Binary hypersonic air inlet channel with single-row cantilever pre-injection
The invention discloses a binary hypersonic air inlet channel with single-row cantilever pre-injection, which is characterized in that a cantilever structure is arranged on the last-stage compression surface of a binary hypersonic air inlet channel unit, and fuel is injected through the cantilever s...
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Format: | Patent |
Sprache: | chi ; eng |
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Zusammenfassung: | The invention discloses a binary hypersonic air inlet channel with single-row cantilever pre-injection, which is characterized in that a cantilever structure is arranged on the last-stage compression surface of a binary hypersonic air inlet channel unit, and fuel is injected through the cantilever structure, so that the flow coefficient and the total pressure recovery coefficient of the air inlet channel are ensured, and the fuel injection efficiency is improved. Fuel and incoming flow air are fully mixed through a long front body and an inner channel of the hypersonic speed air inlet channel, and combustible mixed gas beneficial to combustion is provided for a combustion chamber connected to the rear portion of the air inlet channel.
本发明公开一种带单排悬臂预喷注的二元高超声速进气道,在二元高超声速进气道单元最后一级压缩面设置悬臂结构,通过该结构喷注燃料,在保证进气道流量系数以及总压恢复系数的同时,利用高超声速进气道较长的前体以及内通道实现燃料与来流空气的充分混合,为进气道后方所连接的燃烧室提供利于燃烧的可燃混合气。 |
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