Turbopump Design for Deep Throttling Capability

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX08CD49P
Agency Tracking Number: 070083
Amount: $99,508.00
Phase: Phase I
Program: STTR
Awards Year: 2008
Solicitation Year: 2007
Solicitation Topic Code: T8.02
Solicitation Number: N/A
Small Business Information
6325 West 55th, Arvada, CO, 80002-2777
DUNS: 074072554
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Madhan Bala
 Principal Investigator
 () -
 madhanb@uah.edu
Business Contact
 Dave Kwiatkowski
Title: Business Official
Phone: (303) 421-8111
Email: 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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