Turbopump Design for Deep Throttling Capability

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,508.00
Award Year:
2008
Program:
STTR
Phase:
Phase I
Contract:
NNX08CD49P
Agency Tracking Number:
070083
Solicitation Year:
2007
Solicitation Topic Code:
T8.02
Solicitation Number:
n/a
Small Business Information
Barber-Nichols, Inc.
6325 West 55th, Arvada, CO, 80002-2777
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
074072554
Principal Investigator:
Madhan Bala
Principal Investigator
() -
madhanb@uah.edu
Business Contact:
Dave Kwiatkowski
Business Official
(303) 421-8111
davidk@barber-nichols.com
Research Institution:
University of Alabama, Huntsville
Not Available
301 Sparkman Drive
Huntsville, AL, 35899
(256) 824-6000
Domestic nonprofit research organization
Abstract
A rocket engine turbopump design using a partial emission pump combined with a zero net positive suction pressure inducer design is proposed to achieve a robust, deep throttling capability in 5k to 15k lbf thrust range rocket engines. A partial emission pump can provide better low-flow/thrust stability at a better efficiency than full emission pumps in this throttle range. A zero net positive suction pressure inducer will be able to perform with boiling flow at the inlet and at low flow conditions. This will enable deep throttling as well as restarts with minimal turbopump/engine thermal conditioning.

* information listed above is at the time of submission.

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