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US 9,957,813 B2Granted
Gas turbine engine airfoil platform cooling passage and core
AssigneeUnited Technologies Corporation
InventorBrandon W. Spangler
Life of this patent
Estimating the term…
Abstract
A gas turbine engine blade includes a platform arranged between a root and an airfoil. A cooling passage extends from the root through the platform to the airfoil. The cooling passage includes an inlet that splits into first and second branches that rejoin one another in a platform passage arranged in the platform. An airfoil passage extends from the platform passage and is arranged in the platform.
Claims16
A gas turbine engine blade comprising:
- a platform arranged between a root and an airfoil, a cooling passage extending from the root through the platform to the airfoil, the cooling passage including an inlet splitting into first and second branches that rejoin one another in a platform passage arranged in the platform, and an airfoil passage extending from the platform passage and arranged in the platform.
A core for forming a cooling passage in a gas turbine engine blade, comprising:
- an inlet passage core portion splitting into first and second branch core portions that rejoin one another in a platform passage core portion, and an airfoil passage core portion extending from the platform passage core portion, the first and second branch core portions and the platform passage core portion are arranged in a triangular shape providing an aperture.
Dependencies are inferred from the claim text.