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：US20230167767A1

公开(公告)日：2023-06-01

申请号：US17940035

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J SELLERS ,  Jonathan A CHERRY ,  Craig TOWN

IPC: F02C7/12 ,  F02C3/06

CPC classification number: F02C7/12 ,  F02C3/06 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/40

Abstract: An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine positioned downstream of the fan assembly is rotationally connected to the turbine module. The fan assembly is in fluid communication with the compressor module by an intermediate duct and includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The compressor module includes a lowest pressure compressor stage having a row of rotor blades. An intermediate flow axis is defined joining a radially outer tip of a trailing edge of one of the fan blades of the highest pressure fan stage, and a radially outer tip of a leading edge of one of the rotor blades of a leading edge of a lowest-pressure compressor blade. An intermediate flow axis angle and the intermediate flow axis angle is from −20 to −30 degrees.