Gas turbine engine airfoil cooling circuit
AssigneeUnited Technologies Corporation
InventorsTracy A. Propheter-Hinckley, Rafael A. Perez, Edward F. Pietraszkiewicz
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Abstract
An airfoil for a gas turbine engine includes an airfoil body and a cooling circuit defined within the airfoil body. The cooling circuit includes at least a first cavity in fluid communication with a second cavity. A first portion of the first cavity extends between an outer diameter and an inner diameter of the airfoil body and a second portion of the first cavity extends across a space between a leading edge and a trailing edge of the airfoil body.
Claims20
An airfoil for a gas turbine engine, comprising:
- an airfoil body;
- and
- a cooling circuit defined within said airfoil body, wherein said cooling circuit includes at least a first cavity in fluid communication with a second cavity, wherein a first portion of said first cavity extends between an outer diameter and an inner diameter of said airfoil body and a second portion of said first cavity extends across a space that extends between a leading edge toward a trailing edge of said airfoil body.
A gas turbine engine, comprising:
- a compressor section, a combustor section and a turbine section disposed about an engine centerline axis;
- an airfoil disposed in at least one of said compressor section and said turbine section, wherein said airfoil includes an airfoil body having a trailing edge that establishes a first length;
- and
- a cooling circuit disposed within said airfoil body and having a trailing edge cavity adjacent to said trailing edge that is in fluid communication with at least one other cavity of said cooling circuit, wherein said trailing edge cavity extends across a second length associated with said airfoil body that is less than said first length.
A method for cooling an airfoil of a gas turbine engine, comprising the steps of:
- directing an airflow through a first cavity disposed between an outer diameter and an inner diameter of the airfoil;
- and
- prior to communicating the airflow to a second cavity of the airfoil, communicating the airflow from a leading edge to a trailing edge of the airfoil within the first cavity.
Dependencies are inferred from the claim text.