SBIR/STTR Research Award

Turbopump Design for Deep Throttling Capability

Award identifier 506866dd2f76b6b81d5e87ef9fe9232fe5af8cb2ee0d67e2a4aa8f416ed849d6Awarding agency National Aeronautics and Space Administration

Award amount

$99,508

Program and phase

STTR · Phase I

Award year

2008

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Award details

Awarding agency
National Aeronautics and Space Administration
Branch
Not reported
Recipient company
Barber-Nichols, LLC
Proposal award date
2008-01-18
Contract end date
2009-01-16
UEI
K4GJKMQD4961
Solicitation number
Not reported
Topic code
T8.02

Research 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.

Technology keywords

Not reported

Other awards by this recipient

Verified by the same UEI. These are other public SBIR/STTR award pages, not a merged company record.

Awards with the same topic code

Verified by an exact topic code match. This is not a text-similarity match.

Research funding history

27 SBIR/STTR records share this UEI (1990–2020). Reported award amounts total $5,470,502. Reported amounts are not federal obligations.

Phases: Phase I, Phase II

Agencies: National Aeronautics and Space Administration, Department of Defense, Department of Energy

Agency intelligence

National Aeronautics and Space Administration

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