Propulsive Performances of Pulsed Detonations

Zitoun, Ratiba; Desbordes, D.

doi:10.1080/00102209908924199

Cited by 107 publications

(52 citation statements)

References 6 publications

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“…Beyond this, there does not appear to be significant benefit. These PDE performance results are smaller than what is typically listed in the literature 1,2,10 ; however, because they represent computed results from a validated code, it can be argued that they are more representative of an idealization in the sense of being as good as can be expected.…”

mentioning

confidence: 49%

“…For small tubes, even very thin diaphragms can equal a significant fraction of the initial explosive mixture mass, increasing the tamping effectiveness. 7 Based on information of the diaphragms provided by the researchers, 1,2,4,8 we use the Gurney model (see Ref. 7) to correct the measured impulse values for the diaphragm effect as described by Cooper and Shepherd.…”

Section: Data For Partially Filled Tubesmentioning

confidence: 99%

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Impulse Correlation for Partially Filled Detonation Tubes

Cooper

Shepherd

Schauer

2004

Journal of Propulsion and Power

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to calculate the specific thrust and specific impulse over the Machnumber regime. The specific impulse results are shown in Fig. 3. A Mach-number dependent static inlet temperature profile was used for these calculations in order to account for altitude effects. 7 The nozzle inlet total temperature was chosen to be 4200 R (2300 K). The ratio of specific heats was 1.3. The fuel heating value was 19,000 BTU/lbm (44,000 kJ/kg), typical for many hydrocarbon fuels.Also shown in the Fig. 3 are the performance results for a ramjet and for afterburning turbojets with compressor pressure ratios of 30 and 4. For the turbojet calculations the compressor and turbine adiabatic efficiencies were again 0.85 and 0.90, respectively. The combustor and afterburner were assumed loss free (i.e., constant total pressure). The turbine inlet temperature was 3000 R (1670 K). It can be seen that the ideal PDE performance is fairly consistent over the Mach-number regime and that it is comparable with a nonideal, afterburning turbojet having a compressor pressure ratio of 4.0. For turbojets of a more realistic pressure ratio, the PDE shows significantly less specific impulse and (not shown) specific thrust. Compared with the ramjet, the performance advantages of a PDE are clear at Mach numbers below 3.0. Beyond this, there does not appear to be significant benefit. These PDE performance results are smaller than what is typically listed in the literature 1,2,10 ; however, because they represent computed results from a validated code, it can be argued that they are more representative of an idealization in the sense of being as good as can be expected.Other PDE applications can be examined in a straightforward manner using the map of Fig. 1. Examples would include gas-turbine topping cycles, afterburners (bypass duct or full flow), even ejectorbased cycles (if some assumptions are made regarding the work transfer process).Of the applications that have been examined, the process has been made easier through the use of Eq. (9); however, it should be kept in mind that for a given application, not all values of q 0 (and therefore enthalpy ratio) are possible. Also, the results shown represent a particular gasdynamic cycle. Other cycles, such as PDE cycles with valved exhaust (or low-loss, variable backpressure systems), or those employing shaped tubes can lead to different and possibly superior performance to that presented. 11,12 ConclusionsIt has been demonstrated in this work that idealized airbreathing PDE performance can be mapped onto a single plot of total pressure ratio vs total enthalpy ratio. It has further been shown that this format is useful in system studies because the PDE can be viewed as simply another component with straightforward input and output. The idealized PDE performance data were obtained from a onedimensional CFD code, and it has been shown that this is a more realistic approach than purely analytical methods. The performance shown is generally below that which has been previously reported for so-called idealized PDE ...

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mentioning

confidence: 49%

Section: Data For Partially Filled Tubesmentioning

confidence: 99%

Impulse Correlation for Partially Filled Detonation Tubes

Cooper

Shepherd

Schauer

2004

Journal of Propulsion and Power

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“…This value is reported as a different value. For example, Zitoun et al, 15) Wintenberger et al, 16) and Kailasanath 1) proposed K ¼ 5:3, 4.8 and 4.65, respectively. Though the above researchers proposed K as an empirical value, Endo et al 17) proposed an approximate solution without empirical parameters.…”

Section: Single-shot Thrust Performance For Simplified Pdesmentioning

confidence: 99%

“…Many researchers 1,[15][16][17][18] have reported that the thrust of a simplified PDE with a straight tube with a filling fraction of 1.0 is predicted by the following Eq. (1):…”

Section: Single-shot Thrust Performance For Simplified Pdesmentioning

confidence: 99%

Numerical Study and Performance Evaluation for a Pulse Detonation Engine with an Exhaust Nozzle (1st Report: Estimation on Performance using a Detailed Reaction Model)

Kimura

Tsuboi

Hayashi

et al. 2012

Trans. Japan Soc. Aero. S Sci.

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This paper presents a propulsive performance evaluation for a H 2 /Air pulse detonation engine (PDE) equipped with a converging-diverging exhaust nozzle. The evaluation was conducted using system-level modeling and multi-cycle numerical simulations. This study discusses two-dimensional and axisymmetric compressible Euler equations with a detailed chemical reaction model. First, the single-shot propulsive performance of a simplified-PDE (i.e., no exhaust nozzle) is evaluated to show the validity of the numerical and performance evaluation method. The influences of the initial conditions, ignition energy, grid resolution and scale effects on the propulsive performance are studied using multi-cycle simulations.

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“…A Pulse Detonation Engines (PDEs) [1][2][3][4][5] generate detonation waves intermittently to produce high-pressure burned gas and derive impulsive force and power. PDEs in which the unburned gas is compressed and burned by selfsustained detonation waves, can generate work and force even when the compressor is simplified or eliminated, achieving a simpler engine structure.…”

Section: Introductionmentioning

confidence: 99%

Analysis on Thermal Efficiency of Non-Compressor Type Pulse Detonation Turbine Engines

Maeda

Kasahara

Matsuo

et al. 2010

Trans. Japan Soc. Aero. S Sci.

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applied thermodynamic analysis to a simplified Pulse Detonation Turbine Engine (PDTE) system to estimate ideal performance; the theoretical thermal efficiency of a non-compressor type PDTE system is assumed to be 20% to 30% with an ethylene-oxygen mixture. Several experimental studies were conducted using a test apparatus composed of an automobile turbocharger connected to a single-tube pulse detonation engine (PDE). The results demonstrated that the measured thermal efficiency was 1% to 5%, far lower than the theoretical thermal efficiency. These studies covered the simplest PDTE system, in which the detonation wave from a PDE tube is directly incident to a turbine and can be considered as the lowest PDTE system performance. This study clarifies the reduced thermal efficiency by building a model simulating the inside of a turbine. The relationship between the turbine peripheral velocity and thermal efficiency of a non-compressor type PDTE with an ethylene-oxygen mixture was determined based on the premise of being constant turbine peripheral velocity during one PDE cycle. The PDTE test apparatus with a single-tube PDE connected automobile turbocharger was used to verify this model experimentally. The turbine peripheral velocity was changed by changing the PDTE operating frequency and was applied to the model to obtain the relationship with thermal efficiency. As PDTE operating frequency increased, the thermal efficiency of the model gradually approached the maximum value at a constant peripheral velocity during one PDE cycle as described above. Similar trends were observed in both tests and model predictions of thermal efficiency as a function of PDTE operating frequency i.e. turbine peripheral velocity.

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Propulsive Performances of Pulsed Detonations

Cited by 107 publications

References 6 publications

Impulse Correlation for Partially Filled Detonation Tubes

Impulse Correlation for Partially Filled Detonation Tubes

Numerical Study and Performance Evaluation for a Pulse Detonation Engine with an Exhaust Nozzle (1st Report: Estimation on Performance using a Detailed Reaction Model)

Analysis on Thermal Efficiency of Non-Compressor Type Pulse Detonation Turbine Engines

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