SHOCK WAVES FOR ENHANCED MIXING IN SCRAMJET COMBUSTORS

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: N/A
Agency Tracking Number: 6710
Amount: $50,000.00
Phase: Phase I
Program: SBIR
Awards Year: 1988
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
Flow Research Co
21414-68th Ave S, Kent, WA, 98032
DUNS: N/A
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 DR G STUART KNOKE
 () -
Business Contact
Phone: () -
Research Institution
N/A
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.

* information listed above is at the time of submission.

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