초록 ▼

A turbine vane for use in a gas turbine engine having high turbine inlet temperatures is disclosed. Film cooling is provided at the leading edge of the vane airfoil by cooling air which flows through leading edge holes from a hollow cavity in the airfoil section. Film cooling air is also provided th

A turbine vane for use in a gas turbine engine having high turbine inlet temperatures is disclosed. Film cooling is provided at the leading edge of the vane airfoil by cooling air which flows through leading edge holes from a hollow cavity in the airfoil section. Film cooling air is also provided through wall holes along the suction and pressure sides of the airfoil. A U-shaped insert having a pressure leg and a suction leg is disposed within the hollow cavity to isolate the leading edge holes from the wall holes. When the cavity is pressurized, the legs are each urged against corresponding seal ribs which extend from the cavity wall to effectively isolate the leading edge holes.

대표청구항 ▼

In a cooled turbine vane having a hollow airfoil section including a leading edge having a plurality of leading edge cooling holes in gas communication with the hollow portion thereof, a pressure side, and a suction side having a plurality of suction side holes in gas communication with the hollow p

In a cooled turbine vane having a hollow airfoil section including a leading edge having a plurality of leading edge cooling holes in gas communication with the hollow portion thereof, a pressure side, and a suction side having a plurality of suction side holes in gas communication with the hollow portion thereof, the improvement comprising: a substantially U-shaped insert having a pressure side leg and a suction side leg, the insert being disposed within the hollow portion of the airfoil section; and means located within the hollow portion of the airfoil section, including a first sealing rib on the suction side of the airfoil section between the suction side holes and the leading edge cooling holes and a second sealing rib on the pressure side of the airfoil section adjacent to the leading edge holes, for isolating cooling flow to the leading edge holes from flow to the suction side holes, the suction and pressure legs of the insert being adapted to seal against the first sealing rib and second sealing rib respectively in operative response to the internal pressure within the hollow portion of the airfoil section.