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：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.