公开(公告)号：US20220112841A1

公开(公告)日：2022-04-14

申请号：US17484873

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

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

IPC: F02C7/14

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes 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. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter PEX (W/N) defined as PEX=H/T is 0.4 to 6.0.