Gas turbine engine component with impingement and diffusive cooling
AssigneeUnited Technologies Corporation
InventorJinQuan Xu
Life of this patent
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Abstract
A gas turbine engine component includes a gas path wall having a first surface and second surface and an impingement baffle having impingement holes for directing cooling fluid onto the first surface of the gas path wall. A cooling hole extends through the gas path wall. The cooling hole continuously diverges from an inlet in the first surface to an outlet in the second surface such that cross-sectional area of the cooling hole increases continuously from the inlet to the outlet. A longitudinal ridge divides the cooling hole into lobes.
Claims20
A gas turbine engine component comprising:
- a gas path wall having a first surface and second surface;
- an impingement baffle having impingement holes for directing cooling fluid onto the first surface of the gas path wall;
- a cooling hole extending through the gas path wall, the cooling hole continuously diverging from an inlet in the first surface to an outlet in the second surface such that cross-sectional area of the cooling hole increases continuously from the inlet to the outlet;
- and
- a longitudinal ridge dividing the cooling hole into lobes.
A liner assembly for a gas turbine engine, the liner assembly comprising:
- an impingement baffle having impingement holes;
- a liner wall having a first surface extending along the impingement baffle and a second surface extending opposite the first surface;
- a cooling hole formed in the liner wall, the cooling hole diverging continuously from an inlet in the first surface to an outlet in the second surface;
- and
- a longitudinal ridge dividing the cooling hole into lobes;
- wherein the cooling hole is substantially diffusive from the inlet in the first surface of the liner wall to the outlet in the second surface of the liner wall.
Dependencies are inferred from the claim text.