SBIR/STTR
Inlet Cover Treatment to Enhance Zero NPSH Inducer Operation, Phase I
Project Introduction
Zero net positive suction head (NPSH)-capable hydrogen pump inducers are a critical component needed to lower the cost and increase the effectiveness of Nuclear Thermal Propulsion (NTP) engines. Zero NPSH pumps need to be able to pump up to 55% vapor fraction by volume without significant head fall-off. Current technology inducers can pump liquid hydrogen up to a limit of about 25% vapor fraction by volume because of choking of the vapor in either the inlet pipe or the inducer blade passage. It is proposed that the Concepts NREC (CN) inlet cover treatment cavitation and stability control device (SCD) will be able to increase the hydrogen vapor volume pumping fraction to the required 55%. The device allows the inducer to operate stably at high blade angles and low flow coefficients which increases the blade passage and the inlet pipe area to delay choking of the pumped fluid.
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Anticipated Benefits
Potential NASA Commercial Applications: Nuclear Thermal Propulsion (NTP) hydrogen two-phase pump and chemical rocket pumps for any fluid that exhibits some level of thermal suppression head benefit like hydrogen or oxygen.
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
Marshall Space Flight Center
(MSFC)
|
Lead Organization | NASA Center | Huntsville, AL |
| Concepts ETI, Inc. | Supporting Organization | Industry | White River Junction, VT |
Primary U.S. Work Locations
-
Alabama
-
Vermont
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Organizational Responsibility
Responsible Mission Directorate:
- Space Technology Mission Directorate (STMD)
Lead Center / Facility:
- Marshall Space Flight Center (MSFC)
Responsible Program:
- SBIR/STTR
Project Management
Program Director:
Program Manager:
Project Manager:
Principal Investigator:
- Kerry Oliphant
Project Duration
Start: Jun 2014
End: Dec 2014
Technology Maturity (TRL)
| Start: | 2 |
| Current: | 2 |
| Estimated End: | 2 |
Applied Research
Development
Demo & Test
Technology Areas
Primary:
- TA 2 In-Space Propulsion Technologies
- TA 2.2 Non-Chemical Propulsion
- TA 2.2.3 Thermal Propulsion