NASA STTR 2009 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 09-1 T9.01-9927
RESEARCH SUBTOPIC TITLE: Technologies for Human and Robotic Space Exploration Propulsion Design and Manufacturing
PROPOSAL TITLE: Extremely High Suction Performance Inducers for Space Propulsion

SMALL BUSINESS CONCERN (SBC): RESEARCH INSTITUTION (RI):
NAME: Concepts ETI, Inc. NAME: Brigham Young University
STREET: 217 Billings Farm Road STREET: 435 Crabtree Building
CITY: White River Jct CITY: Provo
STATE/ZIP: VT  05001 - 9486 STATE/ZIP: UT  84602 - 0002
PHONE: (802) 280-6170 PHONE: (801) 422-2625

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Kerry N Oliphant
kno@conceptsnrec.com

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 1
End: 3

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
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.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
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.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
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.

NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Feed System Components
Fluid Storage and Handling
Launch and Flight Vehicle
Propellant Storage
Simulation Modeling Environment
Tankage


Form Generated on 09-18-09 10:14