Extremely High Suction Performance Inducers for Space Propulsion

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$100,000.00
Award Year:
2010
Program:
STTR
Phase:
Phase I
Contract:
NNX10CF78P
Agency Tracking Number:
090073
Solicitation Year:
2009
Solicitation Topic Code:
T9.01
Solicitation Number:
n/a
Small Business Information
Concepts ETI, Inc.
217 Billings Farm Road, White River Jct, VT, 05001-9486
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
024355802
Principal Investigator:
Kerry Oliphant
Principal Investigator
() -
kno@conceptsnrec.com
Business Contact:
Robert Hewett
Business Official
(802) 280-6170
rdh@conceptsnrec.com
Research Institution:
Brigham Young University
Not Available
435 Crabtree Building
Provo, UT, 84602
(801) 422-2625
Domestic nonprofit research organization
Abstract
Advanced pump inducer design technology that uses high inlet diffusion blades, operates at a very low flow coefficient, and employs a cavitation control and stability device. A preliminary scoping inducer test with this technology indicated a doubling of the suction specific speed capability over current inducers. A three to four fold increase over current technology is the goal of this research effort. This increase would significantly enhance the capability of rocket engine systems through increased thrust-to-weight, specific impulse, simplicity, operational safety, and turbopump life. It would also reduce turbopump and propellant tank weight and system costs by eliminating boost pump systems and allowing for thinner lower pressure tank walls. Ultimately, the technology opens up the rocket engine/vehicle design space and allows for a large increase in vehicle performance by significantly moving the pump suction performance constraint from its current position.

* information listed above is at the time of submission.

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