Advanced Cooling Techniques for Hydrocarbon Liquid Rocket Engine Components

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-04-C-2512
Agency Tracking Number: O031-0080
Amount: $749,973.00
Phase: Phase II
Program: SBIR
Awards Year: 2004
Solicitation Year: 2003
Solicitation Topic Code: OSD03-009
Solicitation Number: 2003.2
Small Business Information
1802 N. Carson Street Suite 200, Carson City, NV, 89701
DUNS: 083152975
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Stuart Dunn
 Senior Research Engineer
 (775) 882-1966
Business Contact
 Douglas Coats
Title: President
Phone: (775) 882-1966
Research Institution
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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