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T he Effects of Nozzle Geometry on the Specific Impulse of a Pulse Detonation Engine. -Final Project Report- 12/04/01 Madeline Close and Christopher Johnson Prof. Edward Greitzer, Advisor. Overview. Background and Motivation Objective Technical Approach Experimental Results
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The Effects of Nozzle Geometry on the Specific Impulse of a Pulse Detonation Engine -Final Project Report- 12/04/01 Madeline Close and Christopher Johnson Prof. Edward Greitzer, Advisor
Overview • Background and Motivation • Objective • Technical Approach • Experimental Results • Conclusions • Acknowledgements • Questions
Background-Motivation • Interest in pulse detonation engines (PDEs) has renewed in the past decade. • PDEs are a structurally lightweight form of propulsion with high specific impulse (Isp) CFD calculations have been done to estimate the effects of varying nozzle geometries; however, few experimental results exist to substantiate the theoretical conclusions
Objective To determine the effects of nozzle geometry on the specific impulse of pulse detonation engines
Technical Approach • Six nozzles were designed and manufactured for testing conditions at Air Force Research Laboratory (AFRL)
Nozzle Geometry Matrix All nozzles were manufactured on-campus in the Gelb Laboratory with the exception of the plug (Central Machine Shop).
Nozzle Design • Converging contour derived from the MIT supersonic wind tunnel design and scaled for specific area ratios • Diverging contours calculated using Method of Characteristics • Plug nozzle contour based on a previous geometry
Nozzle Contours Converging-Diverging Contour (CD3) Converging Contour (C10) Plug Nozzle Contour
Testing facility at AFRL • Multi-cycle pulse detonation engine • Sensors
PDE Schematic Spark Detonation tube Inlet Air flow Detonation Fuel injection
Start/end PDE Terms • Cycle: 3-part process Frequency: engine cycles per second (Hz) • Ignition delay time: time between engine fill and ignition (ms) • Fill fraction: fraction of tube the gases would fill at STP Fill Purge Fire
Comparative Data Source: Aircraft Engines and Gas Turbines, Jack L. Kerrerbrock
Data Reduction Isp value for each test taken at steady state
Relative Nozzle Performance Frequency=30 Hz
Summary of Nozzle Performance • Straight nozzle gave slight improvement in performance over baseline at same dimensional frequencies [predicted by Eidelmann and Yang in AIAA paper 98-3877] • Smaller converging nozzle (C10) and small converging-diverging nozzle (CD10) backfired at higher frequencies.
Summary of Nozzle Performance • Larger converging nozzle (C3) performed well: maximum Isp of 4500 sec. at 40Hz • Larger converging-diverging nozzle (CD3) was consistently below baseline performance. • Plug nozzle (PG) was consistently 10%-20% above baseline performance
Conclusions • Shock reflections should be considered in choosing the Atube/A*. • Converging nozzles and plug nozzle performed best relative to baseline. • Converging-diverging nozzles performed poorly in the test conditions.
Future work • More families of nozzles need to be tested. CFD analysis of diverging nozzles shows they improve Isp. • Higher frequency tests should be performed. • Develop design method for making nozzles to maximize Isp.
Acknowledgements • Professor Ed Greitzer, Project Advisor • Don Weiner, Carl Dietrich, and Jerry Wentworth for machine shop help • Dr. Fred Schauer and Dr. Royce Bradley for help at WPAFB-APRL • Professors Ian Waitz and Mark Drela for technical assistance in nozzle design • Dr. David Tew (UTRC) and Dr. Doug Talley (AFRL) for project advice