公开(公告)号：US20190078450A1

公开(公告)日：2019-03-14

申请号：US15698997

申请日：2017-09-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James A. Eley ,  Eric A. Grover ,  Thomas J. Praisner

IPC: F01D9/04 ,  F01D5/14 ,  F01D17/16

Abstract: An inlet guide vane having varied trailing edge geometry is provided. The inlet guide vane may have an inner diameter edge opposite an outer diameter edge, and may comprise a leading edge part and a trailing edge part. The trailing edge part may comprise a trailing edge length defining a length between a forward edge and an aft edge. The trailing edge length may vary in length. The trailing edge part may be displaced from the leading edge part at a stagger angle. The stagger angle may vary in displacement.

公开(公告)号：US20200232330A1

公开(公告)日：2020-07-23

申请号：US16251219

申请日：2019-01-18

Applicant: United Technologies Corporation

Inventor： Sue-Li Chuang ,  John Logan Whelan ,  Mark A. Stephens ,  Kenneth P. Clark ,  Liselle A. Joseph ,  James A. Eley

IPC: F01D5/22 ,  F01D5/14 ,  F01D5/26

Abstract: A component system of a gas turbine engine including: a first component having an outer surface; a second component having an outer surface, the second component and the first component being in a facing spaced relationship defining an air passageway therebetween; and a first recess located in at least one of the outer surface of the first component proximate the air passage and the outer surface of the first component proximate the air passage, wherein the first recess is located proximate a throat within the air passageway stretching between the first component and the second component.