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Ceramic matrix composite turbine engine vaneA vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a depth-wise coefficient of thermal expansion and a second coefficient of thermal expansion transverse thereto, the depth-wise coefficient of thermal expansion being greater than the second coefficient of thermal expansion.
Document ID
20120010615
Acquisition Source
Glenn Research Center
Document Type
Other - Patent
Authors
Prill, Lisa A.
Schaff, Jeffery R.
Shi, Jun
Date Acquired
August 26, 2013
Publication Date
June 26, 2012
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
Patent Number: US-Patent-8,206,098
Patent Application Number: US-Patent-Appl-SN-11/824,174
Funding Number(s)
CONTRACT_GRANT: NAS3-01138
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-8,206,098
Patent Application
US-Patent-Appl-SN-11/824,174

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