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SHOCK WAVES FOR ENHANCED MIXING IN SCRAMJET COMBUSTORS

Award Information

Agency:
National Aeronautics and Space Administration
Branch:
N/A
Award ID:
6710
Program Year/Program:
1988 / SBIR
Agency Tracking Number:
6710
Solicitation Year:
N/A
Solicitation Topic Code:
N/A
Solicitation Number:
N/A
Small Business Information
Flow Research Inc
21414 - 68th Avenue South Kent, WA 98032
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Woman-Owned: No
Minority-Owned: Yes
HUBZone-Owned: No
 
Phase 1
Fiscal Year: 1988
Title: SHOCK WAVES FOR ENHANCED MIXING IN SCRAMJET COMBUSTORS
Agency: NASA
Contract: N/A
Award Amount: $50,000.00
 

Abstract:

AN EXPERIMENTAL INVESTIGATION OF SHOCK WAVE/SHEAR LAYER INTERACTIONS TO ENHANCE MIXING IN A SUPERSONIC COMBUSTION RAMJET (SCRAMJET) ENGINE IS PROPOSED. IN A SCRAMJET ENGINE OPERATING AT HYPERSONIC FLIGHT SPEEDS, THE SHORTER RESIDENCETIME AND DECREASED MIXING RATE CAUSE DETERIORATION IN THE COMBUSTION EFFICIENCY AS COMPARED WITH LOWER SPEEDS. A CONFIGURATION RECENTLY DEVELOPED TO PROMOTE RAPID MIXING IN A SUPERSONIC FLOW WILL BE EXPERIMENTALLY COMPARED WITH A BASELINE CONVENTIONAL CONFIGURATION. THE CONFIGURATION IS ASINGLE-STEP FLAMEHOLDER WITH A WEDGE ON THE OPPOSITE SUPERSONIC PASSAGE WALL TO INDUCE A WEAK SHOCK. THE OBJECTIVE OF THIS STUDY IS TO EVALUATE THE CONFIGURATION AS A MEANS FOR RAPID AND THOROUGH MIXING OF THE FUEL WITH THE SUPERSONIC AIR STREAM. DURING PHASE I, THE FEASIBILITY OF THE SCRAMJET MIXING CONCEPT WILL BE DETERMINED. PHASE I WILL INVOLVE AN EXPERIMENTAL STUDY OF THE CONFIGURATION USING A FACILITY SIMILAR TO A BLOWDOWN WIND TUNNEL. WE PLANTO MIX HELIUM WITH NITROGEN AND MEASURE THE CONCENTRATION PROFILE AT SUITABLE DISTANCES DOWNSTREAM OF THE STEP. IT ISEXPECTED THAT THE SHOCK WAVE/SHEAR LAYER INTERACTION WILL ALLOW THE HELIUM TO DIFFUSE MORE RAPIDLY ACROSS THE SUPERSONIC NITROGEN FLOW. WITH FAVORABLE RESULTS IN PHASE I, A PHASE II RESEARCH AND DEVELOPMENT PROGRAM WILL BE PURSUED TO PROVIDE PARAMETRIC INFORMATION FOR DESIGN OPTIMIZATION.

Principal Investigator:

Dr g stuart knoke

Business Contact:

Small Business Information at Submission:

Flow Research Co
21414-68th Ave S Kent, WA 98032

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