The invention provides an integrated structure
injector for a
rocket engine. The integrated structure
injector comprises an
oxidizing agent inlet, an
oxidizing agent liquid collecting cavity,
oxidizing agent distribution channels, oxidizing agent annular cavities and oxidizing agent injection holes; and a fuel inlet, a fuel liquid collecting cavity, a fuel conveying channel,
fuel distribution channels, fuel annular cavities and
fuel injection holes are formed, and each
propellant flows through the corresponding channel, then enters the corresponding annular cavity and enters the correspondinginjection hole. According to the
machining method, the number of parts is effectively reduced, the
machining process is simplified, the manufacturing period of the
injector is shortened, the machiningcost is reduced, and meanwhile the product reliability is improved. According to the
machining method, the oxidizing agent annular cavities and the fuel annular cavities are arranged in a circle andcorrespond to the injection ports correspondingly, so that the oxidizing agents and fuel are injected correspondingly; and the injection holes form injection pairs, oxidizing agent mist fans and fuelmist fans are formed through mutual
impact, and mutual infiltration and mixing between the oxidizing agent mist fans and the fuel mist fans are achieved, so that it is guaranteed that the oxidizing agents and the fuel can be evenly mixed in proportion, and the
combustion efficiency is improved.