Experimental verification of air-breathing continuous rotating detonation fueled by hydrogen

Wang, Chao; Liu, Weidong; Liu, Shijie; Jiang, Luxin; Lin, Zhiyong

doi:10.1016/j.ijhydene.2015.05.060

Cited by 60 publications

(9 citation statements)

References 23 publications

(27 reference statements)

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“…Figure 18(a) compares the calculated pressure history (solid curve) with the record of high-frequency pressure sensor (dashed curve) reported in Ref. 48 as the record of PCB1 sensor (see Figure 17(a)). Since high-frequency pressure sensors of PCB type detect the level of local instantaneous pressure pulsations rather than the absolute pressure level, the experimental curve in Figure 18(a) is shifted to fit the absolute pressure level ahead of the DW in the calculated signal.…”

Section: Computational Fluid Dynamics Code Verificationmentioning

confidence: 97%

“…24,25. As a reference for further code verification, we used the results reported in Ref. 48 for a hydrogen-air RDE of simple design (Figure 17(a)). Experiments in Ref.…”

Section: Computational Fluid Dynamics Code Verificationmentioning

confidence: 99%

“…Experiments in Ref. 48 were performed in an annular RDE 108 mm in outer diameter and 210 mm long with an annular gap 14 mm wide. Air was supplied to the RDE with a flow rate of 0.6 kg/s with a local Mach number of 2.0 and with stagnation temperature and pressure of 860 K and 860 kPa, respectively.…”

Section: Computational Fluid Dynamics Code Verificationmentioning

confidence: 99%

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Pressure measurements in detonation engines

Иванов

Фролов

Sergeev

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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The influence of waveguide tubes on the signals received by remote pressure sensors measuring pressure histories in pulsed detonation engines (PDEs) and rotating detonation engines (RDEs) is studied computationally. Two types of pressure sensors are considered: low-frequency static pressure sensors and high-frequency sensors of pressure pulsations. Three approaches to solving the problem are used: based on Euler (inviscid flow), Navier–Stokes (laminar flow), and unsteady Reynolds-averaged Navier–Stokes (turbulent flow) equations. The approaches based on the inviscid and laminar flow models are shown to provide the best predictive capability. The laminar flow model is applied to analyzing the readings of pressure sensors installed remotely in the waveguide tubes attached to the hydrogen-fueled PDE, RDE, and detonation ramjet (DR). It is shown that the measurements of static pressure and pressure pulsations by remote pressure sensors do not correspond to the time-averaged mean and local instantaneous values of pressure in the combustors. The pressure time histories can be recovered based on the measurements and computational fluid dynamics calculations of the operation process. The latter is demonstrated by analyzing the results of test fires with a dual-duct DR model.

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Section: Computational Fluid Dynamics Code Verificationmentioning

confidence: 97%

“…24,25. As a reference for further code verification, we used the results reported in Ref. 48 for a hydrogen-air RDE of simple design (Figure 17(a)). Experiments in Ref.…”

Section: Computational Fluid Dynamics Code Verificationmentioning

confidence: 99%

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Pressure measurements in detonation engines

Иванов

Фролов

Sergeev

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Some researchers have used high-temperature air as an oxidant to study the propagation characteristics of RDW. Wang et al (2015) first realised air-breathing rotating detonation fuelled by hydrogen at a total temperature of 860 K in a direct-connect experimental facility. Frolov et al (2018) performed a series of firing tests of a hydrogen-fuelled detonation ramjet model in a pulsed wind tunnel at an approach-airstream Mach number of 5.7 and a stagnation temperature of 1500 K. It was found that the operation mode of the combustor changed from rotating detonation to longitudinal pulse detonation with an increase in equivalence ratio.…”

Section: Introductionmentioning

confidence: 99%

Experimental Research of Two-phase Rotating Detonation Combustor Operating with High Total Temperature Air

2022

JAFM

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Experiments on a two-phase rotating detonation combustor operating with gasoline and high total temperature air were conducted to investigate the initiation characteristics, operation mode, and propagation characteristics of a two-phase rotating detonation wave (RDW). The outer diameter, inner diameter, and length of the annular combustor were 204 mm, 166 mm, and 155 mm, respectively. The initiation characteristics, operation mode, and propagation characteristics of the two-phase RDW were studied by varying the total air temperature. The experimental results show that the initiation time of the RDW first decreases and then increases with an increase in the total air temperature and reaches an extreme value at a total air temperature of 713 K. Four operation modes (failure, intermittent detonation, single wave, coexistence of double wave collision, and single wave) of the detonation combustor were found for different total air temperatures. The effect of the total air temperature on the peak pressure stability and propagation frequency of the RDW was studied in detail. From the results, the effect of the equivalence ratio on the working characteristics of a rotating detonation engine (RDE) was investigated at a total air temperature of 713 K. Four detonation propagation modes (sporadic detonation, intermittent detonation, single-wave mode, coexistence of double-wave collision and single wave) were obtained in the combustor. When the equivalence ratio was 0.52, the detonation initiation failed. The pressure characteristics in the combustor and propagation frequency of the RDW were studied with different equivalence ratios. In addition, a long-duration test was performed for 3 s to verify the continuous working feasibility of the two-phase RDE.

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“…LFI in an RDC seems to be almost ubiquitous. A brief analysis of the pressure-time traces published by the different RDC facilities worldwide gives concrete evidence of the overarching existence of this instability [13,15,[18][19][20][21][22][23][24][25][26][27]. However, most studies have not made an effort to address either the existence, or the mechanism behind LFI.…”

Section: Introductionmentioning

confidence: 99%

Types of Low Frequency Instabilities in Rotating Detonation Combustors

Anand

Gutmark

2018

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Rotating detonation combustors (RDC) offer a significant prospective increase in stagnation pressure across it owing to the presence of one or more rotating detonation waves spinning inside the combustor at the kilohertz regime. Naturally, considerable research impetus has been directed towards this technology in recent years to understand the driving mechanics to harness the associated potential of pressure gain combustion (PGC). One such area of focus has been the off-design operating modes of these devices which cause a myriad of instabilities. The current paper is focused towards the discussion of one such instability regime-low frequency instabilities (LFI)-in RDCs. We review three types of LFIs in RDCs based on prior findings, and propose mechanisms for the same.

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Experimental verification of air-breathing continuous rotating detonation fueled by hydrogen

Cited by 60 publications

References 23 publications

Pressure measurements in detonation engines

Pressure measurements in detonation engines

Experimental Research of Two-phase Rotating Detonation Combustor Operating with High Total Temperature Air

Types of Low Frequency Instabilities in Rotating Detonation Combustors

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