Turbine vane with serpentine cooling
AssigneeFlorida Turbine Technologies, Inc.
InventorGeorge Liang
Life of this patent
Estimating the term…
Abstract
A stator vane for a gas turbine engine having a cooling circuit that passes through the airfoil and both of the inner and the outer diameter endwalls to provide cooling for the airfoil and endwalls. Each endwall includes an intricate cooling circuit and is connected to the serpentine flow circuit within the airfoil to pass cooling air back and fourth from one endwall to the other through one of the legs in the serpentine flow circuit of the airfoil. A row of exit cooling holes is located in one or both of the endwalls and is connected to the last leg of the serpentine circuit to discharge cooling air. The airfoil and endwalls cooling circuit forms a series of passages that meander through the vane before discharging out through the exit holes.
Claims26
A turbine vane comprising:
- An outer diameter endwall and an inner diameter endwall;
- An airfoil extending between the outer diameter endwall and the inner diameter endwall;
- An outer diameter endwall cooling circuit fanned within the outer diameter endwall;
- An inner diameter endwall cooling circuit formed within the inner diameter endwall;
- A multiple pass serpentine flow cooling circuit formed within the airfoil;
- A cooling air supply channel formed within the outer diameter endwall cooling circuit and connected to the first leg of the multiple pass serpentine circuit;
- A first to second cooling passage formed in the ID endwall cooling circuit to connect the first leg to the second leg;
- A second to third cooling passage formed in the OD endwall cooling circuit to connect the second leg to the third leg;
- A third to fourth cooling passage formed in the ID endwall cooling circuit to connect the third leg to the fourth leg;
- A fourth to fifth cooling passage formed in the OD endwall cooling circuit to connect the fourth leg to the fifth leg;
- and,
- A row of exit cooling holes connected to the fifth leg to discharge cooling air from the ID endwall cooling circuit.
A process for cooling a stator vane of a gas turbine engine, comprising the steps of:
- Supplying cooling air to an impingement chamber in the outer diameter endwall;
- Passing the cooling air from the impingement chamber through a first leg of a serpentine cooling circuit formed within the airfoil;
- Passing the cooling air from the first leg through the inner diameter endwall to cool a portion of the inner diameter endwall and then into the second leg of the serpentine circuit;
- Passing the cooling air from the second leg through a portion of the outer diameter endwall to provide cooling for the portion;
- Passing the cooling air from the outer diameter endwall through a third leg of the serpentine circuit;
- and,
- Passing the cooling air from the third leg through a portion of the inner diameter endwall to provide cooling to this portion.
A turbine vane comprising:
- An outer diameter endwall and an inner diameter endwall;
- An airfoil extending between the outer diameter endwall and the inner diameter endwall;
- An outer diameter endwall cooling circuit formed within the outer diameter endwall;
- An inner diameter endwall cooling circuit formed within the inner diameter endwall;
- and,
- A multiple pass serpentine flow cooling circuit formed within the airfoil;
- and,
- Cooling air passage means to connect the two ends wall cooling circuit and the airfoil serpentine flow cooling circuit so that cooling air flows from a first passage in the outer endwall cooling circuit, through a first channel in the airfoil serpentine flow cooling circuit, into a first passage in the inner diameter endwall cooling circuit, through a second channel in the airfoil serpentine flow cooling circuit, and then into a second passage in the outer endwall cooling circuit to provide cooling for the endwalls and the airfoil.
Dependencies are inferred from the claim text.