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Space Shuttle Main Engine Oxidizer Jet Pump (SSME OJP)

Problem: Current Low Pressure Oxidizer Turbopump (LPOTP) is life limited and requires checkouts and maintenance. The design has complex rotating features with 9 critical FMEA failure modes identified.
Solution: Upgrade design to a jet pump configuration that utilizes hydrodynamic momentum exchange (instead of the traditional mechanical pumping) to boost propellant pressure. Elimination of rotating elements vastly simplify the component fabrication, reduce cost, eliminate maintenance and reduce over half the failure modes.
Initial Operation Date: Date-TBD
Mission-TBD
Phase III
Technology Goal: Industry data application currently do not envelop the expected operating range for the SSME. To demonstrate feasibility, confidence in the design momentum exchange codes must be validated at the SSME flow and pressure regions. Sufficient jet pump performance is a necessary prerequisite for go-head into full scale system integration and development. The acquired technology will compliment the existing database of validated design codes for future propulsion systems (i.e. LFBB).
Goals Supported: 1) Fly Safely
2) Meet the Manifest
3) Improve Supportability
4) Reduce Cost
5) Support HEDS


Curator: Kim Dismukes | Responsible NASA Official: John Ira Petty | Updated: 04/07/2002
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