NASA SBIR 2004 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER:04-II X6.01-8118
PHASE-I CONTRACT NUMBER: NNM05AA51C
SUBTOPIC TITLE:Earth-to-Orbit Propulsion
PROPOSAL TITLE:Triaxial Swirler Liquid Injector Development

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
SIERRA ENGINEERING INC.
603 E. Robinson, Suite 7
Carson City ,NV 89701 - 4046
(775) 888 - 8952

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Daniel A Greisen
dag@sierraengineering.com
3050 Fite Circle, Suite 212
Sacramento, CA  89701 -4046
(916) 363 - 2996

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
Sierra Engineering Inc. (Sierra) believes that the subject triaxial liquid propellant swirl injector has the potential to meet many of NASA's Earth-to-Orbit (ETO) propulsion systems goals. The triaxial swirl injector is ideally suited to a wide range of liquid oxidizers and fuels, including hydrogen and a wide range of hydrocarbons. It holds the potential of excellent high-frequency combustion stability characteristics and low injector production cost, similar to a pintle injector. Additionally, the triaxial swirl injector offers the potential for excellent injector and combustion chamber thermal compatibility and outstanding propellant atomization characteristics, both at levels far superior to a pintle injector. The triaxial injector concept is well suited to both main injector and preburner applications. The Phase I SBIR effort focused on understanding the influence design variables have on injector performance. We developed the mechanical design concept for a prototype injector. The proposed Phase II effort will complete the detailed design and analysis of the prototype injector. The test hardware will be fabricated and tested with several propellants. A preliminary design will be developed for a large-scale combustor.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Current NASA applications for the swirl triaxial injector include CEV and a range of in-space applications. The goal is that the injector will be analytically scalable from as small as 50lbf-class to larger than 80,000 lbf-class for a variety of hydrocarbon fuels. The combination of analytical model results and test data will validate the design methodology. The design is amenable to a variety of liquid fuel combinations including LOX/CH4 and LOX/kerosene. The characteristics of the triaxial swirl injector also make it very attractive as a preburner injector for both fuel-rich and ox-rich staged combustion systems.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
There is a wide assortment of non-NASA customers for a demonstrated triaxial swirl injector. The marketplace currently appears to need a 40,000-lbf-class pressure-fed injector - Rocketplane XP, Virgin Galactic and Microcosm/Scorpius Falcon. Additionally, the USAF ARES program is interested in similar sized LOX/hydrocarbon engine systems. The practical market for these engines ranges from as few as a couple a year, plus spares, for novel demonstration flight systems, to hundreds per year in the case of a surge production for a fielded system similar to DARPA's FALCON system.


Form Printed on 08-01-05 13:52