公开(公告)号：JP2002227605A

公开(公告)日：2002-08-14

申请号：JP2001387919

申请日：2001-12-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： NICOLSON MATTHEW ,  DUESLER PAUL W

IPC: F01D9/02 ,  F01D5/14 ,  F01D17/16

Abstract: PROBLEM TO BE SOLVED: To provide a vane in which the stress is reduced in a transitional region between a rigid body portion of the vane (trunnion) and an flexible body portion (air foil). SOLUTION: The vane 10 has a trunnion part 12 and an air foil part 18. A stress reducing undercut part 24 is installed on the trunnion 12 approaching the transitional region 22 demarcating between the trunnion part 12 of the vane 10 and the air foil part 18.

公开(公告)号：JPH11132004A

公开(公告)日：1999-05-18

申请号：JP24789398

申请日：1998-09-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SAMIT MARC ,  WELCH DOUGLAS A ,  DUESLER PAUL W ,  MARKHAM PATRICK D ,  PENDA ALLAN R

IPC: F01D5/14 ,  F01D5/18 ,  F02K3/04

Abstract: PROBLEM TO BE SOLVED: To keep a danger of damage of a following blade to a minimum in the case where a break off hollow fan blade comes into collision with the following blade. SOLUTION: A hollow air foil for gas-turbine engine having a leading edge 50, a trailing edge 52, a positive pressure face 54 and a negative pressure face 56 comprises a solid region 78 in which a thickness of a blade chord is increased, and a plurality of buttresses 82, 84, 86, 88. The hollow air foil for gas-turbine engine is selectively strengthened. Accordingly, a danger of breakage of the air foil is reduced in a case where the air foil comes into collision with a following air foil when the air foil is in a braking state.

公开(公告)号：WO2014186008A3

公开(公告)日：2015-01-22

申请号：PCT/US2014015759

申请日：2014-02-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  DUESLER PAUL W

IPC: F01D5/08 ,  F01D25/10 ,  F02C9/16

CPC classification number: F02C9/18 ,  F01D5/08 ,  F01D25/10 ,  F02C3/06 ,  F02C7/28 ,  F05D2220/32 ,  F05D2230/642 ,  F05D2240/30 ,  F05D2260/232 ,  Y02T50/676

Abstract: A gas turbine engine has a compressor rotor with blades and a disk. A bore is defined radially inwardly of the disk. A combustor includes a burner nozzle. A tap taps air that has been combusted in the combustor section through a valve, and into the bore of the disk. A method is also disclosed.

Abstract translation: 燃气涡轮发动机具有带有叶片和盘的压缩机转子。 孔被径向向内限定在盘的内部。 燃烧器包括燃烧器喷嘴。 分接头敲击已经通过阀在燃烧器部分中燃烧并进入盘的孔中的空气。 还公开了一种方法。

公开(公告)号：DE69827727T2

公开(公告)日：2005-03-31

申请号：DE69827727

申请日：1998-09-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SAMIT MARC ,  DUESLER PAUL W ,  WELCH DOUGLAS A ,  MARKHAM PATRICK D ,  PENDA ALLAN R

IPC: F01D5/14 ,  F01D5/18 ,  F02K3/04 ,  F01D5/28

公开(公告)号：DE69827727D1

公开(公告)日：2004-12-30

申请号：DE69827727

申请日：1998-09-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SAMIT MARC ,  DUESLER PAUL W ,  WELCH DOUGLAS A ,  MARKHAM PATRICK D ,  PENDA ALLAN R

IPC: F01D5/14 ,  F01D5/18 ,  F02K3/04 ,  F01D5/28

公开(公告)号：EP2903776A4

公开(公告)日：2015-10-21

申请号：EP13843647

申请日：2013-10-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUESLER PAUL W ,  FILEWICH PAUL

IPC: B23K26/00 ,  B23K26/06 ,  C21D10/00 ,  C22F1/18 ,  G01M7/08

CPC classification number: G01M7/08 ,  B23K26/0069 ,  B23K2201/001 ,  C21D10/005 ,  C22F1/18

公开(公告)号：EP2959109A4

公开(公告)日：2016-06-01

申请号：EP14797283

申请日：2014-02-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  DUESLER PAUL W

IPC: F01D5/08 ,  F01D25/10 ,  F02C9/16

CPC classification number: F02C9/18 ,  F01D5/08 ,  F01D25/10 ,  F02C3/06 ,  F02C7/28 ,  F05D2220/32 ,  F05D2230/642 ,  F05D2240/30 ,  F05D2260/232 ,  Y02T50/676

Abstract: A gas turbine engine has a compressor rotor with blades and a disk. A bore is defined radially inwardly of the disk. A combustor includes a burner nozzle. A tap taps air that has been combusted in the combustor section through a valve, and into the bore of the disk. A method is also disclosed.