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US 2019/0316474 A1Published application
Cupped contour for gas turbine engine blade assembly
AssigneeUnited Technologies Corporation
InventorsDipanjan Saha, Brooks E. Snyder, Thomas N. Slavens
Life of this patent
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Abstract
A gas turbine engine assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed.
Claims20
A gas turbine engine assembly, comprising:
- an endwall having a first material composition, wherein an airfoil extends in a radial direction from the endwall;
- and
- a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition.
A gas turbine engine blade assembly, comprising:
- an endwall with a plurality of cooling channels;
- an airfoil extending radially from the endwall to a tip;
- and
- a cupped contour formed on the endwall to provide a cooling chamber between the cupped contour and a radially facing surface of the endwall.
1 more element
Dependencies are inferred from the claim text.