NASA SBIR 2019-II Solicitation

Proposal Summary

 19-2- H10.01-2792
 Advanced Propulsion Systems Ground Test Technology
 Injector for LOX-GH Stable Combustion at Low Pressure and High Velocity
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Rocket Propulsion Systems, LLC
6127 Northeast 2nd Lane
Renton, WA 98059
(425) 516-8677

PRINCIPAL INVESTIGATOR (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Maksud (Max) Ismailov
6127 NE 2ND LN
4255168677, WA 98059 - 5358
(425) 516-8677

BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Maksud (Max) Ismailov
6127 NE 2ND LN
4255168677, WA 98059 - 5358
(425) 516-8677

Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

A novel injector is proposed in response to "Robust design solutions for liquid oxygen injection and subsequent stable combustion with high temperature (>1700 R) hydrogen flowing at low pressure (<25 psia) and high velocity (~Mach 0.2)" subtopic, listed under "Advanced Propulsion Systems Ground Test Technology" focus area.  This injector features fully 3D-printed Liquid Oxygen (LOX)-centered swirl coaxial design with high-speed hydrogen flowing peripherally and impinging axially on central LOX conical spray.  We believe that due to ability of the center swirl element to atomize LOX to a fine degree and penetrate into Gaseous Hydrogen (GH) free stream, this injector would be able to sustain combustion in a stable and efficient manner.  Because of its potential to be easily tunable in response to combustion dynamics observed in operation, we expect to develop this injector for a stable operation at a rapid pace.  This injector can be used in any system flowing hot high-speed hydrogen or hydrogen-rich mixture needed to be burned or neutralized, such as NASA's ground testing of nuclear rocket engines or similar hydrogen-rich combustion devices.  Phase I has focused on technical feasibility demonstration and procurement of two sub-scale prototype injectors, with and without premix of LOX-GH propellants upstream of primary combustion zone, completing at TRL 3.  If this project proceeds into Phase II, it will focus on sub-scale hot-fire development testing and demonstration, for follow-on commercialization and field operations, completing at TRL 6. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)
  • NASA Ground testing of nuclear thermal propulsion
  • NASA Ground testing of hydrogen rich rocket engines or combustion devices
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)
  • Nuclear reactor coolant hydrogen combustion 
  • Liquid air cycle engines - thrust augmentation
  • Ram / Scramjet combustion 
  • Air-augmented rockets
  • Research test article at government and university labs  
Duration: 24

Form Generated on 05/04/2020 06:24:14