公开(公告)号：US20240011433A1

公开(公告)日：2024-01-11

申请号：US18215868

申请日：2023-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Stephen J. BRADBROOK ,  William J. SMITH ,  Jonathan P. BRADLEY

IPC: F02C3/06

CPC classification number: F02C3/06 ,  F05D2220/36

Abstract: A novel configuration for axial flow gas turbine engine for aircraft has an engine core having a core length and including first turbine, axial compressor, and drive connecting the first turbine to the axial compressor, the engine core further including a second turbine, and a fan shaft connecting the second turbine to a fan located upstream of the engine core, the fan including a plurality of fan blades extending from a fan hub, the fan having a tip radius from 90 mm to 225 mm and wherein the ratio of fan tip radius to an engine length is 0.15 to 0.25. The engine may have 3, 4 or 5 compressor stages and a combustor volume (in litres) which when divided by the fan tip radius (in mm) is 0.015 to 0.083. The fan may be a multistage fan configured to permit an electric motor to be located within the fan hub diameter.