Component for a gas turbine engine
A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a seco...
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Main Authors | , , |
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Format | Patent |
Language | English |
Published |
03.03.2020
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Subjects | |
Online Access | Get full text |
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Summary: | A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component. |
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Bibliography: | Application Number: US201615182651 |