Description: The proposed work will develop a reliability analysis tool consistent with conceptual-level design for ceramic matrix composite (CMC) turbine blades and vanes. The analysis software will comprise a suite of physics-based discipline specific analysis code modules and NASA's Fast Probability Integrator (FPI). The objective of this analysis tool is to develop optimal material properties, internal and external geometries for a cooled vane/blade using aerothermal, and structural (including creep) analyses. Structural constraints in the form of allowable mechanical/thermal stresses and material constraints in the form of minimum wall thickness and minimum bend radius will be applied. The structural stress analysis will be augmented with a creep module to determine an estimate for part life. The suggested benchmark system problem is a multi-disciplinary analysis of a NASA C3X turbine vane, 2 or 3D versions of the discipline specific models will be taken from the open literature and implemented as plug-in modules for NASA's Open MDAO framework. It is not the intention of this program to develop new MDAO architectures, rather the optimization drivers built into Open MDAO will be used.

Benefits: The NASA Aeronautics Research Mission Directorate has programs and projects regarding subsonic aviation and with goals of improved efficiency, emissions and noise are potential consumers of this effort from a technology development standpoint. Specifically, the development of a reliability analysis tool consistent with conceptual-level design for ceramic matrix composite turbine blades and vanes will facilitate the aforementioned NASA goal.

A ceramic matrix composite blade leads to gains in specific fuel consumption by allowing higher operating temperatures, reductions in required cooling, and reductions in vehicle weight. A reliability analysis tool for CMC turbine blades has a high probability of being implemented by aero-turbine gas engine manufactures, such as GE Aviation, Pratt &Whitney, Rolls-Royce and Honeywell.