Homogeneous-Dilution Model of Partially Fueled Simplified Pulse Detonation Engines

Endo, Tamio; Yatsufusa, Tomoaki; Taki, Shiro; Matsuo, Akiko; Inaba, Kazuaki; Kasahara, Jiro

doi:10.2514/1.21223

Cited by 38 publications

(28 citation statements)

References 10 publications

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“…A pulse detonation engine (PDE) is such a typical heat engine. A PDE can obtain nearly constant thrust and perform mechanical work by the generation of a high-frequency detonation wave [5][6][7][8][9][10][11][12][13][14][15][16][17][18]. The PDEs are classified as air-breathing PDEs [19][20][21][22] or pulse detonation rocket engines (PDREs) [23][24][25].…”

Section: Introductionmentioning

confidence: 99%

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: Introductionmentioning

confidence: 99%

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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“…The reflected shock wave undergoes repeated reflection between the contact surface and the closed end wall, and the impulse increases. Endo et al 26) proposed a homogeneous-dilution model in which the exhaust duration was considered. Sato et al 25) proposed a simple model based on a two-dimensional numerical calculation.…”

Section: Propellant-based Specific Impulsementioning

confidence: 99%

Thrust Performance of Rotary-Valved Four-Cylinder Pulse Detonation Rocket Engine

Matsuoka

Sakamoto

Morozumi

et al. 2015

Trans. Japan Soc. Aero. S Sci.

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We designed a rotary valve for a multi-cylinder pulse detonation rocket engine (PDRE), and constructed a greatly simplified rotary-valved four-cylinder PDRE (inner diameter and length of detonation tube: 37 mm and 1,600 mm, respectively). The partial-fill effect of a propellant in a multi-cylinder PDRE under high-frequency operation was investigated. The suctioned-air fill fraction was estimated using the model of Sato et al., which is a semiempirical formula for the partial-

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“…Cooper [6] predicted that the specific impulse will approach a limiting value on the basis of a simple model, but it is experimentally difficult to approach this limit in the detonation case. Other approximate models [5,8,[11][12][13] have also been proposed to predict the specific impulse dependence on the fill fraction when the fill fraction is close to 1. We examine both limits experimentally, carry out detailed numerical simulations, and compare the results to the approximate analytical models.…”

Section: Introduction Mmentioning

confidence: 99%

“…OTIVATED by recent interest in pulse detonation engines [1], a number of researchers [2][3][4][5][6][7][8][9][10][11][12] have studied the impulse from a partially filled detonation tube. In these experiments and analyses, a portion of the detonation tube near the closed end (thrust surface) contains the combustible mixture whereas the remaining portion of the tube up to the open end contains an inert gas mixture, for example, air.…”

Section: Introduction Mmentioning

confidence: 99%

Impulse Generation by an Open Shock Tube

et al. 2008

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We perform experimental and numerical studies of a shock tube with an open end. The purpose is to investigate the impulse due to the exhaust of gases through the open end of the tube as a model for a partially filled detonation tube as used in pulse detonation engine testing. We study the effects of the pressure ratio (varied from 3 to 9.2) and the volume ratio (expressed as fill fractions) between the driver and driven section. Two different driver gases, helium and nitrogen, and fill fractions between 5 and 100% are studied; the driven section is filled with air. For both driver gases, increasing the pressure ratio leads to larger specific impulses. The specific impulse increases for a decreasing fill fraction for the helium driver, but the impulse is almost independent of the fill fraction for the nitrogen driver. Twodimensional (axisymmetric) numerical simulations are carried out for both driver gases. The simulation results show reasonable agreement with experimental measurements at high pressure ratios or small fill fractions, but there are substantial discrepancies for the smallest pressure ratios studied. Empirical models for the impulse in the limits of large and small fill fractions are also compared with the data. Reasonable agreement is found for the trends with fill fractions using the Gurney or Sato model at large fill fractions, but only Cooper's bubble model is able to predict the small fill fraction limit. Computations of acoustic impedance and numerical simulations of unsteady gas dynamics indicate that the interaction of waves with the driver-driven gas interface and the propagation of waves in the driven gas play an essential role in the partial-fill effect.

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Homogeneous-Dilution Model of Partially Fueled Simplified Pulse Detonation Engines

Cited by 38 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

Thrust Performance of Rotary-Valved Four-Cylinder Pulse Detonation Rocket Engine

Impulse Generation by an Open Shock Tube

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