Cooled highly twisted airfoil for a gas turbine engine
This patent describes a cooled highly twisted airfoil for use in a gas turbine engine. The airfoil has a first cooling air cavity adjacent a leading edge of the airfoil, and a second cooling air cavity, separated from the first cavity by a wall. The second cavity provides cooling air to the first cavity by means of cooling holes provided in the wall. The improvement is characterized by: the wall comprising an integrally formed, continuous warped wall, defined as a surface of revolution about an axis, the axis determined such that the axis intersects the plane of a section close to a desired centerline of a series of impingement holes aligned in opposition to the leading edge, whereby cooling air is directed relatively precisely to the leading edge of the highly twisted airfoil through the impingement holes.
- Assignee:
- United Technologies Corp., Hartford, CT
- Patent Number(s):
- US 4738587
- OSTI ID:
- 7007010
- Resource Relation:
- Patent File Date: Filed date 22 Dec 1986
- Country of Publication:
- United States
- Language:
- English
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