N&R ENGNERING MGT SUPPORT SVCS — National Aeronautics and Space Administration SBIR Phase I: A1.05

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.