Experimental Study on a Two-phase Pulse Detonation Rocket Engine at the Frequency of 35Hz

Experimental studies were performed to investigate the ejector’s effect on the performance of a pulse detonation rocket engine (PDRE). The PDRE employed in the experiments utilizes gasoline as fuel and air as oxidizer. The operating frequency of the PDRE is 10 and 20 Hz respectively. Performance is quantified by thrust measurements, and the average thrust of the PDRE is obtained by integration of the thrust measured in the experiment. The experimental results show that the PDRE can increase thrust augmentation with an ejector, a maximum thrust augmentation is measured by 18.7% at 10 Hz operating frequency. In the experiment, axial placement (X/DPDRE) of the ejector is varied downstream the PDRE tube of 0.5,1 and 2 respectively. It is found that the thrust augmentation obviously increases when the relative position at 1 and 2, and also the thrust augmentation increases at higher operating frequency. The experiment result is useful for the development of a PDRE producing higher thrust.

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Experimental investigation of the effect of bell-shaped nozzles on the two-phase pulse detonation rocket engine performance

Combustion Explosion and Shock Waves ◽

10.1134/s0010508211030117 ◽

2011 ◽

Vol 47 (3) ◽

pp. 335-342 ◽

Cited By ~ 9

Author(s):

Yu. Yan ◽

W. Fan ◽

K. Wang ◽

Ya. Mu

Keyword(s):

Experimental Investigation ◽

Rocket Engine ◽

Engine Performance ◽

Two Phase ◽

Pulse Detonation ◽

Pulse Detonation Rocket Engine

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Experimental Study of Kerosene-Fueled Pulse Detonation Rocket Engine

45th AIAA Aerospace Sciences Meeting and Exhibit ◽

10.2514/6.2007-238 ◽

2007 ◽

Author(s):

Qiang Li ◽

Wei Fan ◽

Chuanjun Yan ◽

Chenqi Hu ◽

Bin Ye

Keyword(s):

Experimental Study ◽

Rocket Engine ◽

Pulse Detonation ◽

Pulse Detonation Rocket Engine

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Experimental Investigation on a Two-Phase Pulse Detonation Rocket Engine With Solenoid Valves

47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition ◽

10.2514/6.2009-296 ◽

2009 ◽

Author(s):

Yu-qian Wang ◽

Wei Fan ◽

Jian-ling Li

Keyword(s):

Experimental Investigation ◽

Rocket Engine ◽

Two Phase ◽

Pulse Detonation ◽

Pulse Detonation Rocket Engine

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Study on Effect of Obstacle Shapes on Filling Process in Pulse Detonation Rocket Engine

Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University ◽

10.1051/jnwpu/20203840784 ◽

2020 ◽

Vol 38 (4) ◽

pp. 784-791

Author(s):

Yun Wang ◽

Wei Fan ◽

Jintao Jiang ◽

Peng Zhang

Keyword(s):

Numerical Simulations ◽

Rocket Engine ◽

Detonation Initiation ◽

Filling Process ◽

Two Phase ◽

Pulse Detonation ◽

Fuel Droplets ◽

Detonation Tube ◽

Different Shapes ◽

Pulse Detonation Rocket Engine

In order to explore the influence of obstacle shapes on the filling process of pulse detonation rocket engine under valveless self-adaptive working mode, the numerical simulations of two-phase single filling process and multi-cycle experiment were carried out, in which gasoline was utilized as fuel, and oxygen-enriched air as oxidizer. The effects of four kinds of obstacles with different shapes on the filling process of PDRE were studied. The results showed that the existence of obstacles blocks the filling of fuel into the tail of detonation tube, resulting in a great non-uniformity of filling results in the axial and radial directions. Fuel droplets collect near the head and wall of detonation tube, and droplets are seriously blocked by orifice plates. The detonation initiation and stable propagation can be achieved by Shchelkin spirals, annular grooves and spiraling grooves, while the detonation initiation cannot be achieved by orifice plates.

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