Integral swirl knife edge injection assembly

A system for delivering cooling air to a knife edge seal arrangement in a turbine stage of a gas turbine engine comprising:

• at least one vane of said turbine stage having a passageway extending from an outer platform of said at least one vane to an inner platform of said at least one vane;
• means for delivering cooling air to said seal arrangement;
• said delivering means comprises a tube insert positioned within said passageway;
• said tube insert having an inlet at one end for receiving cooling air and an outlet at a second end;
• and
• said delivering means further comprising cover means attached to said second end of said tube insert, said cover means having means for receiving cooling air from said tube insert and means for delivering said cooling air to said seal arrangement.

A system for delivering cooling air to a knife edge seal arrangement in a turbine stage of a gas turbine engine comprising:

• at least one vane of said turbine stage having a passageway extending from an outer platform of said at least one vane to an inner platform of said at least one vane;
• means for delivering cooling air to said seal arrangement;
• said delivering means comprising a tube insert positioned within said passageway;
• said tube insert having an inlet at one end for receiving cooling air and an outlet at a second end;
• said delivering means further comprising cover means attached to said second end of said tube insert for receiving cooling air from said tube insert and delivering said cooling air to said seal arrangement;
• and
• said cover means having means for providing said cooling air to said seal arrangement in a pre-swirled manner in a direction of rotation of a turbine rotor stage of said turbine engine.

A system for delivering cooling air to a knife edge seal arrangement in a turbine stage of a gas turbine engine comprising:

• at least one vane of said turbine stage having a passageway extending from an outer platform of said at least one vane to an inner platform of said at least one vane;
• means for delivering cooling air to said seal arrangement;
• said delivering means comprises a tube insert positioned within said passageway;
• said tube insert having an inlet at one end for receiving cooling air and an outlet at a second end;
• said delivering means further comprising cover means attached to said second end of said tube insert for receiving cooling air from said tube insert and delivering said cooling air to said seal arrangement;
• said cover means having means for providing said cooling air to said seal arrangement in a pre-swirled manner in a direction of rotation of a turbine rotor stage of said turbine engine;
• said seal arrangement including a honeycomb pad and a plurality of knife edge seals in contact with said honeycomb pad and said means for providing said cooling air comprising a first nozzle which extends through said honeycomb pad into a space between two of said knife edge seals;
• and
• said cooling air providing means further comprising a second nozzle for providing cooling air to a seal rim cavity.

A system for delivering cooling air to a knife edge seal arrangement in a turbine stage of a gas turbine engine comprising:

• at least one vane of said turbine stage having a passageway extending from an outer platform of said at least one vane to an inner platform of said at least one vane;
• means for delivering cooling air to said seal arrangement;
• said delivering means comprises a tube insert positioned within said passageway;
• said tube insert having an inlet at one end for receiving cooling air and an outlet at a second end;
• said delivering means further comprising cover means attached to said second end of said tube insert for receiving cooling air from said tube insert and delivering said cooling air to said seal arrangement;
• and
• said cover means having a collar protruding from one side and said collar surrounding said outlet end of said tube insert.

A system for delivering cooling air to a knife edge seal arrangement in a turbine stage of a gas turbine engine comprising:

• at least one vane of said turbine stage having a passageway extending from an outer platform of said at least one vane to an inner platform of said at least one vane;
• means for delivering cooling air to said seal arrangement;
• said delivering means comprises a tube insert positioned within said passageway;
• said tube insert having an inlet at one end for receiving cooling air and an outlet at a second end;
• said delivering means further comprising cover means attached to said second end of said tube insert for receiving cooling air from said tube insert and delivering said cooling air to said seal arrangement;
• said delivering means further comprising means affixed to said inlet end of said tube insert for retaining said tube insert in position with respect to said passageway;
• and
• said retaining means having a central portion configured to fit over the inlet end of said tube insert and a plurality of retainer legs affixed to said central portion.