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COMBUSTION PROCESSES IN SPACE STORABLE LIQUID ROCKET ENGINES

Award Information

Agency:
Department of Defense
Branch:
Air Force
Award ID:
12958
Program Year/Program:
1991 / SBIR
Agency Tracking Number:
12958
Solicitation Year:
N/A
Solicitation Topic Code:
N/A
Solicitation Number:
N/A
Small Business Information
Software & Engineering Associa
1000 E William St - Ste 200 Carson City, NV 89701
View profile »
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No
 
Phase 2
Fiscal Year: 1991
Title: COMBUSTION PROCESSES IN SPACE STORABLE LIQUID ROCKET ENGINES
Agency / Branch: DOD / USAF
Contract: N/A
Award Amount: $504,191.00
 

Abstract:

THE EXHAUST FROM NTO/MMH FUEL RICH GAS GENERATORS (GG) ARE KNOWN TO CONTAIN A LARGE FRACTION OF AMMONIA. THIS PHENOMENON MAKES IT POSSIBLE TO ACTIVELY COOL A ROCKET NOZZLE WALL USING THE ENDOTHERMIC DECOMPOSITION OF AMMONIA. A REALISTIC ANALYSIS OF THIS COMBUSTION PROCESS IS TO BE DEVELOPED WHICH INCLUDES ROCKET NOZZLE FLOW WITH FINITE RATE CHEMICAL KINETICS AND THE TANGENTIAL SLOT INJECTION OF GG EXHAUST. THE ANALYSIS IS TO BE APPLIED TO PUMP FED LIQUID ROCKET SPACE ENGINES OPERATING WITH STORABLE PROPELLANTS. THE EFFECT ON WALL HEAT TRANSFER AND ENGINE PERFORMANCE ARE TO BE STUDIED. EFFECTS TO BE INVESTIGATED INCLUDE THOSE OBTAINED BY VARYING THE GAS GENERATOR MIXTURE RATIO AND MASS FLOW RATE. A PRIMARY OBJECTIVE OF THE PROJECT IS TO OBTAIN A BETTER UNDERSTANDING OF THE ROLE PLAYED BY AMMONIA DECOMPOSITION IN THE BOUNDARY LAYER DOWNSTREAM OF THE INJECTION POSITION. RECOMMENDATIONS ARE TO BE MADE FOR IMPROVED ENGINE DESIGN.

Principal Investigator:

Gary R Nickerson
7028821966

Business Contact:

Small Business Information at Submission:

Software & Engineering Associa
1000 E William St - Ste 200 Carson City, NV 89701

EIN/Tax ID:
DUNS: N/A
Number of Employees:
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No