公开(公告)号：US11208895B2

公开(公告)日：2021-12-28

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.

公开(公告)号：US11692454B2

公开(公告)日：2023-07-04

申请号：US17453501

申请日：2021-11-04

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin Mohankumar ,  Mark J. Wilson ,  Cesare A. Hall

IPC: F01D15/12 ,  F02C7/04 ,  F01D25/24 ,  F02K3/068

CPC classification number: F01D15/12 ,  F01D25/24 ,  F02C7/04 ,  F02K3/068 ,  F05D2220/32 ,  F05D2260/4031

Abstract: An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric Stip, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, L/D is between 0.2 and 0.45 and Stip is from −1 to 0.1.

公开(公告)号：US11598214B2

公开(公告)日：2023-03-07

申请号：US17412759

申请日：2021-08-26

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin Mohankumar ,  Mark J. Wilson ,  Cesare A. Hall

IPC: F01D5/14 ,  B64D27/10 ,  B64D27/24 ,  B64D33/02 ,  F02K3/075 ,  F02K3/06

Abstract: An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric S, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, and L/D is between 0.2 and 0.45.