High Performance Cooling Methods for Liquid Rocket Engines

Award Information
Agency:
Department of Defense
Branch
n/a
Amount:
$739,572.00
Award Year:
2013
Program:
SBIR
Phase:
Phase II
Contract:
FA9300-13-C-2013
Award Id:
n/a
Agency Tracking Number:
F112-178-2225
Solicitation Year:
2011
Solicitation Topic Code:
AF112-178
Solicitation Number:
2011.2
Small Business Information
530 New Los Angeles Avenue, Suite115, # 122, Moorpark, CA, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
Y
Duns:
172773272
Principal Investigator:
Tedi Ohanian
CEO/Chief Technical Offic
(805) 529-3800
tedi.ohanian@sci-tech-apps.com
Business Contact:
Lisa Ohanian
Owner/CFO
(805) 529-3800
lisa.ohanian@sci-tech-apps.com
Research Institution:
Stub




Abstract
ABSTRACT: To meet the goals for future generation Air Force LOX/Hydrocarbon booster engines, improvements must be made in performance, operability, reusability, reliability, and cost. To date, operational LOX/hydrocarbon engines have used the fuel as the thrust chamber assembly (TCA) regenerative coolant, and have used fuel film cooling (FFC) as the TCA hot gas wall thermal barrier. The present hydrocarbon fuels show increasing coking behavior at high chamber pressures (Pc) and heat loads and have forced the development of highly refined propellants e.g. RP-2. An alternate path to the fuel cooling road-block is proposed by incorporating LOX regenerative cooling and oxidizer film cooling (OFC). This combination provides greater robustness and safety, and completely de-couples fuel characteristics from the thermally stresses components. Additionally, this cooling method enables the use of military/aviation grade kerosene. BENEFIT: The development of this technology will enable the full-scale development of a high Pc LOX/HC engine to meet the requirements of future military and commercial spacelift systems. The technology is applicable to Air Force Reusable Booster System program and can be adopted to commercial or government RLV and expendable launch vehicles.

* information listed above is at the time of submission.

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