Ultrahigh Temperature Oxidation-Resistant Ceramic Matrix Composite for Rocket Propulsion Components

Award Information
Agency:
Department of Defense
Amount:
$99,996.00
Program:
SBIR
Contract:
F04611-02-M-0060
Solitcitation Year:
N/A
Solicitation Number:
N/A
Branch:
Air Force
Award Year:
2002
Phase:
Phase I
Agency Tracking Number:
021PRO-2501
Solicitation Topic Code:
N/A
Small Business Information
Ultramet
12173 Montague Street, Pacoima, CA, 91331
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
052405867
Principal Investigator
 Jerry Brockmeyer
 Director of Engineering
 (818) 899-0236
 jerry.brockmeyer@ultramet.com
Business Contact
 Craig Ward
Title: Engineering Admin. Mgr.
Phone: (818) 899-0236
Email: craig.ward@ultramet.com
Research Institution
N/A
Abstract
"Future Air Force space, missile, and aircraft systems require advanced high temperature materials to meet projected performance requirements. Rocket engine and turbine engine programs such as the IHPRPT and IHPTET initiatives, respectively, are intendedto double next-generation propulsion capabilities. Reaching this aggressive goal demands the implementation of high temperature capability, environmentally resistant, lightweight material systems. Prominent among the alternative materials underconsideration for such applications are ceramic matrix composites (CMCs). Recent Air Force and NASA programs have considerably progressed the development of CMCs for ~2500¿F combustion environments, but additional work is required to extend current CMCcapabilities to temperatures of 3500¿F. In this project, Ultramet proposes to demonstrate the feasibility of fabricating and using an ultrahigh temperature capable CMC using a hafnium carbide/silicon carbide (HfC/SiC) matrix analogous to Ultramet'sUltra2000TM microlayered HfC/SiC coating system that has previously been shown to be effective for high temperature oxidation protection of carbon/carbon (C/C) and CMCs. Specifically, several innovative variants of chemical vapor deposition (CVD)processing will be evaluated as potential methods for densifying HfC/SiC matrix CMCs, and the resultant structures will be characterized for potential aerospace applications as a demonstration of feasibility.

* information listed above is at the time of submission.

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