公开(公告)号：US20220112866A1

公开(公告)日：2022-04-14

申请号：US17497606

申请日：2021-10-08

Applicant: ROLLS-ROYCE plc

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

IPC: F02K3/075 ,  F02K3/06 ,  B64D33/10 ,  B64D27/20

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：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：US20220112844A1

公开(公告)日：2022-04-14

申请号：US17484974

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 ,  F01D25/12

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). The heat exchanger module comprises a plurality of heat transfer elements.
The heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The inlet duct has a fluid path length along a central axis of the inlet duct between a downstream-most face of the heat transfer elements and an upstream-most face of the fan assembly. The fluid path length is less than 10.0*D.

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：US20220112839A1

公开(公告)日：2022-04-14

申请号：US17484096

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

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

IPC: F02C7/10

Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, an inlet duct, 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 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 the fan assembly.
In use, the first fluid has a maximum temperature of 80° C., and the heat exchanger module transfers at least 300 kW of heat energy from the first fluid to the airflow.