The effect of mixing and heat transfer on regression rate of TAGN-based fuel in a segregated AP/TAGN solid motor

Liu, Shuyuan; Wang, Limin; Han, Luyang; Chen, Zhengchun; Hu, Songqi

doi:10.1016/j.ijthermalsci.2022.108133

Cited by 3 publications

(4 citation statements)

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“…However, most current research studies used global reaction mechanisms and a steady combustion model. The temporal and spatial distribution characteristics of heat release of the coupled combustion process of the SOFSM system under mixing and heat transfer are rarely reported [26,27]. The coupled heat release and transfer characteristics are obtained with the dynamic mesh technique in the present study.…”

Section: Introductionmentioning

confidence: 91%

“…In the present numerical simulation, the method of equivalent source term [26,27] is used to describe the thermal decomposition of the fuel-rich propellant. The pyrolysis model of the rich fuel is shown in Figure 2.…”

Section: Thermal Decomposition Model Of Propellantmentioning

confidence: 99%

“…The propellant combination used in this study includes AP oxygen-rich gas as an oxidizer and TAGN fuel-rich as fuel. The composition of the AP/TAGN propellants can be found in our previous studies [26,27]. The present study used a mechanism involving 190 elementary reactions and 37 inlet components from a previous study [26].…”

Section: Detailed Reaction Mechanismmentioning

confidence: 99%

“…In addition, r O/F is 0.5 repre-senting adequate mixing of oxidizer and fuel gas. The detailed definitions of mixing degree and oxidizer richness index can be found in our previous study [27]. Either the smaller or larger value of the oxidizer richness index means incomplete combustion.…”

Section: Flow and Heat Transfer Characteristicsmentioning

confidence: 99%

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Evaluation of Mixing Effect on Coupled Heat Release and Transfer Performance of a Novel Segregated Solid Rocket Motor

Liu,

Zhang,

Wang

et al. 2024

Aerospace

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The effect of mixing on coupled heat release and transfer performance of a novel segregated solid motor is numerically evaluated with a transient two-dimensional combustion model. The results show that vortex structures are formed and evolved in the combustion chamber. Quantitative calculation of the mixing effect shows the inhomogeneous distribution of oxidant and fuel species. The well-mixing area is located in a narrow belt-like coupled combustion region near the burning surface of the propellant. Heat transfer coefficient decreases greatly due to lower combustion reaction rate and enlarged flow channel area. Heat transfer coefficients near the two ends of the propellant grain are higher than other parts due to the influence of vortex mixing. Raising the inlet mass flow rate leads to enhanced mixing and heat transfer, which results in a lower temperature and regression rate of the propellant with combustion time. Temperature and oxidation rates of H2 and CO are unevenly distributed in the boundary layer of coupled combustion. Increasing the mass flux of inlet oxidizer gas leads to a higher combustion heat release rate. Therefore, the gas-phase temperature increases significantly. The heat release rate reaches the maximum near the ends of the propellant grain, where vortex mixing strengthens the coupled combustion process in the motor.

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Section: Introductionmentioning

confidence: 91%

Section: Thermal Decomposition Model Of Propellantmentioning

confidence: 99%