公开(公告)号：US20160084106A1

公开(公告)日：2016-03-24

申请号：US14959542

申请日：2015-12-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew R. Feulner ,  Shengfang Liao

IPC: F01D17/14 ,  F01D25/24

CPC classification number: F01D17/14 ,  B64D2033/0233 ,  F01D9/04 ,  F01D25/02 ,  F01D25/24 ,  F02C7/04 ,  F02C7/047 ,  F05D2220/32

Abstract: A gas turbine engine is defined wherein the inlet guide vanes leading into a core engine flow path are sized and positioned such that flow paths positioned circumferentially intermediate the vane are sufficiently large that a hydraulic diameter of greater than or equal to about 1.5 is achieved. This will likely reduce the detrimental effect of icing.