公开(公告)号：US11649764B2

公开(公告)日：2023-05-16

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

CPC classification number: F02C7/04 ,  B64D27/10 ,  B64D27/20 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D33/10 ,  F01D9/065 ,  F02C7/08 ,  F02C7/12 ,  F02C7/14 ,  F02C7/18 ,  F02K3/06 ,  F02K3/075 ,  B64D2033/024 ,  B64D2033/0286 ,  F02K3/115 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/213

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：US11549438B2

公开(公告)日：2023-01-10

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.