Numerical investigation on a double layer combined cooling structure for aerodynamic heat control of hypersonic vehicle leading edge

Ding, Rui; Wang, Jianhua; He, Fei; Wang, Meng; Luan, Yun; Dong, Guangqi; Tang, Longsheng

doi:10.1016/j.applthermaleng.2020.114949

Cited by 32 publications

(16 citation statements)

References 30 publications

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“…The design of the geometric model in this work bases on the double layer combined cooling structure at the leading edge of a hypersonic vehicle proposed by Ding et al (2020). The structure is composed of inner and outer layers, the outer layer is a transpiration cooling layer, and the porous medium material is sintered nickel-based superalloy.…”

Section: Description Of the Computational Domain Geometrical Modelmentioning

confidence: 99%

“…In this paper, the computational domain includes hypersonic transpiration cooling, film cooling, heat conduction in the porous (Ding et al, 2020).…”

Section: Computational Domain and Physical Modelmentioning

confidence: 99%

“…Ding et al (2019) concentrated on the thermal protection of the leading edge of a hypersonic vehicle and proposed a coupled numerical method to calculate the overall cooling effect. Based on the previous studies about double layer cooling structures in a turbine blade, a novel double layer combined cooling (DLCC) conception is proposed by Ding et al (2020). The coolant is allocated reasonably by adjusting the layout of the film slots, and the feasibility of the filmtranspiration combined cooling scheme is verified.…”

Section: Introductionmentioning

confidence: 99%

“…The coolant is allocated reasonably by adjusting the layout of the film slots, and the feasibility of the filmtranspiration combined cooling scheme is verified. The work of Ding et al (2020) shows that the double layer combined cooling is a very effective active cooling method, which provides a reference for the design of thermal protection system of a hypersonic vehicle. Ding et al (2020) considered the effects of several discrete film slot layouts on cooling efficiency of the double layer combined cooling structures.…”

Section: Introductionmentioning

confidence: 99%

“…The work of Ding et al (2020) shows that the double layer combined cooling is a very effective active cooling method, which provides a reference for the design of thermal protection system of a hypersonic vehicle. Ding et al (2020) considered the effects of several discrete film slot layouts on cooling efficiency of the double layer combined cooling structures. The transpiration cooling efficiency is mainly determined by the properties of coolants and main flow, blowing ratio, the geometric structure, and mainstream conditions (Zhu et al, 2018).…”

Section: Introductionmentioning

confidence: 99%

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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: Description Of the Computational Domain Geometrical Modelmentioning

confidence: 99%

“…In this paper, the computational domain includes hypersonic transpiration cooling, film cooling, heat conduction in the porous (Ding et al, 2020).…”

Section: Computational Domain and Physical Modelmentioning

confidence: 99%