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PULSE DETONATION ENGINE
GUIDED BY DEEPU.M LECTERER N.S.S.C.E. PRESENTED BY REJEESH K S7MB ROLLNO:117 N.S..S.C.E PULSE DETONATION ENGINE
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CONTEXT INTRODUCTION EXPERIMENTAL-SETUP PRINCIPLE OF ENGINE
PRE-COMPRESSION THERMODYNAMIC STUDIES COMPUTATIONAL STUDIES DIFFERENCES FROM TO OTHER ENGINES ADVANTAGES STATUS CONCLUSION
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INTRODUCTION New concept Early experiments in 1940
Developed for boosting satellites to high orbits Low cost Noise reduction
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Experimental set-up
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ACTUAL ENGINE
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PRINCIPLE OF ENGINE
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6 Stages of combustion Injection of fuel and air mixture
Initiation of detonation Actual combustion, detonation propagates through the chamber Detonation leaves the chamber Rarefaction waves move in from exit Scavenging of the combustion
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COMBUSTION ANALYSIS
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INLET LOSSES
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COMBUSTOR LOSSES
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NOZZLE LOSSES
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SHADOWGRAPH TESTING
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Results
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DIFFERENCES COMPARED TO OTHER ENGINES
Combustion chamber is open No piston is used Combustion occurs in detonative mode
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ADVANTAGES High thermodynamic efficiency Simple engine principle
Applicable for a wide range of velocities Not limited to circular geometries Can be used both in rocket and in air breathing mode
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STATUS First experimenting on the PDE in 1940
No flying applications have been reported
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FUTURE The length of the mixture chamber
The shape of the contraction section Position of spark plug Position of introduction of hydrogen Position of reed valve
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CONCLUSION The pulse detonation engine has several very attractive features and has the potential of becoming an alternative to the current propulsion devices
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