INTERNALLY COOLED TURBINE PLATFORM
A turbine flowpath component (100) for a gas turbine engine (20) includes a platform (102) defining at least one internal cooling cavity (140) and a turbine flowpath component cover (120) disposed radially outward of the platform (102). The turbine flowpath component cover (120) defines a radially o...
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Main Author | |
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Format | Patent |
Language | English French German |
Published |
25.05.2016
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Subjects | |
Online Access | Get full text |
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