Turbopump Design for Deep Throttling Capability

Period of Performance: 01/01/2008 - 12/31/2008

$99.5K

Phase 1 STTR

Recipient Firm

Barber-nichols, Inc.
6325 West 55th
Arvada, CO 80002
Principal Investigator
Firm POC

Research Institution

University of Alabama, Huntsville
301 Sparkman Drive
Huntsville, AL 35899

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.