A ROCKET ENGINE TURBOPUMP DESIGN USING A PARTIAL EMISSION PUMP COMBINED WITH A ZERO NET POSITIVE SUCTION PR…
Award details are derived from public USAspending.gov records. Not a bid recommendation.
Award details
- Award ID
- NNX08CD49P
- Contractor
- Awarding agency
- National Aeronautics and Space Administration
- Sub-agency / office
- National Aeronautics and Space Administration
- Award amount
- $0
- Period of performance
- Jan 18, 2008 – Jan 16, 2009
- NAICS
- 541712 — Research and Development in the Physical, Engineering, and Life Sciences
- PSC
- PSC AR11
- Place of performance
- CO
Public award description
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.
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