Effects of thermal wall conditions on rotating detonation

Wang, Yuhui; Wang, Jianping; Qiao, Wenyou

doi:10.1016/j.compfluid.2016.09.008

Cited by 20 publications

(2 citation statements)

References 16 publications

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“…When a single detonation wave propagated, the peak heat flux was 1.98 MW∕m 2 at the inner wall and 2.63 MW∕m 2 at the outer wall under the condition of a mass flow rate of 0.227 kg/s. Wang et al [50] found that a higher RDW velocity and a thicker deflagration region near the walls were caused by the higher wall temperature based on a two-dimensional numerical model, using hydrogen and air. Jorgensen et al [51] considered the thermal stress generated by the temperature gradient and optimized the structure of an RDC to minimize thermal mechanical stress.…”

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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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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“…There may be one or several rotating detonation waves (RDWs) moving tangentially in the RDE combustor [7]. Chemical reactions mainly occur inside the detonation wave, although there may still be deflagrative combustion near the walls [8] or between the reactants and products [9]. The rotating propagation and pressure-gain combustion together make the detonation wave continuous.…”

Section: Introductionmentioning

confidence: 99%

Combustion Characteristics in Rotating Detonation Engines

Wang

Qiao

JialingLe

2021

International Journal of Aerospace Engineering

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A lot of studies on rotating detonation engines have been carried out due to the higher thermal efficiency. However, the number, rotating directions, and intensities of rotating detonation waves are changeful when the flow rate, equivalence ratio, inflow conditions, and engine schemes vary. The present experimental results showed that the combustion mode of a rotating detonation engine was influenced by the combustor scheme. The annular detonation channel had an outer diameter of 100 mm and an inner diameter of 80 mm. Air and hydrogen were injected into the combustor from 60 cylindrical orifices in a diameter of 2 mm and a circular channel with a width of 2 mm, respectively. When the air mass flow rate was increased by keeping hydrogen flow rate constant, the combustion mode varied. Deflagration and diffusive combustion, multiple counterrotating detonation waves, longitudinal pulsed detonation, and a single rotating detonation wave occurred. Both longitudinal pulsed detonation and a single rotating detonation wave occurred at different times in the same operation. They could change between each other, and the evolution direction depended on the air flow rate. The operations with a single rotating detonation wave occurred at equivalence ratios lower than 0.60, which was helpful for the engine cooling and infrared stealth. The generation mechanism of longitudinal pulsed detonation is developed.

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The effect of the throat width of plug nozzles on the combustion mode in rotating detonation engines

Wang

et al. 2018

Shock Waves

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Effects of thermal wall conditions on rotating detonation

Cited by 20 publications

References 16 publications

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

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

Combustion Characteristics in Rotating Detonation Engines

The effect of the throat width of plug nozzles on the combustion mode in rotating detonation engines

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