Abstract
The flow and heat transfer characteristics of a film jet inclined to different supersonic situations with a varying Mach number of the main flow were numerically investigated. In supersonic situations, complicated waves are generated by the obstacle of the film jet. In this work, extra pressure is exerted onto the film jet, causing better film attachment to the wall. The strengthening of attachment decreases mixing between the main flow and film jet, causing better film cooling. We observed multi-interfacial layered structures caused by the film jet under the complicated effect of shock waves. At the interfaces of the film jet and shock waves, additional pressure is exerted on the film towards the wall. The pressure increases as the Mach number of the main flow increases and contributes to the increased adhesion of the gas film, which causes the cooling enhancement under a supersonic condition. In the vicinity of the film hole exit, a local low pressure region is formed under the influence of the supersonic main flow. An aerodynamic convergent–divergent state was formed in the film hole, devastating the state of supersonic congestion of the film hole and further enhancing the film cooling effect.
Highlights
In the previous designs of the engine nozzle, researchers have not yet fully taken into account the cooling requirement of the expansion section
This paper focuses on components such as the nozzle expansion section working in the supersonic flow environment and the film layer interfered by the shock waves and the boundary layer
The film jet inlet is defined as the pressure inlet; the main flow inlet and exit are defined as the pressure far field, whereas the surfaces are regarded as boundary are defined as the pressure far field, whereas the surfaces are regarded as boundary defined as the pressure far field, whereas the surfaces are regarded as boundary conditions conditions of the adiabatic wall
Summary
In the previous designs of the engine nozzle, researchers have not yet fully taken into account the cooling requirement of the expansion section. As the operating conditions of the engine vary, the main flow velocity and the cooling gas pressure are subject to a wide range of variation in the expansion section of the binary vector nozzle. In this paper, we adopt the locity and the cooling gas pressure areexpansion subject to a wide rangeTherefore, offind variation the expansion section of environment the binary vector nozzle. Researchers it more difficult to flat model to elaborate on influence imposed by the Mach number of the main adopt the nozzle model tovector calculate andthe analyze the film coolingfind characteristics in the adopt the main nozzle model to calculate andexpansion analyze the film cooling characteristics inwe the supersonic flow environment of the section. A reference for the design of the film cooling expansion section of a binary sign of the filmModel cooling of the expansion section of a binary vector nozzle
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