Advanced Injector Designs for Hydrocarbon Liquid Rocket Engine Components

Award Information
Agency:
Department of Defense
Branch
Office of the Secretary of Defense
Amount:
$749,986.00
Award Year:
2004
Program:
SBIR
Phase:
Phase II
Contract:
FA8650-04-C-2513
Award Id:
66807
Agency Tracking Number:
O031-0163
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
603 East Robinson Street Suite 7, Carson City, NV, 89701
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
006620553
Principal Investigator:
JeffreyMuss
Senior Engineer
(916) 363-6161
jmuss@sierraengineering.com
Business Contact:
CurtisJohnson
President
(775) 885-0139
cwj@sierraengineering.com
Research Institute:
n/a
Abstract
Combustion instability is one of the greatest development risks for liquid propellant engines. In developing a stable injector design, the risks arise from a variety of sources - limited modeling capabilities, poor scalability and the high cost of appropriate component test facilities. Sierra Engineering Inc. believes that much of the empirical data on the injection element's driving characteristics can be obtained using a single full-sized injection element in combustion chamber of the same diameter as the full-scale chamber. Our proposed Phase II validation effort covers the critical design, fabrication and testing of a single-element stability tester. Test data, generated in relevant operating environments, will be used to anchor stability model inputs, thereby limiting extrapolation while applying the models to large-scale engines.

* information listed above is at the time of submission.

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