高超声速主流中平/曲面上超声速气膜冷却特性
2025,47(1):126-135
摘要：
超声速气膜冷却技术被广泛应用于高超声速飞行器主动热防护。针对平面和曲面，采用数值模拟方法研究了冷却气体入口马赫数、吹风比以及喷缝高度对于超声速气膜冷却特性的影响，并对气膜冷却效果进行了试验验证。结果表明，无论被冷却壁面是平面或曲面，超声速气膜均具有良好的壁面附着特性，可以对壁面进行有效冷却。相较而言，超声速气膜作用于曲面上的冷却效果优于平面。提高冷却气体入口马赫数及吹风比可以提高冷却效率。随着喷缝高度的增大，气膜冷却效率随之增大，并逐渐达到一个恒定值。即当喷缝高度足够大时，进一步增大喷缝高度的优势不大。
超声速气膜冷却技术被广泛应用于高超声速飞行器主动热防护。针对平面和曲面，采用数值模拟方法研究了冷却气体入口马赫数、吹风比以及喷缝高度对于超声速气膜冷却特性的影响，并对气膜冷却效果进行了试验验证。结果表明，无论被冷却壁面是平面或曲面，超声速气膜均具有良好的壁面附着特性，可以对壁面进行有效冷却。相较而言，超声速气膜作用于曲面上的冷却效果优于平面。提高冷却气体入口马赫数及吹风比可以提高冷却效率。随着喷缝高度的增大，气膜冷却效率随之增大，并逐渐达到一个恒定值。即当喷缝高度足够大时，进一步增大喷缝高度的优势不大。
基金项目：
国家重点研发计划资助项目（2019YFA0405300）
国家重点研发计划资助项目（2019YFA0405300）
Cooling characteristics for supersonic film on flat/curved surfaces in hypersonic mainstream
CHEN Bohong
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
YI Shihe
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
YI Shihe
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073 , China
Abstract：
Supersonic film cooling technology is widely used in active thermal protection of hypersonic aircraft. A numerical simulation method was used to investigate the effects of the Mach number at the cooling gas′s inlet, blowing ratio and the height of the spray seam on the supersonic film cooling characteristics for both flat and curved surfaces, and the effectiveness of film cooling was experimentally verified. Results show that regardless of whether the cooled wall is flat or curved, the supersonic gas film has good wall adhesion characteristics and can effectively cool the wall. In comparison, the cooling effect of supersonic gas film on curved surfaces is better than that on flat surfaces. Increasing the Mach number at the cooling gas′s inlet and blowing ratio can improve cooling efficiency. As the height of the spray seam increases, the film cooling efficiency increases and gradually reaches a constant value. When the height of the spray seam is large enough, the advantage of further increasing the height of the spray seam is not significant.
Supersonic film cooling technology is widely used in active thermal protection of hypersonic aircraft. A numerical simulation method was used to investigate the effects of the Mach number at the cooling gas′s inlet, blowing ratio and the height of the spray seam on the supersonic film cooling characteristics for both flat and curved surfaces, and the effectiveness of film cooling was experimentally verified. Results show that regardless of whether the cooled wall is flat or curved, the supersonic gas film has good wall adhesion characteristics and can effectively cool the wall. In comparison, the cooling effect of supersonic gas film on curved surfaces is better than that on flat surfaces. Increasing the Mach number at the cooling gas′s inlet and blowing ratio can improve cooling efficiency. As the height of the spray seam increases, the film cooling efficiency increases and gradually reaches a constant value. When the height of the spray seam is large enough, the advantage of further increasing the height of the spray seam is not significant.
收稿日期：
2023-09-28
2023-09-28
