公开(公告)号：US20210372323A1

公开(公告)日：2021-12-02

申请号：US17399309

申请日：2021-08-11

Applicant: Raytheon Technologies Corporation

Inventor： Jonathan Gilson ,  Bruce L. Morin ,  Ramons A. Reba ,  David A. Topol ,  Wesley K. Lord

IPC: F02C3/107 ,  F01D9/04 ,  F04D29/54 ,  F01D25/16 ,  F04D29/66 ,  F02K3/06

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.