公开(公告)号：US20170204742A1

公开(公告)日：2017-07-20

申请号：US14997315

申请日：2016-01-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Anthony B. SWIFT ,  Paul M. LUTJEN ,  Neil L. TATMAN ,  Dominic J. MONGILLO, JR. ,  Matthew A. DEVORE ,  Ken F. BLANEY

IPC: F01D25/12 ,  F01D11/08

CPC classification number: F01D25/12 ,  F01D11/08 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/676

Abstract: A gas turbine engine component is provided. The gas turbine engine component comprises a main body and a leading edge cooling passage defined within the main body. The main body has a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The leading edge cooling passage comprises an axial flow cooling passage defined within the main body and adjacent to the leading edge wall and has a leading edge periphery that generally conforms to the elongated transition portion of the leading edge wall.