Experimental investigations on ethylene-air Continuous Rotating Detonation wave in the hollow chamber with Laval nozzle

Peng, Haoyang; Liu, Weidong; Liu, Shijie; Zhang, Hailong

doi:10.1016/j.actaastro.2018.06.025

Cited by 68 publications

(6 citation statements)

References 18 publications

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“…Among the past studies on detonation in HCCs, similarities between RDWs and the tangential combustion instability of an LRE have been mentioned [21]. Recent progress on this topic has been to investigate the feasibility of detonation in an HCC with a Laval nozzle [17] and analyze the relationship of RDWs and tangential combustion instability of an LRE based on their frequency [20,28]. From the perspective of combustion instability, 1T and 2T intrinsic acoustic frequencies (i.e., 6.24 and 10.34 kHz) of the HCC can be calculated from intrinsic acoustic frequency formula f m00 c∕2α m0 ∕R out [20], respectively, where c is computed from the initial state parameters of the H 2 -air mixture (P 0 90 kPa, T 0 288 K); the value of α m0 is the mth root of the zero-order Bessel function, 0.5861 and 0.9722 for the first-order and secondorder tangential acoustic frequencies, respectively.…”

Section: Resultsmentioning

confidence: 99%

“…On the contrary, experimental observation demonstrated a shift from the dual-wave mode to the single-wave mode in H 2 -air propellant [14], which are two distinct mechanisms relating to the formation of RDWs in an HCC under atmospheric ambient pressure with different injection conditions [15,16]. Moreover, the Laval nozzle with optional contraction ratios [17], hydrocarbon fuel [14,17], and contrasting injection area ratio [4,13] make the stability of RDW more diverse and complicated. As for the thrust performance, simulation results reported that the absence of the inner wall does not hinder the thrust performance of RDEs [18].…”

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confidence: 99%

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Propagation Mode Analysis on H2–Air Rotating Detonation Waves in a Hollow Combustor

Lin¹,

Tong²,

Lin

et al. 2020

AIAA Journal

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Section: Resultsmentioning

confidence: 99%

mentioning

confidence: 99%

Propagation Mode Analysis on H2–Air Rotating Detonation Waves in a Hollow Combustor

Lin¹,

Tong²,

Lin

et al. 2020

AIAA Journal

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“…In addition, the collision of waves also contributes to the great velocity deficit. and μ = S/f , where S is standard deviation, N is the number of propagation cycles, and μ is relative standard deviation [29]. The propagation stability is negatively correlated with the combustor width in different CRD propagation modes.…”

Section: Effects Of Combustor Widthmentioning

confidence: 99%

“…The CRD wave propagated in single wave mode with relatively high velocity at 1647.92 m/s. Furthermore, Peng et al [29] achieved ethylene-air CRD with large operating range and low velocity deficit in the hollow combustor with a Laval nozzle. The highest propagation velocity reached 1915.4 m/s in single wave mode.…”

Section: Introductionmentioning

confidence: 99%

Effects of Annular Combustor Width on the Ethylene-Air Continuous Rotating Detonation

Fan

Liu

Zhang

et al. 2020

International Journal of Aerospace Engineering

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The realization and stable operation of Continuous Rotating Detonation (CRD) in the annular combustor fueled by hydrocarbon-air are still challenging. For further investigation of this issue, a series of ethylene-air CRD tests with the variation of combustor width is conducted, and the effects of combustor width are well analyzed based on high-frequency pressure and high-speed photograph images. The results show that the combustor width plays a significant role in the realization and sustainability of the ethylene-air CRD. In this paper, the critical combustor width for the CRD realization and stable single wave are 20 mm and 25 mm, respectively. In wide combustors, the backward-facing step at the combustor forepart makes the main flow slow down, and thus, the mixing quality is promoted. Besides, the pilot flame at the recirculation zone contributes to sustaining the CRD wave. As the width increases, the propagation mode changes from counter-rotating two-wave mode to single wave mode with higher propagation velocity and stability. The highest propagation velocity reaches 1325.56 m/s in the 40 mm wide combustor, accounting for 71.51% of the corresponding Chapman-Jouguet velocity. Despite large combustor volume, high combustor pressure is obtained in detonation combustion mode indicating that a better propulsive performance could be achieved by CRD.

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“…Currently, gaseous fuels were generally used in the studies of the hollow RDC. Wang et al (2018), Peng et al (2018), andPeng et al (2019) obtained the single-and double-rotating detonation wave in the experiments based on hydrocarbon fuels such as methane and ethylene. Analyzing the rotating detonation propagation modes, the range of stable operating conditions is significantly smaller due to the worse detonation of methane.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Two-Phase Rotating Detonation Fueled by Kerosene in a Hollow Directed Combustor

Xue

Ying²,

Ma³

et al. 2022

Front. Energy Res.

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The operating characteristic of two-phase rotating detonation fueled by kerosene in a hollow combustor with the isolation section is experimentally studied. When the air mass flow rate is 1.5 kg/s, the equivalence ratio is 0.98, and the total temperature of the mixture is 650 K, the stable rotating detonation wave (RDW) is obtained, which verifies the feasibility of the designed two-phase rotating detonation combustor (RDC). It is found that there is a high-frequency oblique shock induced by the upstream rotating detonation wave in the isolation section. A series of experimental tests have been carried out by changing the total temperature of incoming air , which is an important factor affecting the initiation. When the equivalent ratio of reactants is between 0.950–1.152, a stable single-wave detonation is formed. With the increase of equivalent ratio, the time of detonation wave establishment decreases, the intensity and frequency of detonation wave increases, and the temperature of engine tail flame rises. The equivalent chamber pressure Δpφ was defined, and the curve of the performance of the RDC with the equivalent ratio was obtained. The velocity of the RDW increases with the increase of equivalent ratio, and the chamber pressure has an optimal value, a higher or lower equivalent ratio will lead to the decrease of equivalent chamber pressure and the combustion chamber performance.

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Experimental investigations on ethylene-air Continuous Rotating Detonation wave in the hollow chamber with Laval nozzle

Cited by 68 publications

References 18 publications

Propagation Mode Analysis on H2–Air Rotating Detonation Waves in a Hollow Combustor

Propagation Mode Analysis on H2–Air Rotating Detonation Waves in a Hollow Combustor

Effects of Annular Combustor Width on the Ethylene-Air Continuous Rotating Detonation

Experimental Investigation on Two-Phase Rotating Detonation Fueled by Kerosene in a Hollow Directed Combustor

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