Active-passive composite hydrocarbon fuel supersonic gas film cooling system with staggered discrete slot structure
The invention provides an active and passive composite hydrocarbon fuel supersonic gas film cooling system with a staggered discrete slot structure. The inner side of the cooling ring is attached to the wall face of an engine combustion chamber, a composite material structure is adopted on the attac...
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| creator | ZHANG SILONG WEI JIANFEI ZHAO GUICHEN LI XIN BAO WEN WANG HEYANG WEI BAOXI ZHOU XINGYU ZUO JINGYING |
| description | The invention provides an active and passive composite hydrocarbon fuel supersonic gas film cooling system with a staggered discrete slot structure. The inner side of the cooling ring is attached to the wall face of an engine combustion chamber, a composite material structure is adopted on the attaching face to meet the thermal protection requirement of the cooling ring, hydrocarbon fuel flows into a plenum chamber in the cooling ring through a regeneration cooling channel and reaches critical injection through an acceleration spray pipe, and meanwhile regeneration cooling is provided for the cooling ring in the process. In order to make up the defect of the transverse diffusion effect of a supersonic gas film and guarantee the structural strength of the combustion chamber, a staggered discrete slot gas film injection mode fully covering the combustion chamber in the circumferential direction is provided. According to the cooling system, efficient regeneration/film composite cooling of the scramjet combustion |
| format | Patent |
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The inner side of the cooling ring is attached to the wall face of an engine combustion chamber, a composite material structure is adopted on the attaching face to meet the thermal protection requirement of the cooling ring, hydrocarbon fuel flows into a plenum chamber in the cooling ring through a regeneration cooling channel and reaches critical injection through an acceleration spray pipe, and meanwhile regeneration cooling is provided for the cooling ring in the process. In order to make up the defect of the transverse diffusion effect of a supersonic gas film and guarantee the structural strength of the combustion chamber, a staggered discrete slot gas film injection mode fully covering the combustion chamber in the circumferential direction is provided. 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| language | chi ; eng |
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| subjects | BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | Active-passive composite hydrocarbon fuel supersonic gas film cooling system with staggered discrete slot structure |
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