Component for a turbine engine with a hole
AssigneeGeneral Electric Company
InventorRonald Scott Bunker
Life of this patent
Estimating the term…
Abstract
An engine component, such as an airfoil, for a turbine engine having a hole, which can be a film hole, within the outer wall of the engine component where cooling air moves from an interior cavity through the hole to an outer surface of the engine component providing a cooling film on the outer surface of the engine component.
Claims41
A component for a turbine engine comprising:
- a wall separating a cooling airflow from a hot airflow having a first surface facing the cooling airflow and a second surface facing the hot airflow;
- at least one film hole extending through the wall defining a passage extending between an inlet located in the first surface and an outlet located in the second surface, where the passage defines an inner surface having an upstream side and a downstream side with respect to the hot airflow, with one of the inlet and outlet having a non-occluded portion located on the downstream side;
- and
- a porous material located within the hole extending along at least a portion of the upstream side of the passage with respect to the hot airflow and at least partially defining a border of the non-occluded portion;
- wherein a remaining portion of the border is defined by the downstream side of the passage that is free of porous material.
A method of controlling a momentum profile of a cooling air flow emitted from a hole defining a passage extending between an inlet on a cooled surface of an engine component and an outlet on a heated surface facing a hot airflow of the engine component where the passage defines an inner surface having an upstream side and a downstream side with respect to the hot airflow, the method comprising:
- introducing a cooling air flow into the inlet of the hole,
- emitting the introduced cooling air flow from a non-occluded portion of the hole along the downstream side of the passage free of porous material, and
- emitting the introduced cooling air flow from a partially-occluded portion of the hole defined by a porous material located in a sub-portion of the outlet along the upstream side of the outlet to modify the momentum profile of the emitted cooling air flow passing through the porous material where the emitted cooling air flow from the porous material has an emerging velocity less than the cooling air flow emitted from the non-occluded portion.
A component for a turbine engine comprising:
- a wall separating a cooling airflow from a hot airflow having a first surface facing the cooling airflow and a second surface facing the hot airflow;
- at least one film hole extending through the wall and having an inlet located in the first surface and an outlet located in the second surface, a passage connecting the inlet and the outlet, with the passage having a non-occluded passage portion extending from the inlet to the outlet;
- and with one of the inlet and outlet having a non-occluded portion;
- and
- a porous material located within the hole forming a border of the non-occluded passage portion and at least partially defining a border of the non-occluded portion;
- wherein the passage comprises a passage centerline, the porous material comprises a body axis, and a passage cross section is different in shape than a porous material cross section when either one of:
- the passage cross section is perpendicular to the passage centerline at the same location in the hole as the porous material cross section;
- or
- the passage cross section is parallel to the passage centerline, the porous material cross section is parallel to the body axis, and the cross sections are in parallel planes.
Dependencies are inferred from the claim text.