Advanced Cooling Techniques for Hydrocarbon Liquid Rocket Engine Components

Award Information
Agency:
Department of Defense
Branch
Office of the Secretary of Defense
Amount:
$749,973.00
Award Year:
2004
Program:
SBIR
Phase:
Phase II
Contract:
FA8650-04-C-2512
Award Id:
66798
Agency Tracking Number:
O031-0080
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
1802 N. Carson Street Suite 200, Carson City, NV, 89701
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
083152975
Principal Investigator:
Stuart Dunn
Senior Research Engineer
(775) 882-1966
stu@seainc.com
Business Contact:
Douglas Coats
President
(775) 882-1966
doug@seainc.com
Research Institution:
n/a
Abstract
Liquid rocket engines may be run for repeatedly over extended periods of time, requiring active cooling. An efficient means of cooling LRE nozzles involves using the liquid fuel or oxidizer itself to provide the cooling, often referred to as regenerative cooling. SEA's liquid rocket combustion chamber and nozzle design code, TDK, can predict the heat transfer to the surface of the nozzle as a function of the nozzle geometry and fuel / oxidizer properties. The standard RTE code predicts the amount of cooling produced by a regenerative cooling system, given the heat transfer to the cooling fluid. In this research effort, we are combining the two codes, so they may iteratively determine the optimal cooling design. In addition, we are extending the capabilities of TDK and RTE to evaluate novel nozzle designs and cooling concepts.

* information listed above is at the time of submission.

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