Experimental research on the performance of hollow and annular rotating detonation engines with nozzles

Zhang, Yunzhen; Sheng, Zhaohua; Rongx, Guangyao; Shen, Dawen; Wu, Kevin; Wang, Jianping

doi:10.1016/j.applthermaleng.2022.119339

Cited by 22 publications

(2 citation statements)

References 43 publications

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“…In the experimental apparatus, the injectors are sometimes located only near the outer wall [18,41]. In this section, we investigate the impact of the inner radius on the system while maintaining a constant injection area near the outer wall.…”

Section: Effect Of Inner Radius With Fixed Injection Areamentioning

confidence: 99%

Numerical Study of the Effects of Injection Conditions on Rotating Detonation Engine Propulsive Performance

Shi,

Fan,

Shen

et al. 2023

Aerospace

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A three-dimensional upwind conservation element and solution element method (CESE) in cylindrical coordinates is first developed to effectively solve the unsteady reactive Euler equations governing a hydrogen–air rotating detonation engine (RDE) with coaxial structures. The effects of the annular width on the structure of the detonation front and the relationship between the thrust and mass flow rate are then investigated. Additionally, RDEs with various injection conditions are systematically analyzed regarding flow patterns and propulsion performance. The results reveal a positive correlation between the specific impulse and the area ratio of the injection slot to the head-end wall. Nevertheless, the specific impulse shows minimal dependence on the injector slot’s location when the area ratio is constant. Ultimately, it is concluded that the area ratio between the injector and the head-end wall is critical in determining the loss of specific impulse.

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Section: Effect Of Inner Radius With Fixed Injection Areamentioning

confidence: 99%

Numerical Study of the Effects of Injection Conditions on Rotating Detonation Engine Propulsive Performance

Shi,

Fan,

Shen

et al. 2023

Aerospace

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“…Since RDEs have attracted extensive attention as potential fuelers of aerospace and weapons, researchers are focusing on further enhancing the performance of RDEs, such as the propellant injection [3][4][5], combustor geometry [6][7][8][9], method of ignition [10][11][12], and formation mechanism of the rotating detonation wave (RDW) [10,13]. In addition, the rotating detonation rocket engines [14,15], scramjet engines [16][17][18], and turbine engines [19,20] have been built as experimental prototypes to promote engineering application, but the running time of RDEs is limited to seconds due to the harsh thermal environment.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Thermal Prediction and Heat Transfer Characteristics of Two-Phase RDE during Long-Duration Operation

Wang,

Song,

Chen

et al. 2024

Energies

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Accurately predicting the thermal characteristics and heat transfer distribution of the rotating detonation engine (RDE) and acquiring a clear understanding of the performance and mechanism of the rotating detonation are of great significance for achieving the safe and reliable long-duration operation of RDEs. Using RP-3 as fuel, a long-duration experimental study is performed on a 220 mm-diameter RDC to investigate the details with respect to the thermal environment. The heat flux at the typical location and the average heat flux of both the inner and outer cylinders are measured, respectively. Meanwhile, the peak pressure of the rotating detonation wave (RDW) and specific thrust are analyzed. When the ER is between 0.5 and 1 (oxidizer 2 kg/s), the stable rotating detonation mode is obtained, and the detonation duration is set as 40 s to accurately calculate the heat released by the detonation combustion. The heat flux in the upstream region of the RDW location ranges from 2.40 × 105 W/m2 to 3.17 × 105 W/m2, and the heat flux in the downstream area of the RDW location ranges from 1.05 × 106 W/m2 to 1.28 × 106 W/m2. The results demonstrate the important role of the detonation combustion zone, and the thrust performance of RDC can be improved by making the RDW move forward along the RDC axis, which is the optimal direction of detonation combustion. Through a comparison of average heat flux under different conditions, it is found that the heat released by the RDC is directly related to its thrust. In addition, the average heat flux of the inner cylinder is about three times that of the outer cylinder for the two-phase RDC with a Tesla valve intake structure, indicating that the high-temperature combustion product is closer to the inner wall. Therefore, more thermal protection should be allocated to the inner cylinder, and a more systematic analysis of the two-phase flow field distribution in the annular combustion chamber should be carried out to improve the thrust performance. In this paper, the average heat flux of the inner and outer cylinders of the RDC as well as the typical local heat flux of the outer cylinders is quantitatively measured by means of experiments, which not only deepens the understanding of RDC flow field distribution, but also provides quantitative boundary conditions for the thermal protection design of RDCs.

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Effects of the outlet contraction ratio on the performance of liquid kerosene/air two-phase rotating detonation combustors

Li,

Jin,

et al. 2024

Acta Astronautica

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Experimental research on the performance of hollow and annular rotating detonation engines with nozzles

Cited by 22 publications

References 43 publications

Numerical Study of the Effects of Injection Conditions on Rotating Detonation Engine Propulsive Performance

Numerical Study of the Effects of Injection Conditions on Rotating Detonation Engine Propulsive Performance

Experimental Investigation of Thermal Prediction and Heat Transfer Characteristics of Two-Phase RDE during Long-Duration Operation

Effects of the outlet contraction ratio on the performance of liquid kerosene/air two-phase rotating detonation combustors

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