2400K GAS SAMPLE CELL

A PHASE I FEASIBILITY STUDY IS PROPOSED FOR THE DEVELOPMENT OF A 2400 DEGREE KELVIN GAS SAMPLE CELL WHICH IS CAPABLE OF SIMULATING THE COMBU STION PRODUCTS OF HYDROGEN-AIR SCRAMJET PROPULSION SYSTEM AT PRESURES FROM 0.5 TO 2.0 ATMOSPHERES, FLOWS FROM 0 TO 1.0 STANDARD LITERS PERMI NUTE, AND A CELL COMPOSITION OF AIR WITH 20 PERCENT WATER VAPOR BY WEI GHT. ADDRESSED WITHIN THE PROPOSAL IS THE PRIMARY DESIGN REQUIREMENT THAT THE CELL MUST ACCEPT LASER RAMAN SPECTROSCOPY DIAGNOSTIC INSTRUME NTATION AND THUS MUST INCORPORATE UV GRADE OPTICAL VIEW PORTS WHICH IN TRODUCE MINIMAL DISTORTION INTO THE RAMAN MEASUREMENT. CONSIDERATION IS MADE TO THE JAMOR SUBSYSTEMS REQUIRED INCLUDING THE HEATING SOURCE, SAMPLE GAS SOURCE, TEMPERATURE CONTROL, PRESSURE CONTROL, FLOW CONTRO L, OPTICAL VIEW PORTS AND COOLING AND INSULATION PACKAGES. THE SUBSYS TEMS ARE TO BE EVALUATED SEPARATELY BUT WITH THE GOAL OF DEVELOPING A WORKABLE GAS SAMPLE CELL. THE RESULT OF THE FEASIBILITY STUDY WILL IN CLUDE A DETAILED DESCRIPTION OF THE TECHNIQUE AND EQUIPMENT NECESSARY TO INITIATE A PHASE II DESIGN AND CONSTRUCTION, AND DEMONSTRATION OF A PROTOTYPE SYSTEM. THE PHASE I FEASIBILITY STUDY IN ADDITION, WILL IN CLUDE A LABORATORY DEMONSTRATION OF A 2400 DEGREE KELVIN GAS SAMPLE.