Dual passage heat exchanger for reducing cold wall stress and method thereof
AssigneeRtx Corporation
InventorsCheng GAO, Andrew S. MILLER
Life of this patent
Estimating the term…
Abstract
A ceramic matrix composite (CMC) component of a gas turbine engine forming a portion of a substantially ring-shaped gas turbine engine stage includes an inner surface configured for exposure to a hot gas path of the gas turbine engine and an outer surface on a non-gas path side. The inner surface can be cooled with cold air fed to an inner heat exchange passage disposed adjacent the inner surface of the CMC component at a first radial distance relative to an axis of the gas turbine engine. Thermal stress at the cold outer surface can be reduced by feeding hot air to an outer heat exchange passage disposed adjacent the outer surface at a second radial distance greater than the first radial distance.
Claims20
A ceramic matrix composite (CMC) component of a gas turbine engine forming a portion of a substantially ring-shaped gas turbine engine stage, the CMC component comprising:
- an inner surface configured for exposure to a hot gas path of the gas turbine engine;
- an outer surface on a non-gas path side;
- an inner heat exchange passage disposed adjacent the inner surface of the CMC component at a first radial distance relative to an axis of the gas turbine engine;
- and
- an outer heat exchange passage disposed at a second radial distance greater than the first radial distance.
A ceramic matrix composite (CMC) blade outer air seal (BOAS) segment forming a portion of a substantially ring-shaped BOAS stage of a gas turbine engine, the CMC BOAS segment comprising:
- an inner surface configured for exposure to a hot gas path of the gas turbine engine;
- an outer surface on a non-gas path side;
- an inner heat exchange passage disposed adjacent the inner surface of the CMC BOAS segment at a first radial distance relative to an axis of the gas turbine engine;
- and
- an outer heat exchange passage disposed adjacent the outer surface of the CMC BOAS segment at a second radial distance greater than the first radial distance.
A method of reducing thermal stress in a ceramic matrix composite (CMC) component segment forming a portion of a substantially ring-shaped stage of a gas turbine engine, wherein the CMC component has an inner surface exposed to a hot gas path of the gas turbine engine and an outer surface on a cold non-gas path side, the method comprising:
- feeding a cold air flow to an inner heat exchange passage disposed adjacent the inner surface of the CMC component at a first radial distance relative to an axis of the gas turbine engine;
- and
- feeding a hot air flow to an outer heat exchange passage disposed adjacent the outer surface of the CMC component at a second radial distance greater than the first radial distance.
Dependencies are inferred from the claim text.