公开(公告)号：US20230025200A1

公开(公告)日：2023-01-26

申请号：US17958405

申请日：2022-10-02

Applicant: Raytheon Technologies Corporation

Inventor： Yuan J. Qiu ,  Robert M. Miller ,  Wesley K. Lord ,  Gavin Hendricks

IPC: F02C7/04 ,  F02K3/06 ,  F01D5/02 ,  F01D17/10 ,  F01D25/24 ,  F02C3/04

Abstract: A gas turbine engine includes a fan section including a fan. A fan nacelle surrounds the fan and includes an inlet with an inlet leading edge plane and a throat. A compressor section is arranged in a core nacelle and includes a first compressor and a second compressor. A turbine section is arranged in the core nacelle and includes a fan drive turbine and a second turbine. A fan hub mounts the fan and a spinner axially forward of the fan. The fan drive turbine drives the fan through a geared architecture. The fan includes a fan leading edge forward-most point spaced apart from the inlet leading edge plane by an inlet length. The spinner includes a spinner length from a spinner forward-most point to the fan leading edge forward-most point. A ratio of the spinner length to inlet length is greater than or equal to 0.5.