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US 2015/0308274 A1Published application
Engine component with wear surface protection
AssigneeUnited Technologies Corporation
InventorsGraham Ryan Philbrick, Ken Lagueux, Bret M. Teller
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component according to an exemplary aspect of this disclosure includes a peripheral portion defining an internal cooling passage and a recess in fluid communication with the internal cooling passage. The peripheral portion includes an outer wear surface, and the recess tapers toward the outer wear surface.
Claims18
A gas turbine engine component, comprising:
- a peripheral portion defining an internal cooling passage and a recess in fluid communication with the internal cooling passage, the peripheral portion including an outer wear surface, wherein the recess tapers toward the outer wear surface.
A gas turbine engine component, comprising:
- a structure having a peripheral outer surface and defining an internal cooling passage and a recess in fluid communication with the internal cooling passage, wherein the peripheral outer surface includes a wear surface configured to (1) cover the recess in a first condition and (2) to uncover the recess in a second condition, wherein the internal cooling passage is fluidly coupled to a region outside the structure via the recess in the second condition.
An assembly for a gas turbine engine, the assembly comprising:
- an abradable component;
- and
- an abrasive component adjacent the abradable component, the abrasive component having a wear surface and configured to move relative to the abradable component during operation of the engine, the abrasive component including an internal cooling passage and a recess in fluid communication with the internal cooling passage, wherein the recess is tapered toward the wear surface of the abrasive component.
Dependencies are inferred from the claim text.