Extremely High Suction Performance Inducers for Space Propulsion

Advanced pump inducer design technology that uses high inlet diffusion blades, operates at a very low flow coefficient, and employs a cavitation control and stability device. A preliminary scoping inducer test with this technology indicated a doubling of the suction specific speed capability over current inducers. A three to four fold increase over current technology is the goal of this research effort. This increase would significantly enhance the capability of rocket engine systems through increased thrust-to-weight, specific impulse, simplicity, operational safety, and turbopump life. It would also reduce turbopump and propellant tank weight and system costs by eliminating boost pump systems and allowing for thinner lower pressure tank walls. Ultimately, the technology opens up the rocket engine/vehicle design space and allows for a large increase in vehicle performance by significantly moving the pump suction performance constraint from its current position.

The technology could be used for any situation where it is necessary to pump a low vapor pressure fluid. Nuclear reactor boiler feed pumps, vehicle fuel pumps, and cryogenic fluid transfer pumps are all potential commercial applications. In addition, the inducer suction performance predictive capability that will be validated and enhanced during this project will be incorporated into Concepts NREC's suite of commercially available turbomachinery design software tools.

The technology could be used as a retrofit onto current, in development, or future rocket engines for launch vehicle or in space propulsion that require high suction performance, high turbopump efficiency, and wide operating range. It is ideally suited for clean sheet engine designs where the full advantage of moving a key system constraint, pump suction performance, can be used to optimize the entire launch system. The technology could also be used for propellant ground handling systems and aircraft fuel pumps were fuel vaporization is an issue. Finally, the code validation work in the technology development will enhance the turbopump design tools used by NASA and improve the suction performance prediction capability.

This is early/mid-stage (TRL 3) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

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