Analysis of combustion instability via constant volume combustion in a LOX/RP-1 bipropellant liquid rocket engine

Zhang, Huiqiang; Ga, YongJing; Wang, Bing; Wang, Xiaohao

doi:10.1007/s11431-012-4743-7

Cited by 12 publications

(6 citation statements)

References 21 publications

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“…Pressure waves cannot propagate to the surrounding control volumes in this short period, which leads to a high-amplitude increase of pressure, namely, pressure spikes. These results are also supported by the work of Keenan et al [48], Zhang et al [44], Grenda et al [50], and Daimon et al [51], which indicates violent combustion (bombing) may occur in LRE. Keenan et al [48] found that injecting the LOX and RP-1 droplets along the same vector in a given angel to mimic fan atomization may trigger self-excited instabilities, because the LOX and RP-1 droplets can interact more rapidly.…”

Section: The Instability Phenomenonsupporting

confidence: 73%

“…The standard k − ε two-equation turbulence model is used. The governing equations of mass, momentum, energy, species mass fraction, turbulence kinetic energy, and turbulent dissipation can be expressed in the unified form [44]:…”

Section: Numerical Modelmentioning

confidence: 99%

“…S pφ and S cφ are the source terms determined by droplet vaporization and chemical reaction. The detailed variables are presented in Reference [44].…”

Section: Numerical Modelmentioning

confidence: 99%

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Numerical Analysis of Self-Excited Combustion Instabilities in a Small MMH/NTO Liquid Rocket Engine

Qin

Zhang

2020

International Journal of Aerospace Engineering

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Combustion instabilities in a small MMH/NTO liquid rocket engine used for satellite attitude and course control are numerically investigated. A three-dimensional Navier-Stokes code is developed to simulate two-phase spray combustion for cases with five different droplet Sauter Mean Diameters. As the droplet size increases from 30 microns to 80 microns, pressure oscillations are stronger with larger amplitudes. But an increase of the droplet size in the range of 80 microns to 140 microns indicates a reduction in the amplitudes of pressure oscillations. This trend is the same as the Hewitt criterion. The first tangential (1T) mode and the first longitudinal (1L) mode self-excited combustion instabilities are captured in the 60-micron and 80-micron cases. Abrupt spikes occur in the mass fraction of MMH and coincide with abrupt spikes in the mass fraction of NTO at the downstream regions just adjacent to the impinging points. Thus, local combustible high-dense mixtures are formed, which result in quasiconstant volume combustion and abrupt pressure spikes. The propagation and reflection of pressure waves in the chamber stimulate the combustion instability. When the droplet size is too small or too large, it is difficult to form local high-dense premixtures and combustion is stable in the chamber.

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Section: The Instability Phenomenonsupporting

confidence: 73%

Section: Numerical Modelmentioning

confidence: 99%

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Numerical Analysis of Self-Excited Combustion Instabilities in a Small MMH/NTO Liquid Rocket Engine

Qin

Zhang

2020

International Journal of Aerospace Engineering

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“…Combustion instability is a thorny problem in motors [1][2][3]. Its fundamental characteristics are the periodic oscillations of pressure, burning rate and thrust [4]. For a solid rocket, the oscillations in motors could be induced by complex mechanisms, such as pressure-coupled response [5], vortex-acoustic coupling [6], distributed combustion [7], et al Combustion instability typically includes linear state and nonlinear state.…”

Section: Introductionmentioning

confidence: 99%

Experimental and theoretical study on characteristics of pulse excitation in T-burners

Yan

Wang

et al. 2017

Acta Astronautica

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Pulse excitation is the key to measure the pressure-coupling response function of composite propellant. It is also a key trigger factor for nonlinear combustion instability. This paper aims at understanding characteristics of pulse excitation in T-burners. Pulse excitation is provided by black powder (BP). D 2 law is used to calculate BP burning properties. Firstly, the experimental pressure history of a pulse excitation is analyzed. Pressure pulse and mean pressure increment are introduced to describe pulse excitation. Secondly, the modified zero-dimension model and one-dimension model of pressure pulse are established based on energy conservation and modification. The results of models indicate that the modified zero-dimensional model can accurately predict the pressure pulse. The modified zero-dimension model demonstrates that the pressure pulse is determined by pulse build-up time threshold, volume coefficient, effective weight fraction of BP, weight of BP et. al. When burning time of BP is larger than the threshold, volume coefficient is equal to 2, and effective weight fraction of BP is less than 1. The pressure pulse is approximately linear correlation with weight and effective weight fraction of BP. Otherwise, volume coefficient is larger than 2, and effective weight fraction of BP is equal to 1. The pressure pulse is approximately linear correlation with volume coefficient and BP weight. Thirdly, a zero-dimensional prediction model of mean pressure is established based on conservations of energy and mass. The prediction models of pressure pulse and mean pressure are validated by T-burner experiments. Finally, effects of BP burning properties on pressure pulse and mean pressure increment are studied. The results show that both pressure pulse and mean pressure increment increase with increasing BP weight, linearly. The pressure pulse is more sensitivity to the variations of burning time of BP. As burning time of BP decreases, the mean pressure increment gradually increases to the maximum, and the pressure pulse can become a very large value.

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“…In the scramjet engine (Qin et al, 2012), it is necessary to promote the mixing process between the fuel and the supersonic crossflow before ignition, and thus enhance combustion efficiency (Wang et al, 2011a;Zhang et al, 2012). In the past decades, many fuel injection schemes have been proposed for scramjet engines (Takahashi et al, 2010b;Huang et al, 2011a;2013c;Yang et al, 2011;, especially using a cantilevered ramp injector design as the inlet injector (Huang et al, 2013c) and the transverse injection scheme which has been widely employed in the scramjet combustor (Cecere et al, 2011).…”

Section: Introductionmentioning

confidence: 99%

Progress in research on mixing techniques for transverse injection flow fields in supersonic crossflows

Huang

Yan

2013

J. Zhejiang Univ. Sci. A

111

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The transverse injection flow field has an important impact on the flowpath design of scramjet engines. At present a combination of the transverse injection scheme and any other flame holder has been widely employed in hypersonic propulsion systems to promote the mixing process between the fuel and the supersonic freestream; combustion efficiency has been improved thereby, as well as engine thrust. Research on mixing techniques for the transverse injection flow field is summarized from four aspects, namely the jet-to-crossflow pressure ratio, the geometric configuration of the injection port, the number of injection ports, and the injection angle. In conclusion, urgent investigations of mixing techniques of the transverse injection flow field are proposed, especially data mining in the quantitative analytical results for transverse injection flow field, based on results from multi-objective design optimization theory.

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Analysis of combustion instability via constant volume combustion in a LOX/RP-1 bipropellant liquid rocket engine

Cited by 12 publications

References 21 publications

Numerical Analysis of Self-Excited Combustion Instabilities in a Small MMH/NTO Liquid Rocket Engine

Numerical Analysis of Self-Excited Combustion Instabilities in a Small MMH/NTO Liquid Rocket Engine

Experimental and theoretical study on characteristics of pulse excitation in T-burners

Progress in research on mixing techniques for transverse injection flow fields in supersonic crossflows

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