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SBIR/STTR

Turbopump Design for Deep Throttling Capability, Phase I

Completed Technology Project

Project Introduction

Turbopump Design for Deep Throttling Capability, Phase I
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. More »

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This is a historic project that was completed before the creation of TechPort on October 1, 2012. Available data has been included. This record may contain less data than currently active projects.

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