Flow guide plate capable of improving propellant filling synchronism and injector

Abstract

The invention relates to a flow guide plate capable of improving propellant filling synchronism and an injector, and aims to solve the technical problems that the filling synchronism of the injector is reduced and the working stability is reduced during starting due to the fact that fuel filling is unidirectional and the stroke is long due to a flow guide plate of a fuel cavity of the existing injector. The flow guide plate comprises a flow guide plate body, a center hole formed in the center area of the flow guide plate body, a plurality of edge area flow dividing holes evenly distributed in the edge area of the flow guide plate body in the circumferential direction and a plurality of nozzle mounting holes, wherein the ratio of the total area of the edge area flow dividing holes to the area of the center hole is 20%-30%. The injector comprises an injector face, a plurality of nozzles arranged on the injector face, a fuel cavity and the flow guide plate, wherein the flow guide plate is installed in the fuel cavity and divides the fuel cavity into an upper fuel cavity and a lower fuel cavity, and the nozzles penetrate through the fuel cavity and penetrate through the corresponding nozzle mounting holes in the fuel cavity. According to the invention, the cooling of the injector face and the fuel filling speed can be both considered.

Description

technical field [0001] The invention relates to a deflector and an injector which can improve the synchronization of liquid propellant filling. The deflector is applied in the fuel cavity of the injector, and the injector is applied to the thrust chamber or the gas generator of the engine, especially It is a liquid rocket engine thrust chamber that requires high propellant filling synchronization. Background technique [0002] Liquid rocket engine thrust chamber injectors are the main components for atomizing and mixing liquid propellant components. The working condition of the injector largely determines the degree of complete combustion of the propellant and the stability of the working process of the thrust chamber. On the one hand, the synchronicity of the liquid propellant filling process in the injector affects the ignition quality of the thrust chamber and the working stability at start-up; cooling to ensure its working reliability. Therefore, improving the filling...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the technical problem that the deflector of the fuel chamber of the existing injector makes the fuel filling one-way and the stroke is long, which leads to the decrease of the injector filling synchronization and the work stability during start-up, and proposes a Deflector and injector that can improve the synchronization of propellant filling. The deflector can improve the filling synchronization of liquid propellant in the injector, taking into account the flow rate of the fuel lower chamber, thereby increasing the cooling margin of the injector surface

Images