Turbine engine component with a cooling aperture
OwnerEmily Hope Davenport, Zachary Daniel Webster +5inventors
InventorsEmily Hope Davenport, Zachary Daniel Webster, Daniel Endecott Osgood, Michal Osusky, Ricardo Caraballo, Emma Grace Schuele, Evin Nathaniel Barber
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Abstract
An engine component for a gas turbine engine, such as an airfoil rotatable about the engine centerline, includes an outer wall with a cooling aperture. The cooling aperture defines a cavity within the outer wall, and exhausting at a diffuser outlet to provide a cooling film over the outer wall. At least one metering hole fluidly couples the cooling aperture to an interior cooling circuit, where a cooling fluid flow is provided into the cooling aperture and then exhausts from the diffuser outlet.
Claims20
A turbine blade assembly for a gas turbine engine, the turbine blade assembly comprising:
- an airfoil including an outer wall defining an interior, the outer wall having an interior surface facing the interior and an exterior surface opposite the interior surface;
- a cooling circuit in the interior to provide a flow of cooling fluid;
- and
- a cooling aperture in the outer wall and fluidly coupled to the cooling circuit, the cooling aperture comprising:
- a cavity;
- at least one metering hole that fluidly couples the cooling circuit and the cavity, with the at least one metering hole defining a longitudinal axis;
- a diffuser outlet exhausting from the cavity at the exterior surface, the diffuser outlet having a forward edge spaced from an aft edge, the forward edge meeting the aft edge at a first end and a second end;
- a metering hole area (A1) of the cooling aperture is defined as the minimum cross-sectional area of the at least one metering hole when only one metering hole is present or a sum of the minimum cross-sectional areas of the at least one metering hole when multiple metering holes are present, wherein the metering hole area (A1) is 0.051 to 0.456 millimeters squared (m2);
- a diffuser outlet area (A2) defined as an area of the diffuser outlet at the exterior surface of the airfoil, wherein the diffuser outlet area (A2) is 0.129 to 4.000 mm2;
- a diffuser outlet length (le) defined as a length measured along a curved line that is equidistant between the forward edge and the aft edge and extends between the first end and the second end of the diffuser outlet, wherein the diffuser outlet length (le) is 1.524 to 7.167 millimeters (mm);
- and
- a diffuser outlet vector length (le,v) defined as a vector length measured extending between the first end and the second end of the diffuser outlet, wherein the diffuser outlet vector length (le,v) is 1.295 to 6.096 mm;
- wherein
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A turbine blade assembly for a turbine engine, the turbine blade assembly comprising:
- an airfoil having outer wall defining an interior, the outer wall having an exterior surface and an interior surface;
- a cooling circuit in the interior to provide a flow of cooling fluid;
- and
- a cooling aperture in the outer wall, the cooling aperture comprising:
- a cavity at least partially defined between an inner surface and an outer surface, the cavity having a linear portion where the inner and outer surfaces are planar and parallel to each other;
- a first side partially defining the cavity;
- a second side partially defining the cavity, and meeting the first side at a junction, wherein a virtual plane is defined as extending through the junction spaced equidistant between the inner surface and the outer surface along the linear portion;
- a diffuser outlet exhausting from the cavity at the exterior surface, the diffuser outlet having a forward edge spaced from an aft edge, with the forward edge meeting the aft edge at a first end arranged at the first side and a second end arranged at the second side;
- a first axis defined extending between the junction and the first end;
- a first side axis defined as a projection of the first axis onto the virtual plane;
- a second axis defined extending between the junction and the second end;
- a second side axis defined as a projection of the second axis onto the virtual plane;
- a first curvature angle (γA) defined as an angle between the first axis and the first side axis, wherein the first curvature angle (γA) is 0.227 to 0.524 radians;
- and
- a second curvature angle (γB) defined as an angle between the second axis and the second side axis, wherein the second curvature angle (γB) is 0.227 to 0.524 radians,
- wherein
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Dependencies are inferred from the claim text.