公开(公告)号：SG121797A1

公开(公告)日：2006-05-26

申请号：SG200305669

申请日：2003-09-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUBE BRYAN ,  MILLIKEN ANDREW C ,  MOSLEY JOHN H ,  COOK CONAN

IPC: F01D9/02 ,  F01D5/08 ,  F01D9/00 ,  F01D9/06 ,  F01D11/00 ,  F01D11/04 ,  F02C7/18 ,  F02C7/28 ,  F04D29/10 ,  F04D29/58 ,  F16J15/44 ,  F16J15/447

Abstract: The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

公开(公告)号：DE10344843B4

公开(公告)日：2010-04-29

申请号：DE10344843

申请日：2003-09-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUBE BRYAN ,  MILLIKEN ANDREW D ,  MOSLEY JOHN H ,  COOK CONAN

IPC: F01D9/02 ,  F01D11/02 ,  F01D5/08 ,  F01D9/06 ,  F01D11/00 ,  F01D11/04 ,  F02C7/18 ,  F02C7/28 ,  F04D29/10 ,  F04D29/58 ,  F16J15/44 ,  F16J15/447

Abstract: The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

公开(公告)号：DE10344843A1

公开(公告)日：2004-04-15

申请号：DE10344843

申请日：2003-09-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUBE BRYAN ,  MILLIKEN ANDREW D ,  MOSLEY JOHN H ,  COOK CONAN

IPC: F01D9/02 ,  F01D5/08 ,  F01D9/06 ,  F01D11/00 ,  F01D11/04 ,  F02C7/18 ,  F02C7/28 ,  F04D29/10 ,  F04D29/58 ,  F16J15/44 ,  F16J15/447 ,  F01D11/02

Abstract: The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

公开(公告)号：GB2394257B

公开(公告)日：2005-06-08

申请号：GB0322642

申请日：2003-09-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MILLIKEN ANDREW D ,  MOSLEY JOHN H ,  COOK CONAN

IPC: F01D5/08 ,  F01D9/06 ,  F01D11/00 ,  F01D11/04 ,  F01D9/02 ,  F02C7/18 ,  F02C7/28 ,  F04D29/10 ,  F04D29/58 ,  F16J15/44 ,  F16J15/447

Abstract: The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

公开(公告)号：GB2394257A

公开(公告)日：2004-04-21

申请号：GB0322642

申请日：2003-09-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MILLIKEN ANDREW D ,  MOSLEY JOHN H ,  COOK CONAN

IPC: F01D5/08 ,  F01D9/06 ,  F01D11/00 ,  F01D11/04 ,  F01D9/02 ,  F02C7/18 ,  F02C7/28 ,  F04D29/10 ,  F04D29/58 ,  F16J15/44 ,  F16J15/447

Abstract: Means for delivering cooling air to a seal arrangement 22 in a turbine stage of a gas turbine engine comprises at least one vane 12 having a passageway 20 extending between outer and inner platforms 14, 16, and a tube insert 36, positioned within, having an air inlet 38 and an outlet. Preferably cover means 48 is attached to the outlet to pre-swirl air in the direction of rotor rotation, preferably having a first exit and nozzle placed in the honeycomb pad 28, delivering air into space between two of knife edge seals 32. Preferably a second exit cools seal rim cavity 24. The cover means 48 has a collar portion surrounding the outlet, the collar portion having an interior portion corresponding in shape to the cross section of the insert 36. The central portion of a retainer means may be welded or joined by braze material to the inlet 38, legs may be attached to portion and to a fillet weld. The passageway 20 may allow cooling of internal vane portions.

公开(公告)号：FR2845119A1

公开(公告)日：2004-04-02

申请号：FR0311251

申请日：2003-09-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUBE BRYAN ,  MILLIKEN ANDREW D ,  MOSLEY JOHN H ,  COOK CONAN

IPC: F01D9/02 ,  F01D5/08 ,  F01D9/06 ,  F01D11/00 ,  F01D11/04 ,  F02C7/18 ,  F02C7/28 ,  F04D29/10 ,  F04D29/58 ,  F16J15/44 ,  F16J15/447 ,  F01D25/12 ,  F01D5/18

Abstract: The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

公开(公告)号：EP2971673A4

公开(公告)日：2016-11-09

申请号：EP14774334

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MOSLEY JOHN H ,  CHRISIKOS JAMES P ,  GATES ROGER ,  O'CONNOR JOHN J ,  WU CHARLES C ,  GLASSPOOLE DAVID

IPC: F01D5/08

CPC classification number: F02C9/18 ,  F01D5/082 ,  F02C7/18 ,  F05D2220/3215 ,  Y02T50/673 ,  Y02T50/676

Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.

公开(公告)号：EP2901082A4

公开(公告)日：2015-10-14

申请号：EP13842492

申请日：2013-09-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： NIGGEMEIER CHRIS ,  MOSLEY JOHN H ,  SADIL ANDREAS ,  BLUME KARL D

IPC: F23R3/50 ,  F01D9/06 ,  F01D25/28 ,  F02C3/13 ,  F02C6/08 ,  F02C7/00 ,  F23R3/02

CPC classification number: F02C7/20 ,  F01D9/065 ,  F01D25/24 ,  F01D25/28 ,  F02C3/13 ,  F02C6/08 ,  F02C7/04 ,  F23R3/02 ,  F23R3/50

Abstract: An inner diffuser case for use in a combustor of a gas turbine engine includes a multiple of struts across an annular flow path between an outer shroud and an inner shroud, at least one of the multiple of struts is an open strut.

公开(公告)号：EP2855884A4

公开(公告)日：2016-05-11

申请号：EP13797827

申请日：2013-05-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MOSLEY JOHN H ,  ALVANOS IOANNIS ,  STRIPINIS PHILIP S ,  FREIBERG DOUGLAS PAUL ,  PINERO HECTOR M ,  O'CONNOR JOHN J ,  PIETROBON JON

IPC: F02C7/12 ,  F01D5/08 ,  F01D25/08 ,  F01D25/12

CPC classification number: F01D5/082 ,  F01D25/12

Abstract: A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.