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Nasa Hytec CMC Turbine Blade Durability The objective of the CMC turbine blade durability program is to identify critical material and design parameters that affect durability of ceramic matrix composite (CMC) turbine blades. A baseline architecture for a cooled high-pressure turbine (HPT) CMC blade and accompanying sub-component test articles were developed with the intent to demonstrate through analysis and subcomponent testing how material and design parameters impact key failure modes.

As part of this program, a notional architecture for a cooled CMC blade was matured through a design review rhythm to produce a blade test article containing the necessary features required for operation in an engine like environment. Further validation of the durability of these features were achieved through coupon and sub-component testing to demonstrate the durability of cooling hole configurations and blade attachment designs.

Analytical methods were also used to evaluate the acceptability of the baseline blade test article architecture against relevant design requirements and identify abatement and recommended changes to key design drivers to improve component durability for future design iterations.
Document ID
Acquisition Source
Glenn Research Center
Document Type
Contractor or Grantee Report
Dane Dale
(GE Aerospace )
Alex Ruschau
(GE Aerospace)
Date Acquired
May 24, 2023
Publication Date
June 1, 2023
Subject Category
Composite Materials
Funding Number(s)
WBS: 698154.05.03.04
Distribution Limits
Use by or on behalf of the US Gov. Permitted.
Technical Review
NASA Peer Committee
CMC, Blade
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