Cooling hole with asymmetric diffuser
AssigneeUnited Technologies Corporation
InventorsMatthew S. Gleiner, Atul Kohli, Mark F. Zelesky
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component 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 diverging longitudinally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.
Claims20
A gas turbine engine component comprising:
- a wall having first and second opposing wall surfaces and defining a cooling hole, the cooling hole extending from an inlet in the first surface to an outlet in the second surface and having:
- a metering section extending downstream from the inlet and comprising a first lateral sidewall;
- and
- a diffusing section extending from the metering section to the outlet and comprising:
- a first lobe diverging longitudinally from the metering section and comprising a second lateral sidewall parallel to the first lateral sidewall;
- and
- a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section.
A wall of a component of a gas turbine engine, the wall comprising:
- 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 comprising a first lateral sidewall;
- and
- a diffusing section extending from the metering section and terminating at the outlet, the diffusing section comprising:
- a first lobe diverging longitudinally from the metering section and comprising a second lateral sidewall parallel to the first lateral sidewall;
- a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section;
- and
- a ridge located between the first and second lobes.
A method for producing a cooling hole in a gas turbine engine wall having first and second wall surfaces, the method comprising:
- forming a metering section between the first wall surface and the second wall surface, wherein the metering section comprises a first lateral sidewall;
- and
- forming a diffusing section between the metering section and the second wall surface, wherein the diffusing section distributes the flow of the fluid into lobes to form a film of cooling fluid at a hole outlet at the second wall surface of the gas turbine engine wall, and wherein the diffusing section comprises:
- a first lobe that diverges longitudinally from the metering section and comprising a second lateral sidewall parallel to the first lateral sidewall;
- and
- a second lobe adjacent the first lobe that diverges longitudinally and laterally from the metering section.
Dependencies are inferred from the claim text.