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US 2015/0308342 A1Published application
Gas turbine engine vapor cooled centrifugal impeller
AssigneeUnited Technologies Corporation
InventorJames W. Norris
Life of this patent
Estimating the term…
Abstract
A gas turbine engine radial impeller includes first and second impeller portions that are secured to one another along a neutral bending plane of the radial impeller. A vapor cooling cavity is provided between the first and second impeller portions. The neutral bending plane is arranged in the vapor cooling cavity.
Claims20
A gas turbine engine radial impeller comprising:
- first and second impeller portions secured to one another along a neutral bending plane of the radial impeller, and a vapor cooling cavity provided between the first and second impeller portions, the neutral bending plane arranged in the vapor cooling cavity.
A gas turbine engine compressor section comprising:
- a radial impeller mounted to a shaft, the radial impeller includes a vapor cooling cavity having inner and outer chambers fluidly connected by a passageway, the inner chamber arranged at an inner diameter of the radial impeller, the inner diameter in fluid communication with a cooling flow path within the shaft.
Dependencies are inferred from the claim text.