Performance Evaluation Method for Ideal Airbreathing Pulse Detonation Engines

Paxson, Daniel E.

doi:10.2514/1.11426

Cited by 28 publications

(14 citation statements)

References 6 publications

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“…The difficulties associated with coupling the inlet flow to the unsteady flow inside the detonation tube(s) and the interaction of the detonation wave and the subsequent unsteady flow with an exit nozzle are two significant modeling challenges. Paxson 27 has carried out unsteady, one-dimensional computations and represented the results in terms of a performance map in total-pressuretotal-temperature coordinates. This methodology has been used to compute specific impulse and make comparisons to idealized ramjet and turbojet performance over a range of flight Mach numbers.…”

Section: A Vmentioning

confidence: 99%

Model for the Performance of Airbreathing Pulse-Detonation Engines

Wintenberger

Shepherd

2006

Journal of Propulsion and Power

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A simplified flowpath analysis of a single-tube airbreathing pulse detonation engine is described. The configuration consists of a steady supersonic inlet, a large plenum, a valve, and a straight detonation tube (no exit nozzle). The interaction of the filling process with the detonation is studied, and it is shown how the flow in the plenum is coupled with the flow in the detonation tube. This coupling results in total pressure losses and pressure oscillations in the plenum caused by the unsteadiness of the flow. Moreover, the filling process generates a moving flow into which the detonation has to initiate and propagate. An analytical model is developed for predicting the flow and estimating performance based on an open-system control volume analysis and gasdynamics. The existing single-cycle impulse model is extended to include the effect of filling velocity on detonation tube impulse. Based on this, the engine thrust is found to be the sum of the contributions of detonation tube impulse, momentum, and pressure terms. Performance calculations for pulse detonation engines operating with stoichiometric hydrogen-air and JP10-air are presented and compared to the performance of the ideal ramjet over a range of Mach numbers. Nomenclature

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Section: A Vmentioning

confidence: 99%

Model for the Performance of Airbreathing Pulse-Detonation Engines

Wintenberger

Shepherd

2006

Journal of Propulsion and Power

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“…It was suggested in Ref. 5 that this parameter has a fairly modest effect on performance for straight tubes. The impact with area variation is unknown, and it is thus included here.…”

Section: Operational Mode Parametersmentioning

confidence: 99%

“…The general effect of this parameter has been demonstrated elsewhere. 5,6 In terms of stand-alone thrust devices, reducing Reactant Fraction increases fuel specific impulse at the expense of specific thrust.…”

Section: Operational Mode Parametersmentioning

confidence: 99%

“…These may be solved (integrated) numerically, which is done so here using a robust, well-tested code that has been described in the literature. 5 The idealizations described do not suppose quasi-steady operation, since such an assumption does not, in the author's opinion allow meaningful assessment of area profiling.…”

mentioning

confidence: 99%

“…It is noted that this same grid-spacing (and associated time step) has been used in other numerical studies and in comparison with experimental measurements, with reasonably accuracy. 5 Furthermore, since this paper is intended to compare the effects of different shapes, it is essentially important only that a consistent grid-spacing was used. For reference however, a brief comparison is presented in Appendix 1 between the present Q-1-D code and the axisymmetric code of Ref.…”

mentioning

confidence: 99%

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