Computational investigation on combustion instabilities in a rocket combustor

Yuan, Lei; Shen, Chibing

doi:10.1016/j.actaastro.2016.06.015

Cited by 19 publications

(5 citation statements)

References 25 publications

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“…A proposed heat flux profile agreed with the experimental data. They also demonstrated acoustic oscillation modes and frequencies using proposed simulations which almost agreed with classic acoustic analysis [21]. Yuan et al also simulated a large eddy in a combustion instability in a tri-propellant air heater to predict self-excited transverse oscillations.…”

Section: Literature Survey Of the Combustion Instabilitysupporting

confidence: 57%

“…For this reason, correlations in the overall behavior of the combustion instability were studied in detail. In addition, a proposed new process that is to predict the acoustic oscillation modes and corresponding frequencies by current simulations was identified in the simulation and compared to previous investigations [21].…”

Section: Literature Survey Of the Combustion Instabilitymentioning

confidence: 99%

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A Real-Time Combustion Instability Simulation with Comprehensive Thermo-Acoustic Dynamic Model

et al. 2018

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The thermo-acoustic instability in the combustion process of a gas turbine is caused by the interaction of the heat release mechanism and the pressure perturbation. These acoustic vibrations cause fatigue failure of the combustor and decrease the combustion efficiency. This study aims to develop a segmented dynamic thermo-acoustic model to understand combustion instability of a gas turbine. Then, the combustion instability was designed using the acoustic heat release model, and the designed instability model was segmented using the finite difference method, to evaluate the characteristics of flame propagation at each node. The combustion instability model was validated using experimental data to verify the instability amplitude. Also, the optimal node number was determined using the adiabatic flame temperature response. 10 nodes were selected in this study. A sensitivity analysis showed the predicted instability amplitude decreased when the nodes increased until node 4, due to heat generation. However, above 4 nodes the amplitude decreased, since the combustion outlet was directly connected to the ambient. As a result, the segmented combustion instability model was able to evaluate the flame propagation characteristics more accurately and found the largest area of instability was near the flame area.

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Section: Literature Survey Of the Combustion Instabilitysupporting

confidence: 57%

Section: Literature Survey Of the Combustion Instabilitymentioning

confidence: 99%

A Real-Time Combustion Instability Simulation with Comprehensive Thermo-Acoustic Dynamic Model

et al. 2018

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“…Distance from the pressure sensor to the nozzle axis is 1.6 m. Sizes of the T-burner and grain, propellant and BP properties are shown in Table 1. Length of the T-burner is 3.4 m, volume was 0.0216 m 3 , and area of nozzle throat is 1.81×10 -5 m 2 . Burning rate of the propellant can be calculated by the exponential burning rate formula, which is expressed as r =4.12p 0.25 mm/s (where, the unit of p is MPa).…”

Section: Pulse Excitation Experiments In a T-burnermentioning

confidence: 99%

“…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].…”

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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“…The detached eddy simulation (DES) method was developed in recent years and has been used to the prediction of combustion instability because its advantages in the computational efficiency of Reynolds-averaged Navier-Stokes (RANS) and high accuracy of LES. Yuan et al [6] captured self-exciting high-frequency combustion instability in a rocket engine combustion chamber by the two-dimensional DES technique and verified the existence of self-exciting high-frequency combustion instability.…”

Section: Introductionmentioning

confidence: 99%

Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant

Gao¹,

Zhang

Cheng

et al. 2022

Aerospace

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Combustion instability is the biggest threat to the reliability of liquid rocket engines, whose prediction and suppression are of great significance for engineering applications. To predict the stability of a combustion chamber with a hypergolic propellant, this work used the method of decoupling unsteady combustion and acoustic system. The turbulence is described by the Reynolds-averaged Navier–Stokes technique, and the interaction of turbulence and chemistry interaction is described by the eddy-dissipation model. By extracting the flame transfer function of the combustion field, the eigenvalues of each acoustic mode were obtained by solving the Helmholtz equation, thereby predicting the combustion stability for the combustion chamber. By predictions of the combustion chamber instability with different flow rate distributions, it was found that the increasing of inlet flow rate amplitude will improve the stability or instability of combustion. The combustion stability of the chamber was optimized when the flow rate distribution for the oxidant was set more uniform in the radial direction. The heterogeneity of the flow rate distribution in the circumferential direction is not recommended, considering that a homogeneous flow rate distribution in the circumferential direction is beneficial to the combustion stability of the chamber.

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Computational investigation on combustion instabilities in a rocket combustor

Cited by 19 publications

References 25 publications

A Real-Time Combustion Instability Simulation with Comprehensive Thermo-Acoustic Dynamic Model

A Real-Time Combustion Instability Simulation with Comprehensive Thermo-Acoustic Dynamic Model

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

Influence of Flow Rate Distribution on Combustion Instability of Hypergolic Propellant

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