SHOCK WAVES FOR ENHANCED MIXING IN SCRAMJET COMBUSTORS

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$50,000.00
Award Year:
1988
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Agency Tracking Number:
6710
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
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
DR G STUART KNOKE
() -
Business Contact:
() -
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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