Integrated injector of liquid rocket engine

Abstract

The invention relates to an integrated injector of a liquid rocket engine. The integrated injector comprises a bottom plate, an outer barrel, fuel injection nozzles, oxidant injection nozzles, swirlers and flow equalization fixators. The outer barrel is provided with a center shaft. The center shaft and the barrel wall of the outer barrel are connected through an annular horizontal plate. The annular horizontal plate divides an inner cavity of the outer barrel into an upper cavity and a lower cavity. The sidewall of the lower cavity is provided with a plurality of fuel through holes. The bottom of the lower cavity is connected with the bottom plate. The bottom plate is provided with a plurality of fuel injection nozzle fixing holes. The annular horizontal plate is provided with a pluralityof oxidant injection nozzle fixing holes. Each fuel injection nozzle and the corresponding oxidant injection nozzles are adaptively connected to between each pair of fuel injection nozzle fixing holes and the corresponding oxidant injection nozzle fixing holes. Annular fuel channels are formed between the inner walls of the fuel injection nozzles and the outer walls of the corresponding oxidant injection nozzles. The top ends of the oxidant injection nozzles are inlaid in the corresponding swirlers. The flow equalization fixators are arranged in the upper cavity. The swirlers are fixed by theflow equalization fixators through a plurality of stand columns in one-to-one correspondence. Through the integrated injector, the fixing structure of the swirlers is simplified, and meanwhile, the oxidant flow uniformity is improved.

Description

technical field [0001] The invention relates to the technical field of rocket engine injectors, in particular to an integrated injector for liquid rocket engines. Background technique [0002] The development direction of the rocket engine is to simplify the structure to improve the reliability of the engine while ensuring the performance of the engine. [0003] The traditional rocket engine injector adopts a coaxial centrifugal structure, including a coaxial tangential hole centrifugal injector and a coaxial vortex centrifugal injector. The swirling flow and atomization of the fuel nozzle; the axial injection of the fuel is realized through the annular gap between the oxidizer nozzle and the fuel nozzle; the outlet of the oxidizer nozzle is indented by a certain distance from the outlet of the fuel nozzle, so that the atomized oxidizer can be ejected at a high speed Driven by the fuel, it is further atomized, and the two are fully mixed and then burned. The oxidant and fu...

AI Technical Summary

Problems solved by technology

[0009] The technical problem to be solved by the present invention is to provide an integrated injector for a liquid rocket engine in view of the defect that the vortexer of the injector in the prior art is complicated to fix, resulting in poor flow uniformity of the oxidant

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