公开(公告)号：US20210062761A1

公开(公告)日：2021-03-04

申请号：US16985880

申请日：2020-08-05

Applicant: ROLLS-ROYCE plc

Inventor： Chia Hui LIM ,  Christopher T.J. SHEAF

IPC: F02K3/02 ,  F01D25/34 ,  F02C3/113

Abstract: A gas turbine engine for an aircraft includes an engine core, a fan, an air intake and a gearbox. The engine core includes a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The fan is upstream of the engine core and includes a plurality of fan blades, and has a diameter greater than 2.0 m. The air intake is upstream of the fan and has ratio of intake length to fan diameter of 0.20 to 0.60. The gearbox receives an input from the core shaft and drives the fan at a lower rotational speed than the core shaft. The gas turbine engine has a bypass ratio greater than 10; and the air intake defines a highlight area, wherein the ratio of highlight area to throat area is from 1.15 to 1.35 and the ratio of diffuser area to throat area is from 0.85 to 1.15.