Flow and thermal analyses of regenerative cooling in non-uniform channels for combustion chamber

Jing, Tingting; He, Guoqiang; Li, Wenqiang; Qin, Fei; Wei, Xianggeng; Liu, Yang; Hou, Zhiyuan

doi:10.1016/j.applthermaleng.2017.03.062

Cited by 44 publications

(5 citation statements)

References 16 publications

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“…In Equation (3), considering that the flow velocity (relative to local sound speed, about 1500 m/s) in this paper is relatively low, the terms related to viscous dissipation are ignored. The buoyancy effect can be determined by the formula [21] Bo = Gr/Re 3:425 Pr 0:8 . When Bo is less than 5:6 × 10 −7 , it can be ignored.…”

Section: Modelmentioning

confidence: 99%

“…The effects of the coupling effect of flow cracking on the heat sink of fuel, heat, and mass transfer mechanism of the chemical reaction flow field and flow field optimization of local special cooling structures in cooling channels were studied. Jing [21] proposed several different nonuniform regenerative cooling channel structures and used numerical simulation to analyze the influence of inlet and outlet structures and relative inlet and outlet widths on flow and heat transfer characteristics in channels. Their results demonstrated that when Ω = 1, violent nonuniform flow exists in the channel near the inlet pipe, and the flow distribution is more sensitive to the inlet position than to the outlet position.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Effect of Cooling Header on the Hydrocarbon Fuel Flow Distribution in a Regenerative Cooling Channel

Yin

Jiaqiang

Ding

2022

International Journal of Aerospace Engineering

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Regenerative cooling technology is the most widely used cooling technology in liquid rocket engines, and flow distribution is very important for regenerative cooling heat transfer. In this work, the flow distribution characteristics of Z -type parallel channels were studied through numerical simulation, and the effects of flow area ratio, inlet header shape, and inlet aspect ratio were analyzed. Results showed that changing the inlet cooling header can improve the uniform distribution of flow rate effectively. The nonuniformity coefficient and fuel temperature varied with change in the flow area ratio, inlet header shape, and inlet aspect ratio. The maximum temperature of the wall decreased from 1334.52 K to 1220.61 K when the flow area ratio was changed from 1 to 0.25. An appropriate decrement in the inlet header shape was beneficial to the uniform flow distribution. The inlet aspect ratio should be reduced properly to ensure that each channel experiences similar pressure drop. This research has a certain reference value for the structural design of regenerative cooling channels.

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Section: Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Effect of Cooling Header on the Hydrocarbon Fuel Flow Distribution in a Regenerative Cooling Channel

Yin

Jiaqiang

Ding

2022

International Journal of Aerospace Engineering

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“…In a study by Liu [88], the thermal structure of the cooling front of the cooling channel of an endothermic hydrocarbon-cooled scramjet was analyzed, the thermal/stress distribution of the aircraft under steady flight conditions was classified by finite element software (see Figure 24), and the feasibility of the materials of C-103/Na and T-111/Li was demonstrated. Jing et al [89] proposed a regenerative cooling channel designed by various non-uniform patterns, and numerically investigated the conjugate flow and heat transfer behavior between the coolant and solid combustion chamber. In a study by Taddeo [90], the effect of fuel cooling on the combustion chamber was explored, the heat transfer efficiency of the cooling system was evaluated, and the hysteresis effect caused by heat transfer kinetics was demonstrated as well.…”

Section: Low-temperature Systemsmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

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“…Therefore, the telescopic wing structure requires the ability of thermal protection and load-bearing simultaneously.Thermal protection has become one of the bottleneck problems restricting high-speed aircraft development. 11 At present, the thermal protection system of high-speed aircraft is mainly divided into active, 12,13 semi-active, 14,15 and passive type. 16,17 Active and semi-active cooling techniques have excellent thermal protection performance, but the relatively complex structure and unsatisfactory reusability preclude their application to the telescopic wing.…”

Section: Introductionmentioning

confidence: 99%

Design and analysis of thermal protection and load-bearing integrated structure of the telescopic wing

Xiao,

Guo,

et al. 2023

Advances in Mechanical Engineering

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A novel three-layer integrated structure was designed to meet the thermal-insulation and load-bearing requirements of high-speed telescopic wing aircraft. The structure consists of heat shield layer, load-bearing skeleton, and pyramid lattice structure filled with aerogel to achieve the insulation function. Sensitivity analysis of the design parameters and optimal design of the integrated structure was carried out, and the structure was optimized by using response surface method. Compared to the initial structure, the optimized structure has an equivalent thermal conductivity of 0.0276, reduced by 40%, and a relative density of [Formula: see text], reduced by 3.7%. And it has a thermal conductivity that is over 20% lower than that of ceramic insulating tiles. Then, the integrated structure was regarded as a homogeneous plate, and the equivalent mechanical and thermal parameters were determined and verified by simulation and experimental results. The equivalence error was controlled within 10%. Finally, a simulation model of the telescopic wing was established. The result shows that the maximum deformation under 20 kPa surface pressure is 3.96 mm. The temperature resistance of the structure surface is up to 1500°C, and the wing internal temperature is controlled within 200°C after 1200 s of thermal loading. The results verified that the integrated structure meets the requirement of a high-speed telescopic wing.

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Flow and thermal analyses of regenerative cooling in non-uniform channels for combustion chamber

Cited by 44 publications

References 16 publications

Effect of Cooling Header on the Hydrocarbon Fuel Flow Distribution in a Regenerative Cooling Channel

Effect of Cooling Header on the Hydrocarbon Fuel Flow Distribution in a Regenerative Cooling Channel

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Design and analysis of thermal protection and load-bearing integrated structure of the telescopic wing

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