High Suction Specific Speed Inducers for Cryogenic Upper Stage Engines

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$99,939.00
Award Year:
2002
Program:
SBIR
Phase:
Phase I
Contract:
F04611-02-M-0029
Award Id:
57664
Agency Tracking Number:
021PRO-1949
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
217 Billings Farm Road, White River Jct, VT, 05001
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
024355802
Principal Investigator:
KerryOliphant
Principal Investigator
(802) 296-2321
kno@conceptsnrec.com
Business Contact:
KennethRosen
President
(802) 296-2321
kmr@coneptsnrec.com
Research Institute:
n/a
Abstract
"Pump inducer suction performance is directly linked to turbopump rotational speed and weight. It has become standard practice to use boost pumps to provide higher inlet pressure to main turbopumps. This allows for higher speed, lower weight, and moreefficient turbopumps. Propellant tank pressure is also minimized. However, the boost pumps add to the weight and complexity of the propellant management system. The proposer is developing advanced inducer technology using a test intensive approach withsupport from NASA and the NSF. The latest inducer technology allows for both lower inlet pressures and efficient pump operation without one or both boost pumps. The Phase I project is structured to demonstrate feasibility and to quantify the impact onthe engine performance, weight, reliability, and cost. Phase I begins with a pump and turbine scoping study for a selected engine cycle. Iterative engine cycle analyses will be used to judge the relative merits of conceptual LOX and LH2 turbpumps. Moredetailed preliminary pump and turbine design work and engine cycle studies will take place for the most highly rated configurations. During the Phase II SBIR project, inducer components will be designed and rig-tested for application in a Phase II IHPRPTdemonstrator. The most direct application high suction specific speed inducer technology and the engine cycle will be under a Phase II IHPRPT demonstration program. The developed pump t

* information listed above is at the time of submission.

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