Influence of nozzle geometry on the performance of a pulse detonation wave engine

Stuessy, W. S.; Wilson, Donald R.

doi:10.2514/6.1997-2745

Cited by 7 publications

(2 citation statements)

References 6 publications

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“…It was found that Laval nozzle has better results as compared to other three nozzles; it produced the best performance of 1800N thrust, gross specific impulse of 1750s and mass rate of 313kg/ (m 2 .s). [16] investigated experimentally the effect of nozzle geometry on the performance of a pulse detonation wave engine. The tests were conducted on two chamber geometries, cylindrical and annular with and without exhaust nozzles.…”

Section: Review Of Work Carried Outmentioning

confidence: 99%

Effect of Different Nozzles on the Performance of Pulse Detonation Engine- A Review

Jindal¹

2016

IJRET

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Pulse Detonation Engine (PDE) has recently got fancy of aero-propulsion community due to its simplicity and advantages over current propulsion systems. The PDE operates on the detonation of combustion products, which is produced by burning of a reactive gas mixture at normal pressure and temperature. The reactants are then at a high pressure and high temperature. The impulsive thrust is produced through rapid ignition and formation of detonation waves. The present paper is a review of various efforts made to enhance the Pulse detonation Engine performance by using different types of nozzle geometries.

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Section: Review Of Work Carried Outmentioning

confidence: 99%

Effect of Different Nozzles on the Performance of Pulse Detonation Engine- A Review

Jindal¹

2016

IJRET

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“…(i-r)J rtf 2 r /? vr + ij (4) where P! is the propellant pressure upstream from the injector, and P 2 is the pressure at the exit.…”

Section: Injection Timementioning

confidence: 99%

Injection and mixing of gas propellants for pulse detonation propulsion

Musielak

1998

34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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Detonation has received attention of late because of its role as the primary combustion mechanism in rocket and airbreathing Pulse Detonation Engines (PDEs). However, there are many unresolved issues related to the proper utilization of detonation combustion in these applications. The detonation process has been studied predominantly under the assumption of premixed gases. However, the unsteady nature of PDEs requires relatively small tunes to inject and mix the propellants prior to each cyclic detonation; and this condition is difficult to achieve experimentally. This paper addresses the injection and mixing processes, and presents new data aimed at supporting the development of practical PDEs. Results are given to illustrate the mixing characteristics of fuel-oxidizer mixtures, modeled with a CFD combustion code.

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