公开(公告)号：US11506059B2

公开(公告)日：2022-11-22

申请号：US17030040

申请日：2020-09-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shailesh Kumar ,  Shakeel Nasir ,  Jyotichandra Jingade ,  Mahmoud Mansour

IPC: F01D5/14 ,  F02C3/08 ,  F01D5/04

Abstract: An impeller associated with a compressor of a gas turbine engine includes a plurality of impeller blades. Each impeller blade of the plurality of impeller blades has a leading edge and a trailing edge opposite the leading edge in a streamwise direction. Each impeller blade of the plurality of impeller blades extends in a spanwise direction from a hub at 0% span to a tip at 100% span, and each impeller blade of the plurality of impeller blades has a plurality of mean camber lines that each extend from the leading edge to the trailing edge at a respective spanwise location. The leading edge includes a partially swept leading edge surface defined between 70% span to 100% span that extends in the streamwise direction between 3% to 15% of a mean camber line at 100% span.