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.