NASA SBIR 2015 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 15-1 A1.05-9471
SUBTOPIC TITLE: Physics-Based Conceptual Aeronautics Design Tools
PROPOSAL TITLE: Physics-based MDAO tool for CMC blades and vanes conceptual design

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
N&R Engineering
6659 Pearl Road, #201
Parma Heights, OH 44130 - 3821
(440) 845-7020

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Ian T Miller
imiller@nrengineering.com
6659 Pearl Road, #201
Parma Heights, OH 44130 - 3821
(440) 845-7020

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Vinod Nagpal
vnagpal@nrengineering.com
6659 Pearl Road, #201
Parma Heights, OH 44130 - 3821
(440) 845-7020

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 3

Technology Available (TAV) Subtopics
Physics-Based Conceptual Aeronautics Design Tools is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
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.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
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.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
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.

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Aerodynamics
Analytical Methods
Ceramics
Composites
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)

Form Generated on 04-23-15 15:37