MULTI-LOBED COOLING HOLE
First Claim
1. A gas turbine engine component subjected to a flow of high temperature gas, the component comprising:
- a wall having first and second wall surfaces; and
a cooling hole extending through the wall and comprising;
an inlet located at the first wall surface;
an outlet located at the second wall surface;
a metering section extending downstream from the inlet; and
a diffusing section extending from the metering section to the outlet and comprising;
a first lobe diverging longitudinally and laterally from the metering section and having a first shape;
a second lobe generally opposite the first lobe and diverging longitudinally and laterally from the metering section and having a second shape different from the first shape; and
a transition region positioned between the first and second lobes, the transition region comprising a downstream end adjacent the outlet.
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Accused Products
Abstract
A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe, a second lobe and a transition region. The first lobe diverges longitudinally and laterally from the metering section and has a first shape. The second lobe is generally opposite the first lobe and diverges longitudinally and laterally from the metering section and has a second shape different from the first shape. The transition region is positioned between the first and second lobes and includes a downstream end adjacent the outlet.
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Citations
18 Claims
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1. A gas turbine engine component subjected to a flow of high temperature gas, the component comprising:
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a wall having first and second wall surfaces; and a cooling hole extending through the wall and comprising; an inlet located at the first wall surface; an outlet located at the second wall surface; a metering section extending downstream from the inlet; and a diffusing section extending from the metering section to the outlet and comprising; a first lobe diverging longitudinally and laterally from the metering section and having a first shape; a second lobe generally opposite the first lobe and diverging longitudinally and laterally from the metering section and having a second shape different from the first shape; and a transition region positioned between the first and second lobes, the transition region comprising a downstream end adjacent the outlet. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A wall of a component of a gas turbine engine subjected to a flow of high temperature gas, the wall comprising:
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first and second wall surfaces; an inlet located at the first wall surface; an outlet located at the second wall surface; a metering section commencing at the inlet and extending downstream from the inlet; and a diffusing section extending from the metering section and terminating at the outlet, the diffusing section comprising; a first lobe diverging longitudinally and laterally from the metering section and having a first shape; a second lobe generally opposite the first lobe and diverging longitudinally and laterally from the metering section and having a second shape different from the first shape; and a transition region positioned between the first and second lobes, the transition region comprising a downstream end adjacent the outlet. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18)
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Specification