Modeling and analysis of triggering pulse to thermoacoustic instability in an end-burning-grain model solid rocket motor

Ji, Shixiang; Wang, Bing

doi:10.1016/j.ast.2019.105409

Cited by 24 publications

(3 citation statements)

References 37 publications

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“…For simulations over short periods of time, it is reasonable to maintain a constant propellant geometry (i.e., keeping the propellant thickness unchanged) while performing flow field and structural computations. It has been proven that, using this quasi-steady approach, reliable simulation results for the transient phenomena in SRMs could be obtained and considerable computational time could be saved [30]. According to the parallel combustion law, three propellant thicknesses, namely, 9/10, 1/2, and 1/10, of the initial propellant thickness (35 mm, as given in Table 1), are examined, representing the burning surface transient conditions at different burning instants (Figure 2).…”

Section: Physical Model and Initial Settingsmentioning

confidence: 99%

“…Greatrix and Harris [28][29][30] argued that severe SRM instabilities are caused by the coupling of structural vibrations and acoustic oscillations. Thus, the investigation of the relationship between the natural frequencies of the structure and acoustics is of great significance to reveal the mechanism behind SRM instability.…”

Section: Effects Of Aerodynamic Heating and Fixed Constraints On Stru...mentioning

confidence: 99%

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Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Wang,

Li,

et al. 2024

Aerospace

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A solid rocket motor (SRM) with a high aspect ratio that performs normally during ground tests may experience instability during flight. To address this issue, this study employs the pulse triggering method and the numerical approach of two-way fluid–structure interaction to investigate the mechanisms behind the SRM instability resulting from distinctions between on-ground and in-flight conditions. The results indicate that the main distinctions between the on-ground and in-flight conditions for SRMs are the strong constraints during the ground test, as well as aerodynamic forces and aerodynamic heating during flight. The strong constraints in the ground test effectively suppress structural vibrations by limiting displacements. In flight conditions, the aerodynamic heating reduces the strength of the SRM casing and aerodynamic forces provide sustained energy input for structural vibrations during flight. The mechanism for the ground/flight differences that induce SRM instability is that the structural natural frequencies are reduced by aerodynamic heating and the first-order acoustic frequency increased by the propellant regression approach reaches the resonance condition. Therefore, an instability factor Φ is proposed to represent the resonance relationship between the structural natural modes and the acoustic mode of SRMs. Furthermore, the closer the frequency of the aerodynamic forces is to the resonance frequency of the acoustic-structure coupling, the more pronounced the SRM instability.

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Section: Physical Model and Initial Settingsmentioning

confidence: 99%

Section: Effects Of Aerodynamic Heating and Fixed Constraints On Stru...mentioning

confidence: 99%

Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Wang,

Li,

et al. 2024

Aerospace

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“…In addition, some scholars also improve the combustion instability by adjusting the fuel supply strategy and changing the temperature pattern in the combustor. Compared to gas turbines, rocket engines encountered combustion instability earlier, the mechanisms of which and suppression methods in solid and liquid rocket engines have been studied by many scholars (Ji et al 2020;Xue et al 2020;Nguyen and Sirignano 2019;Ji and Wang 2019;Wang et al 2020;Sehgal and Strand 1964). With the investigation of rocket combustion chambers, it has been discovered that aluminum preparation affects the distribution of flame surface in the combustion process and plays important roles in restraining combustion instability (Povinelli 1967;Price 1971).…”

Section: Introductionmentioning

confidence: 99%

Experimental Studies on Suppression of Combustion Instability with the Addition of Helium

2022

JAFM

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When combustion instability occurs, fluctuation in the release of heat couples with oscillating pressure, while the sensitivity of flame to acoustic disturbance restricts the oscillation intensity. This paper investigates the efficacy of helium in suppressing combustion instability. The flame structure, its sensitivity to acoustic disturbance and the inhibition of oscillating pressure with the addition of helium were studied by means of open tests, external-excited and self-excited combustion instability experiments. First of all, the addition of helium made larger flame surface area, which shaped the distributed flame, and the heat was such released over a broader space. Then, the external-exited combustion instability experiments confirmed that adding helium to fuel could decrease the sensitivity of flame to acoustic disturbance. Finally, Helium was used in the case of self-excited combustion instability to further investigate its effectiveness on the oscillation suppression. Proper Orthogonal Decomposition (POD) and Dynamic Mode Decomposition (DMD) methods were used to study flame fluctuation intensity. The results showed that the amplitudes of oscillating pressure were greatly reduced by the added helium. For 250Hz mode, adding helium with 20% of fuel flow could significantly reduce the flame pulsation and reduce the pulsation pressure by more than half. However, for the 160hz mode, more helium should be added to achieve better results. When the helium flow exceeded 80% of fuel flow, the combustion instability could be converted to stable combustion.

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Analysis on Solid Rocket Motor Using Computational Method for Uniform Flow Field

Jadhav,

Mishra,

et al. 2024

Lecture Notes in Mechanical Engineering

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Modeling and analysis of triggering pulse to thermoacoustic instability in an end-burning-grain model solid rocket motor

Cited by 24 publications

References 37 publications

Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Experimental Studies on Suppression of Combustion Instability with the Addition of Helium

Analysis on Solid Rocket Motor Using Computational Method for Uniform Flow Field

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