Pressure History at the Thrust Wall of a Simplified Pulse Detonation Engine

Endo, Tamio; Kasahara, Jiro; Matsuo, Akiko; Inaba, Kazuaki; Sato, Shigeru; Fujiwara, Toshi

doi:10.2514/1.976

Cited by 130 publications

(73 citation statements)

References 10 publications

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“…I sp,FF of the stoichiometric C 2 H 4 -O 2 mixture was 171.2 sec [30]. The specific impulse at the second and higher PDE cycle, I sp,PF, 2nd , was different from the first specific impulse, I sp,PF, 1st , because the burned gas did not exist in the combustor at the first cycle.…”

Section: Experimental Setup and Conditionsmentioning

confidence: 99%

“…11 (under the positive-time ignition condition) and the time-history of the pressure at the closed-tube end wall, p wall , which was obtained by using the model of Endo et al [30]. Figure 14 shows the x-t diagram of the combustion wave and the shock wave as shown in Fig.…”

Section: Shock Wavementioning

confidence: 99%

“…Wintenberger et al [28], numerical analysis by Wintenberger et al [29] and theoretical analysis by Endo et al [30]. Moreover, according to Cooper et al [31] and Sato et al [32], a PDE can achieve a dramatically high specific impulse by performing a partial fill of the propellant.…”

Section: Introductionmentioning

confidence: 99%

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Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

Matsuoka

Esumi

Ikeguchi

et al. 2012

Combustion and Flame

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We developed a rotary valve for a pulse detonation engine (PDE), and confirmed its basic characteristics and performance. In a square cross-section combustor, we visualized a multi-shot of a pulse detonation rocket engine (PDRE) cycle at an operation frequency of 160 Hz by using a high-speed camera (time resolution: 3.33 μsec, space resolution: 0.4 mm) and a Schlieren method.The propellant filling process and the purge process were confirmed, and each process was modeled.Moreover, we confirmed the processes of detonation wave generation and burned gas blowdown. In addition, we investigated the impact of shortening the passage width of a combustor and negative-time ignition (ignition time is earlier than the end-time of the propellant filling process) on the deflagration-to-detonation transition (DDT) distance and time. The DDT distance did not depend on the passage width of a combustor and decreased under the negative-time ignition condition. With a passage width of 20 mm, the DDT distance decreased by 22% under the negative-time ignition condition to a minimum value (76 ± 8 mm). The DDT time from spark time reached a minimum value (69 ± 14 μsec) under the condition of a passage width of 10 mm and negative-time ignition.The detonation initiation time and the DDT distance were represented by the time until the flame expanded toward the tube-axis one-dimensionally from ignition (characteristic time). We also carried out thrust measurement using a PDRE system composed of a circular cross-section combustor and the newly developed valve. We obtained a stable time-averaged thrust in a wide range of operation frequency (40 Hz -160 Hz) and confirmed the increase of specific impulse due to a partial-fill effect.

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Section: Experimental Setup and Conditionsmentioning

confidence: 99%

Section: Shock Wavementioning

confidence: 99%

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Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

Matsuoka

Esumi

Ikeguchi

et al. 2012

Combustion and Flame

Self Cite

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“…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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“…However, it is important to investigate the local ignitions behind shock waves under low temperature conditions, from the point of view of chemical kinetics in high-prssure (non-diluted test gases) shock tube experiments in which the non-uniformity of reflected shock waves tends to be greater because of increased viscous effects [23,24] and from the view of application systems (for example, pulse detonation engines (PDEs) [25][26][27][28][29][30][31][32][33][34][35] etc.). Therefore we focused on local ignitions induced by non-uniformity behind reflected shock waves under low-temperature conditions (Voevodsky and Soloukhin [17] : mild ignition, Gilbert and Strehlow [2] : hot spot initiation, Mayer and Oppenheim [18] : mild ignition) and investigated numerically and experimentally the local ignition position and the reason why local ignitions are located at a point distant from the reflecting wall.…”

Section: Objective Of the Present Studymentioning

confidence: 99%

Visualization study of ignition modes behind bifurcated-reflected shock waves

Yamashita

Kasahara

Sugiyama

et al. 2012

Combustion and Flame

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This study was a numerical and experimental investigation of lowtemperature auto-ignitions behind reflected shock waves in which a shock tube was employed as the experimental system. We used a high-speed video camera and the Schlieren method to visualize the ignition phenomena. Experiments were performed over a temperature range from 54910 to 134911 K and a pressure range from 56 to 203  kPa, and a non-diluted stoichiometric acetylene-oxygen mixture was chosen as the combustible gas. We introduced a numerical simulation to help us understand the disturbed temperature distribution behind bifurcated shock waves due to interference between reflected shock waves and the boundary layer developed behind incident shock waves.Additionally, we experimentally observed and evaluated quantitatively a tendency for ignition positions to be located farther from the reflecting wall as the temperature decreased behind reflected shock waves. To focus our attention on the ignition positions, we classified the ignition types behind reflected shock waves as near-wall ignition and far-wall ignition by 4.7 mm distance from Combustion and Flame 159 (2012)

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Pressure History at the Thrust Wall of a Simplified Pulse Detonation Engine

Cited by 130 publications

References 10 publications

Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

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

Visualization study of ignition modes behind bifurcated-reflected shock waves

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