Experiment on operation stability of valveless pulse detonation rocket engine

TAN Fengguang; WANG Ke; YU Xiaodong; WANG Yun; LI Qing'an; FAN Wei

doi:10.7527/S1000-6893.2020.24189

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2021 , Vol. 42 >Issue 3: 124189 - 124189

DOI: https://doi.org/10.7527/S1000-6893.2020.24189

Fluid Mechanics and Flight Mechanics

Experiment on operation stability of valveless pulse detonation rocket engine

TAN Fengguang ,
WANG Ke ,
YU Xiaodong ,
WANG Yun ,
LI Qing'an ,
FAN Wei

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1. School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China;
2. Shaanxi Key Laboratory of Thermal Sciences in Aeroengine System, Northwestern Polytechnical University, Xi'an 710129, China

Received date: 2020-05-07

Revised date: 2020-07-11

Online published: 2020-08-07

Supported by

National Natural Science Foundation of China (91641101, 91441201); Natural Science Basic Research Program of Shaanxi Province(2020 JQ-185); the Fundamental Research Funds for the Central Universities (3102018AX006, 3102019ZX024)

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Abstract

Despite the ability of the valveless scheme to produce high frequency detonations, the problems leading to unsteady operations such as deflagration, ignition failure, and discrepancy in frequencies of operation and ignition are not clear. To study the influence of supply conditions on steady operations of the pulse detonation rocket engine, experiments have been conducted based on the valveless mode. Ethylene and oxygen-enriched air have been utilized as fuel and oxidizer, respectively. Influence of the oxygen volume fraction on the operation stability has also been analyzed. The results indicate that steady detonations are available only when the equivalence ratio is within a proper range, i.e., 1.2-1.7 and 0.8-2.3, when the oxygen volume fractions of 40% and 66% are used, respectively. The range of the equivalence ratio increases for producing detonation when the oxidizer with the volume fraction of 66% is used. In addition, pressure oscillations near the closed end of the detonation tube will propagate upwards to the supply passages when fully-developed detonations are produced, and thus flow oscillations, with a frequency times of the detonation frequency, will be induced inside the supply passages. However, the flow oscillations appear disorderly if steady detonations are not obtained in the detonation tube. Since the disorderly flow oscillations inside the supply passages will further influence the operation stability, measures to control them should be considered.

Key words： detonation; valveless scheme; operation stability; oxygen volume fraction; flow oscillation

Cite this article

TAN Fengguang , WANG Ke , YU Xiaodong , WANG Yun , LI Qing'an , FAN Wei . Experiment on operation stability of valveless pulse detonation rocket engine[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021 , 42(3) : 124189 -124189 . DOI: 10.7527/S1000-6893.2020.24189

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