The invention relates to a micro-rib jet impingement cooling channel for a hot end component of an aircraft, which is of an integral structure and comprises 1-100 sub-channels, the sub-channels are arranged in parallel, and the side walls of the adjacent sub-channels are shared. Each sub-channel comprises a main channel, micro-ribs and jet flow holes. Fuel oil enters the main channel from one end of the main channel and the jet flow hole and is discharged from the other end of the main channel. The cross section of the main channel is rectangular, micro-ribs are arranged at the bottom of the main channel and form array micro-ribs, jet holes are formed in the top of the main channel and are uniformly or non-uniformly distributed, and two side walls of the main channel are smooth planes. The array micro-ribs and the jet flow holes are arranged, the micro-ribs are coupled with the jet flow impact effect, on the premise that additional mass burden is not increased, the wall surface temperature of the combustion chamber of the scramjet engine is effectively reduced, temperature rise of high-heat parts of an aircraft is effectively restrained, and therefore the purpose of flight with the higher Mach number is achieved.
本发明涉及一种用于飞行器热端部件的微肋射流冲击冷却通道,为整体结构,包括1~100个子通道,子通道并列设置,相邻子通道的侧壁共用。子通道包括主通道、微肋、射流孔。燃油分别由主通道的一端、射流孔进入主通道,从主通道的另一端排出。主通道横截面为矩形,主通道底部设置微肋,微肋组成阵列微肋,主通道顶部设置射流孔,射流孔均匀或非均匀分布,主通道两侧壁为光滑平面。本发明设置了阵列微肋、射流孔,微肋与射流冲击的作用相互耦合,在不增加额外的质量负担的前提下,有效降低了超燃冲压发动机燃烧室壁面温度,有效遏制了飞行器高热部件的温升,从而达到更高马赫数飞行的目的。
Micro-rib jet impingement cooling channel for aircraft hot end component
一种用于飞行器热端部件的微肋射流冲击冷却通道
2023-05-16
Patent
Elektronische Ressource
Chinesisch
OPTIMIZATION OF AN INDIRECT MICRO-JET IMPINGEMENT COOLING SYSTEM
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