Lightweight Ultrahigh Temperature CMC-Lined C/C Combustion Chambers, Phase II

Award Information
Agency:
National Aeronautics and Space Administration
Branch:
N/A
Amount:
$600,000.00
Award Year:
2007
Program:
SBIR
Phase:
Phase II
Contract:
NNC07CA19C
Agency Tracking Number:
054694
Solicitation Year:
2005
Solicitation Topic Code:
X2.01
Solicitation Number:
N/A
Small Business Information
Ultramet
12173 Montague Street, Pacoima, CA, 91331-2210
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
052405867
Principal Investigator
 Gautham Ramachandran
 Principal Investigator
 (818) 899-0236
 gautham.ramachandran@ultramet.com
Business Contact
 Craig Ward
Title: Engineering Administrative Mgr
Phone: (818) 899-0236
Email: craig.ward@ultramet.com
Research Institution
N/A
Abstract
NASA and DoD are seeking high-performance, lightweight liquid rocket combustion chambers with future performance goals that cannot be achieved using state-of-the-art actively cooled metallic liners, silicided C103, or even carbon fiber-reinforced silicon carbide (C/SiC) ceramic matrix composites (CMC). Ultramet has previously developed and successfully demonstrated carbon fiber-reinforced zirconium carbide (C/ZrC) and zirconium-silicon carbide (C/Zr-Si-C) matrix CMCs for use in liquid propellant applications up to 4200oF. In Phase I, Ultramet demonstrated the feasibility of combining the light weight of C/C with the oxidation resistance of ZrC and Zr-Si-C matrix composites in a unique system composed of a C/C primary structure with an integral CMC liner. The system effectively bridges the gap in weight and performance between coated C/C and bulk CMCs. Rapid fabrication was demonstrated through an innovative variant of Ultramet's melt infiltration refractory composite processing technology. In Phase II, Ultramet will team with ATK-GASL for process optimization, component fabrication, and comprehensive testing of lightweight, high-strength, elevated temperature oxidation-resistant liquid rocket combustion chambers. The fully developed system will have strength that is comparable to that of C/C, low density comparable to that of C/SiC, and ultrahigh temperature (>4000oF) oxidation stability.

* information listed above is at the time of submission.

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