公开(公告)号：JPH1122409A

公开(公告)日：1999-01-26

申请号：JP12192998

申请日：1998-05-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FUKUDA TAKAO ,  PRICE FRANCIS R ,  COOK CONAN P ,  HOFF RICHARD W ,  SINGER IRWIN D

IPC: F01D9/02 ,  F01D5/18 ,  F01D9/06 ,  F02C7/18

Abstract: PROBLEM TO BE SOLVED: To remove particulates from cooling air and efficiently cool a front edge region. SOLUTION: An air foil capable of cooling having a passage to blow out particulates brought by cooling air is opened. Various details of a structure supply cooling air to front edges 60, 69 of the air foil. A chord directional duct 100 is extended to an inlet of a rear part passage extending in the blade length direction passing through a supply passage 92 extending in the blade length direction, a part of cooling air and particulates from the duct 100 are directed to the inside of the rear passage through an inlet 72 of the supply passage 92 by amomemtum effect, and most of a flow of cooling air is directed to the supply passage 92 to cool the front edges 60, 69 of the air foil.

公开(公告)号：WO9412768A3

公开(公告)日：1994-07-21

申请号：PCT/US9310740

申请日：1993-11-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOFF RICHARD W ,  MARTIN DAVID R

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/187 ,  F05D2260/202 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676

Abstract: A coolable airfoil having internal cooling passages (82, 84, 74) is disclosed. Various construction details are developed to increase cooling in critical locations of the airfoil. In one embodiment, a pair of side-by-side spanwisely extending passages (82, 84) flow charting air to the tip (flag) passage (74).

公开(公告)号：DE602007000674D1

公开(公告)日：2009-04-23

申请号：DE602007000674

申请日：2007-08-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LUTJEN PAUL M ,  HOFF RICHARD W ,  PAGE RICHARD H ,  GATES ROGER J ,  BLAIR MICHAEL F

IPC: B22C9/10

公开(公告)号：DE69826367D1

公开(公告)日：2004-10-28

申请号：DE69826367

申请日：1998-06-26

Applicant: UNITED TECHNOLOGIES CORP HARTF

Inventor： FUKUDA TAKAO ,  PRICE FRANCIS R ,  COOK CONAN P ,  HOFF RICHARD W ,  SINGER IRWIN D

IPC: F01D9/02 ,  F01D5/18 ,  F01D9/06 ,  F02C7/18 ,  F01D25/32

Abstract: A coolable airfoil has a passage 94 for discharging particulates entrained in cooling air to provide clean cooling air to the leading edge 60 of the airfoil. A chordwise duct 100 extends past a spanwisely extending supply passage 92 to the inlet of a spanwisely extending rear passage 94 such that momentum effects direct the flow of a portion of cooling air and particulates from the duct, past the entrance of the supply passage 92 and into the rear passage 94. The rear passage 94 has a purge hole 96 through which the particulates may be removed.

公开(公告)号：SG139617A1

公开(公告)日：2008-02-29

申请号：SG2007028566

申请日：2007-04-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THOLEN SUSAN M ,  LUTJEN PAUL M ,  PAGE RICHARD H ,  HOFF RICHARD W ,  GATES ROGER J ,  BLAIR MICHAEL F

Abstract: BLADE OUTER AIR SEAL CORES AND MANUFACTURE METHODS A blade outer air seal (BOAS) casting core has first and second end portions and a plurality of legs. Of these legs, first legs each have: a proximal end joining the first end portion; a main body portion; and a free distal portion. Second legs each have: a proximal end joining the second end portion; a main body portion; and a free distal portion.

公开(公告)号：DE69826367T2

公开(公告)日：2005-02-17

申请号：DE69826367

申请日：1998-06-26

Applicant: UNITED TECHNOLOGIES CORP HARTF

Inventor： FUKUDA TAKAO ,  PRICE FRANCIS R ,  COOK CONAN P ,  HOFF RICHARD W ,  SINGER IRWIN D

IPC: F01D9/02 ,  F01D5/18 ,  F01D9/06 ,  F02C7/18 ,  F01D25/32

Abstract: A coolable airfoil has a passage 94 for discharging particulates entrained in cooling air to provide clean cooling air to the leading edge 60 of the airfoil. A chordwise duct 100 extends past a spanwisely extending supply passage 92 to the inlet of a spanwisely extending rear passage 94 such that momentum effects direct the flow of a portion of cooling air and particulates from the duct, past the entrance of the supply passage 92 and into the rear passage 94. The rear passage 94 has a purge hole 96 through which the particulates may be removed.

公开(公告)号：CA1045040A

公开(公告)日：1978-12-26

申请号：CA239355

申请日：1975-11-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOFF RICHARD W

IPC: F01D5/08 ,  F02C7/18

Abstract: TURBINE VANE COOLING A method and apparatus for providing high pressure cooling air to the turbine vanes of a gas turbine engine is disclosed. A centrifugal compressor stage is interposed in the flow path of cooling air to the turbine vanes. The centrifugal compressor stage raises the pressure of the cooling air to a value substantially greater than the pressure of the combustion gases entering the turbine. The availability of high pressure cooling air allows the incorporation of improved cooling systems in the turbine vanes. Increasingly effective cooling systems are necessary to the continued development of low pressure drop combustion chambers which discharge high temperature gases to the inlet of the turbine.