NASA SBIR 2014 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 14-1 A3.07-9772
SUBTOPIC TITLE: Propulsion Efficiency-Propulsion Materials and Structures
PROPOSAL TITLE: Improved Attachment Design for Ceramic Turbine Blades Via Hybrid Concepts

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)
John Gayda
johngaydajr@yahoo.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)
Vinod K 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
Propulsion Efficiency-Propulsion Materials and Structures 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)
This proposal presents a hybrid metal-CMC turbine blade. A SiC/SiC CMC airfoil section will be bonded to a single crystal superalloy root section in order to mitigate risks associated with an all-CMC blade inserted in a superalloy disk. This allows current blade attachment technology (SX blade with a dovetail attachment to a slotted Ni disk) to be used with a ceramic airfoil. The bond between the CMC and single crystal will be primarily mechanical in nature, and enhanced with clamping arising from thermal expansion mismatch. Two single crystal root sections will be bonded to each other using diffusion bonding and/or transient liquid phase bonding at temperatures near 2200 0F. The single crystals will form a clam shell around the CMC, with little or no gap between the metal and ceramic. Upon cooling, the metal will shrink around the CMC spar to firmly clamp it. Single crystals will resist stress relaxation at an operating temperature of 1500 0F, thus maintaining clamping loads for long lives. The use of an inter layer ("compliant layer") between the CMC and the single crystal may also be entertained. 1500 0F is a reasonable upper limit for chemical reactivity issues between the metal and ceramic.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The potential post application is a technology for reliably inserting ceramic matrix composite blades into high temperature nickel alloy disks. The results of this work are an enabling technology for meeting future goals of achieving SFC gains. Since incorporating CMC materials into turbo engine designs permit higher operating temperatures.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The potential post application is a technology for reliably inserting ceramic matrix composite blades into high temperature nickel alloy disks. The results of this work are an enabling technology for meeting future goals of achieving SFC gains. Since incorporating CMC materials into turbo engine designs permit higher operating temperatures.

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.)
Analytical Methods
Ceramics
Joining (Adhesion, Welding)
Metallics

Form Generated on 04-23-14 17:37