COMPLIANT INTERMEDIATE COMPONENT OF A GAS TURBINE ENGINE
The present application provides an intermediate structure (130) in a gas turbine engine. The intermediate structure is positioned between a first component (120) and another component (110). The first component (120) may be a composite component. The components may be interlocking. The intermediate...
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Main Authors | , , |
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Format | Patent |
Language | English French |
Published |
25.02.2020
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Subjects | |
Online Access | Get full text |
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Summary: | The present application provides an intermediate structure (130) in a gas turbine engine. The intermediate structure is positioned between a first component (120) and another component (110). The first component (120) may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure (130). |
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Bibliography: | Application Number: CA20132897965 |