公开(公告)号：US20210222563A1

公开(公告)日：2021-07-22

申请号：US17064667

申请日：2020-10-07

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin MOHANKUMAR ,  Mark J WILSON ,  Cesare A HALL

IPC: F01D5/14

Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, compressor, and core shaft connecting turbine to the compressor; a fan located upstream of engine core, the fan containing a plurality of fan blades mounted for rotation about an engine axis, each blade of the plurality of fan blades having a leading edge and trailing edge extending across a span of an airflow duct from blade root to tip; and a gearbox that receives an input from core shaft and outputs drive to fan so as to drive the fan at a lower rotational speed than the core shaft, wherein the trailing edge of each blade is characterized by a metric M defined as a rate of change of an angle of trailing edge between 0.4 and 0.8 of the span divided by an area averaged trailing edge angle, M being not less than around 4.