Analysis on Propulsive Performance of Hollow Rotating Detonation Engine with Laval Nozzle

In the present study, an experimental performance analysis of hollow rotating detonation engines (RDEs) with Laval nozzles is carried out for the first time. Experiments of a hollow rotating detonation engine with a Laval nozzle were performed with a modular RDE at a backpressure condition of 1 atm....

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Bibliographic Details
Published in:Journal of propulsion and power 2023-09, Vol.39 (5), p.765-779
Main Authors: Zhang, Yunzhen, Ma, John Z., Wu, Kevin, Cheng, Miao, Sheng, Zhaohua, Rong, Guangyao, Shen, Dawen, Wang, Jianping, Zhang, Shujie
Format: Article
Language:English
Subjects:
Combustion chambers
Detonation
Engineering schools
Engines
Experiments
Heat
Mathematical models
Nozzles
Performance evaluation
Rocket engines
Rotation
Specific impulse
Stagnation pressure
Velocity
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Summary:In the present study, an experimental performance analysis of hollow rotating detonation engines (RDEs) with Laval nozzles is carried out for the first time. Experiments of a hollow rotating detonation engine with a Laval nozzle were performed with a modular RDE at a backpressure condition of 1 atm. Two configurations with area ratios of the outlet throat to the inlet of Ath/Ain=5.3 and 2.7 have been tested with gaseous methane/oxygen as propellants. Three normalized metrics, usually used for evaluating the performance of conventional rocket engines, are introduced to analyze the performance deficit between the measured value of an RDE and the ideal value of an isobaric-combustion-based engine. These metrics allow for assessing the entire engine and each component separately. The metric analysis suggests a small outlet-to-inlet area ratio (Ath/Ain) is detrimental to the propulsive performance. To explain the mechanism, a gas-stratification flowfield model is further proposed. It is found that the unchoked region in the combustible gas layer, which is caused by unchoked injection on the injecting plate, is responsible for the performance deficit of the combustion chamber. This model is then validated by one-dimensional numerical simulations and experimental data. In addition, we also focus on the global performance, including the gross thrust, the specific impulse, and the utilization of the supplied stagnation pressure. The result implies a tradeoff space when choosing an appropriate Ath/Ain.
ISSN:0748-4658
1533-3876
DOI:10.2514/1.B38830