Trenched cooling hole arrangement for a ceramic matrix composite vane
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc.
InventorsJack K. Moody, Richard C. Uskert, Adam L. Chamberlain, David J. Thomas
Life of this patent
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Abstract
One aspect of the present application provides an apparatus comprising a shape operable as a gas turbine engine component, an internal cavity within the shape including a radius, a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity, and a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component.
Claims20
An apparatus comprising:
- a shape operable as a gas turbine engine component;
- an internal cavity within the shape including a radius;
- a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity;
- and
- a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench,
- wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component.
An apparatus comprising:
- a component having an airfoil shape with an external flow surface and a trailing edge portion, the component structured to be exposed to high temperature fluid flow;
- an internal cavity for receiving cooling fluid disposed within the component, the internal cavity defined by an aft-most region adjacent the trailing edge portion that includes a surface having a radius of curvature;
- at least one trench formed proximate an external portion of the trailing edge portion of the component, the at least one trench having a rear wall disposed at an angle to the external flow surface, and opposing lateral walls extending downstream from the rear wall of the at least one trench;
- and
- at least one cooling hole extending from the internal cavity through the rear wall of the at least one trench.
A method comprising:
- constructing a gas turbine engine component having an airfoil shape that includes a trailing edge and an internal cavity which is proximate the trailing edge;
- shaping a trench on an external surface proximate the trailing edge of the airfoil shape including a trench face tangential to an arc centered on a radius of an aft region of the internal cavity;
- and
- forming a cooling hole extending from the internal cavity to the trench face.
Dependencies are inferred from the claim text.