高超声速飞行器异型气膜孔无喷流热增量研究

Thermal Increment of Hypersonic Flight Vehicles with Non-jet Heterotypic Film Cooling Hole

目的获取高超声速飞行器气膜孔不喷流时的热负荷增量。方法通过计算流体力学(CFD)方法针对典型高超声速飞行器50km、飞行马赫数为15条件下的无开孔、有开孔气膜冷、有开孔无喷流3种工况开展壁面热流分布研究。结果无开孔的最大热流分布在头部滞止点附近,约为2.2 MW/m^2,有气膜冷却的工况热流最高值在侧面气膜孔没有覆盖到的部位,约为1.4 MW/m^2,有异型孔但是不喷流的工况,热流密度最大值主要分布在开孔附近,最大值大于3.3 MW/m^2。结论对于在高超声速飞行器表面开孔采用气膜冷却方式冷却时,如果由于某种原因气膜孔不喷流,那么在孔的附近乃至整个滞止区域附近的热流负荷将会大幅度升高。

Objective To obtain the thermal increment of hypersonic flight vehicles with non-jet heterotypic film cooling hole. Methods The wall heat flux distribution was researched in three operating conditions （non-hole case （Case 1）, heterotypic film cooling hole with jet case （Case 2） and heterotypic film cooling hole without jet case （Case 3）） at 50 km and 15 Ma with computational fluid mechanics （CFD）. Results The maximum heat flux of non-hole case was 2.2 MW/m^2, and distributed in the stagnation point of the head. For the Case 2, the maximum heat flux was 1.4 MW/m^2, did not cover the lateral hole. The maxi-mum heat flux of Case 3 was more than 3.3 MW/m^2, and distributed near the holes. Conclusion When film cooling is used for surface hole of hypersonic flight vehicles, if the film hole does not inject air flow for some reasons, the heat current flow near the hole or even the hole stagnation area might increase significantly.