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US 9,790,859 B2Granted
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.
Claims17
A radial impeller for a gas turbine comprising:
- a vapor cooling passage in which a gaseous and liquid phase coolant flows, wherein the vapor cooling passage is along a neutral bending plane of the radial impeller with the neutral bending plane of the radial impeller passing through a longitudinal axis of a portion of the vapor cooling passage;
- an inner chamber in fluid communication with the vapor cooling passage through a plurality of slots formed along the neutral bending plane, wherein the inner chamber is radially inward of the vapor cooling passage so as to provide heat exchange between a gas turbine coolant and the inner chamber.
A gas turbine engine compressor section comprising:
- a radial impeller for a gas turbine comprising:
- a vapor cooling passage in which a gaseous and liquid phase coolant flows, wherein the vapor cooling passage is along a neutral bending plane of the radial impeller with the neutral bending plane of the radial impeller passing through a longitudinal axis of a portion of the vapor cooling passage;
- an inner chamber in fluid communication with the vapor cooling passage through a plurality of slots formed along the neutral bending plane, wherein the inner chamber is radially inward of the vapor cooling passage so as to provide heat exchange between a gas turbine coolant and the inner chamber.
Dependencies are inferred from the claim text.