An experimental investigation on transpiration cooling with phase change under supersonic condition

Shen, Lin; Wang, Jianhua; Dong, Wenjie; Pu, Jian; Peng, Jinlong; Qu, Dejun; Chen, Lianzhong

doi:10.1016/j.applthermaleng.2016.03.039

Cited by 69 publications

(10 citation statements)

References 24 publications

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“…The boundary conditions are shown in Table 2 setting according to the experimental data in references (Shen et al, 2016;Ding et al, 2020) to provide some conveniences for turbulence model validations.…”

Section: Boundary Conditions and Solvermentioning

confidence: 99%

“…Scholars have carried out some experimental and numerical studies on the application of transpiration cooling in hypersonic vehicles. Shen et al (2016) carried out transpiration cooling experiments using water as the coolant. The experimental results show that the cooling efficiency is the lowest in the stagnation zone where bears high aerodynamic heating and high stagnation pressure.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Effects of Coolants of Double Layer Transpiration Cooling System in the Leading Edge of a Hypersonic Vehicle

et al. 2021

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As a promising and efficient active cooling method, double layer transpiration cooling is introduced into the design of the cooling system in the leading edge of a hypersonic vehicle. The physical model is built combined with hypersonic transpiration cooling, film cooling, heat conduction, porous media heat conduction and convection heat transfer. In addition, effects of different kinds of coolants are considered to reveal cooling mechanisms in different operation conditions. A comprehensive turbulence model validation and mesh independence study are provided. Flow characteristics caused by flow impingement, separation, transition and interaction with the cooling flows are displayed and analyzed in the work. When different kinds of coolants supplied at the same mass flow rate, the coolants with low densities, i.e., H2 and He, have the lowest peak temperature compared with the coolants with large densities, i.e., N2 and CO2. The coolants with low densities have a large ejecting velocity which provides large kinetic energy to penetrate deeply in the porous media. In addition, when the ejecting velocity is large enough, a recirculation is formed in front of the leading edge and pushes the high temperature region located in stagnation region away from the leading edge. However, when the coolants are ejected at the same velocity, the coolants with large densities exhibit better cooling performance.

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Section: Boundary Conditions and Solvermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Effects of Coolants of Double Layer Transpiration Cooling System in the Leading Edge of a Hypersonic Vehicle

et al. 2021

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“…There has been increasing interest in applying the transpiration cooling to more challenging conditions of high speed flow among many researchers, and they have been successful in showing the effectiveness of the technique experimentally both with and without phase change involved [25][26][27][28][29]. The flow conditions and geometries involved vary widely, and the research involves mostly experimental work.…”

Section: Numerical Simulation Of Transpiration Cooling For Re-entry Ementioning

confidence: 99%

Modelling and Simulation of Transpiration Cooling Systems for Atmospheric Re-Entry

Bandivadekar

Minisci

2020

Aerospace

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Aerothermodynamic heating is one of the primary challenges faced in progressing towards reliable hypersonic transportation. In the present study, the transpiration cooling method applied to the thermal protection system of re-entry vehicles is investigated. The complexity in analysing the incoming heat flux for re-entry lies not only in the extreme conditions of the flow but also in the fact that the coolant flow through the porous medium needs to be treated appropriately. While the re-entering spacecraft passes through various flow regimes, the peak conditions are faced only near continuum regime. Focusing on these conditions, traditional computational fluid dynamics techniques are used to model transpiration cooling for re-entry vehicles. In the current work, the open source CFD framework OpenFOAM is used to couple two different solvers iteratively and then analyse the thermal response for flow speed conditions typical of re-entry vehicles. Independent computations are performed using the explicit, loosely coupled procedure for high speed argon flow over a 2D axi-symmetrical cylindrical vehicle. The results presented indicate distinct heat flux drop along the surface of the cylindrical vehicle as a function of parameters such as coolant pressure and wall temperature.

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“…Qian [13] used solid hydrogel as coolant and Wu [14] combined sublimation and transpiration cooling, to improve the cooling effect for porous plates. Foreest [15] and Wang et al [16,17] respectively observed and analyzed the ice formation on a nose cone under supersonic condition in the process of transpiration cooling with phase change. Jiang et al [6,18] studied a combined cooling method for porous struts and observed the bow shock waves in front of the struts.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on the Mechanism of Transpiration Cooling for Porous Struts Based on Local Thermal Non-Equilibrium Model

Yang

Bian

et al. 2022

Energies

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Struts as an important structure in the combustion chamber of hypersonic flight vehicles to inject fuel into main flow face a severe thermal environment. Transpiration cooling is considered as a potential method to provide a thermal protection for struts. This paper presents a numerical investigation on transpiration cooling for a strut based on Darcy–Forchheimer model and the local thermal non-equilibrium model and analyzes the mechanism of transpiration cooling. A coolant film and a velocity boundary layer are formed on the strut surface and the shock wave is pushed away from the strut, which can effectively reduce the heat load exerted on the strut. The temperature difference between coolant and solid matrix inside the porous strut is analyzed, a phenomenon is found that the fluid temperature is higher than solid temperature at the leading edge inside the porous strut. As flowing in the porous medium, the coolant absorbs heat from solid matrix, and the fluid temperature is higher than solid temperature at the stagnation point of the strut. The influence of coolant mass flow rate and various coolants on transpiration cooling is studied. As mass flow rate increases, the cooling efficiency becomes higher and the temperature difference between fluid and solid in the porous medium is smaller. The coolant with a lower density and a higher specific heat will form a thicker film on the strut surface and absorbs more heat from solid matrix, which brings a better cooling effect for strut.

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An experimental investigation on transpiration cooling with phase change under supersonic condition

Cited by 69 publications

References 24 publications

Effects of Coolants of Double Layer Transpiration Cooling System in the Leading Edge of a Hypersonic Vehicle

Effects of Coolants of Double Layer Transpiration Cooling System in the Leading Edge of a Hypersonic Vehicle

Modelling and Simulation of Transpiration Cooling Systems for Atmospheric Re-Entry

Numerical Investigation on the Mechanism of Transpiration Cooling for Porous Struts Based on Local Thermal Non-Equilibrium Model

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