Injector Stability Screening Technique (ISST)

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9300-11-C-3010
Agency Tracking Number: F083-112-0551
Amount: $746,528.00
Phase: Phase II
Program: SBIR
Awards Year: 2011
Solicitation Year: 2008
Solicitation Topic Code: AF083-112
Solicitation Number: 2008.3
Small Business Information
Space Center, 1212 Fourier Drive, Madison, WI, -
DUNS: 196894869
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Ryan Cavitt
 Propulsion Engineer
 (608) 229-2801
Business Contact
 Eric Rice
Title: CEO
Phone: (608) 229-2730
Research Institution
ABSTRACT: ORBITEC proposes to demonstrate and validate a laboratory-scale experimental injector stability screening technique which will quantify injector element stability characteristics. The experimental approach promises to dramatically reduce development cost by utilizing a gaseous single element test facility which presents savings in hardware manufacturing, consumables, and test facility labor. The simple test facility will allow rapid stability characterization of multiple candidate injectors which will be unobtrusive to schedule requirements. The key cost and time savings will be fewer full-scale hardware configurations that must be manufactured which will in turn reduce the number of full-scale tests required for qualification. The Phase I effort evaluated a Russian pentad injector at full-scale and laboratory-scale conditions. Correlation between laboratory scale and full scale experimental data showed that both combustion devices operated without experiencing high frequency combustion instability. During Phase II, an available database for the injector will be utilized to ensure unstable operation which will be scaled up for engine testing. Laboratory-scale methods of providing similarity such as heating and reactant dilution will also be evaluated. The Phase II programs will set the necessary scaling requirements and produce plans for Phase III ORBITEC test facility implementation. BENEFIT: The end product of this overall research and validation effort will create an experimental test facility and scaling technique which will significantly decrease engine development time at a reduced cost. The scaling technique will have application to virtually all high pressure liquid rocket engine development programs and existing engine upgrades for the Air Force, Navy, MDA, NASA and their contractors as well as commercial satellite launch companies. Development may reveal application to the screech phenomenon in air-breathing engines which will significantly open the commercial aircraft sector.

* Information listed above is at the time of submission. *

Agency Micro-sites

SBA logo
Department of Agriculture logo
Department of Commerce logo
Department of Defense logo
Department of Education logo
Department of Energy logo
Department of Health and Human Services logo
Department of Homeland Security logo
Department of Transportation logo
Environmental Protection Agency logo
National Aeronautics and Space Administration logo
National Science Foundation logo
US Flag An Official Website of the United States Government