公开(公告)号：US20230167784A1

公开(公告)日：2023-06-01

申请号：US17940034

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J SELLERS ,  Stephen J BRADBROOK ,  Robert J CORIN ,  Richard J HUNSLEY

IPC: F02K3/06 ,  F01D15/10

CPC classification number: F02K3/06 ,  F01D15/10 ,  F05D2220/323 ,  F05D2220/36

Abstract: An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine is positioned downstream of the fan assembly and is connected to the turbine module. The fan assembly includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The turbine module includes a lowest pressure turbine stage having a row of rotor blades. The gas turbine engine has a fan tip axis that joins a radially outer tip of the leading edge of one of the plurality of fan blades of the highest pressure fan stage, and the radially outer tip of the trailing edge of one of the rotor blades of the lowest pressure turbine stage. The fan tip axis lies in a longitudinal plane which contains a centreline of the gas turbine engine. The fan axis angle is between 11 and 20 degrees.