Jonathan A CHERRY ,  Thomas S BINNINGTON

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

Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly comprises 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 comprises a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. The heat exchanger module has a square axial cross-sectional profile, where a side length of the square cross-section is D.

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.