Advanced Materials and Cooling Schemes for Rocket Engine Combustion Chambers

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$0.00
Award Year:
2001
Program:
SBIR
Phase:
Phase I
Contract:
F04611-01-C-0047
Agency Tracking Number:
001PR-2782
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
SIERRA ENGINEERING, INC.
603 E. Robinson Street,Suite 7, Carson City, NV, 89701
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
006620553
Principal Investigator:
Jeffery Muss, PhD
Principal Investigator
(916) 447-6064
jamuss@pacbell.net
Business Contact:
Curtis Johnson
President
(775) 885-0139
curtis@johnsonrockets.com
Research Institution:
n/a
Abstract
We will produce and test a flight-type transpiration cooled combustion chamber for high performance, reusable, liquid rocket engines utilizing a novel uniform pore material. The Sierra Engineering design produces a durable, low cost, flight-weighttranspiration cooled liner with integral fluid distribution and structural support hardware. The design will be based upon the rigorous analysis procedure and associated methodology developed under the Phase I project. The Phase I effort also fabricateda transporation cooled combustion chamber barrel segment and applied the design methodology and fabrication technique to a chamber concept for an NK-33 class hydrocarbon booster engine. The Phase II SBIR program shall: l)generate the data necessary toevaluate and improve the design methodology for a wide range of transpiration coolants, 2) demonstrate scale-up of the fabrication techniques from a heavy-weight research scale to a relevant flight-type booster class engine, and 3) produce a commerciallyviable 40 Klbf-class combustion chamber. Transpiration cooled combustion chamber technology has been demonstrated by others at a concept level, but flight weight hardware has never been developed.

* information listed above is at the time of submission.

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