Pre-whirling type pintle injector applied to double-component liquid propellant rocket engine

Abstract

The invention discloses a pre-whirling type pintle injector applied to a double-component liquid propellant rocket engine. The pre-whirling type pintle injector applied to the double-component liquidpropellant rocket engine comprises a center rod, an inner nozzle, an outer nozzle and a connecting ring, all of which are rotation bodies. The inner nozzle coaxially sleeves the center rod, and a cavity for conveying fuel is formed by the inner nozzle and the center rod. The outer nozzle coaxially sleeves the outer nozzle, a cavity for conveying an oxidizing agent is formed by the outer nozzle andthe inner nozzle, and the connecting ring coaxially sleeves the outer nozzle. Pre-whirling treatment is conducted before oxidizing agent spraying-out, and the problem that a conventional pintle injector is not high in effective mixing efficiency is effectively solved; meanwhile, through the arrangement of two rows of fuel direct flow injection holes, cooling to a liquid film on the wall face of athrust chamber through propellant is effectively achieved; and the performance and the reliability of the double-component liquid propellant rocket engine can be obviously improved.

Description

technical field [0001] The invention relates to a pre-rotating pintle injector applied to a dual-component liquid rocket engine, especially suitable for a high-performance dual-component space liquid rocket engine, and belongs to the field of space propulsion technology. Background technique [0002] The pintle injector has been widely used in space liquid rocket engines due to its advantages of simple structure, uniform mixing and easy adjustment of variable thrust. In the prior art, the pintle injector usually adopts the way of vertical mutual collision of propellants for atomization and mixing, which has the following disadvantages: [0003] First, due to the excessive impact angle of the two propellants, the mixing efficiency of the propellants in the combustion chamber is not high, which restricts the improvement of engine performance. [0004] Second, the composite angle after the propellants collide with each other is related to the flow ratio of the two propellants,...

AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, the present invention provides a pre-swirl pintle injector structure applied to the dual-component liquid rocket engine, by pre-swirling the oxidant before spraying , which effectively solves the problem of low effective mixing efficiency of conventional pintle injectors; at the same time, by setting two rows of direct-flow fuel injection holes, the liquid film cooling of the propellant on the wall of the thrust chamber is effectively realized; it can significantly improve the efficiency of the bicomponent liquid Rocket Motor Performance and Reliability

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