Combined power rocket engine injector

Abstract

The invention provides a combined power rocket engine inspirator which mainly comprises an inspirator lower bottom, an inspirator middle bottom, an inspirator upper bottom, an inspirator upper cover, a propellant inlet nozzle and a chamber pressure measuring nozzle, the inspirator lower bottom and the inspirator middle bottom form a combined part, and then the combined part is welded to the inspirator upper bottom in an aligned mode; the injector upper cover and the injector upper bottom are installed and welded together in a contact mode, one end of the propellant inlet nozzle is installed on the upper end face of the injector upper cover, the other end of the propellant inlet nozzle is connected with a propellant supply pipeline ball head, one end of the chamber pressure measuring nozzle is installed on the upper end face of the injector upper bottom, and the other end of the chamber pressure measuring nozzle is connected with a pressure sensor ball head. The equal-proportion complex harmonic cavity structure design is adopted, unstable combustion in the starting stage and the steady-state stage can be restrained at the same time, the structure is simple, manufacturability is good, weld joints can be detected, the production cost is low, the thermal structural strength is stable and reliable, repeated use can be achieved, and manufacturing raw materials are low in cost and easy to purchase.

Description

technical field [0001] The invention belongs to the field of aerospace technology, in particular to a combined power rocket engine injector. Background technique [0002] The injector is the core component of the combined power liquid rocket engine. It is located at the head of the thrust chamber. Its function is to inject the propellant evenly into the combustion chamber under the specified propellant flow rate, mixing ratio and injection pressure drop. Ensure that the mixing ratio and mass distribution meet the requirements of the design state, and quickly complete the atomization and mixing process of the propellant, so that the propellant can be burned efficiently and fully in the combustion chamber. The design level and processing accuracy of the injector have a great influence on the stability, efficiency and life of the combustion chamber. The existing combined power rocket engine thruster uses a variety of parts to form the internal flow channel, which has complex s...

AI Technical Summary

Problems solved by technology

[0003] The technical problem solved by the present invention is to provide a combined power rocket engine injector. The middle bottom of the injector and the lower bottom of the injector are fixed by two butt circular laser welds to form an assembly, and then connected to the upper injector. Bottom fitting and installation, butt joints are circular laser welds or electron beam welds, which solves the problem that the existing combined power rocket engine thruster uses a variety of parts to form the internal flow channel, the structure shape is complicated, the connection is difficult to form, and the dead channel , There are many blind holes, especially inside the injector, multiple parts are connected and fixed by vacuum brazing, the brazing seam cannot be detected, and the requirements for the brazing process are high. question

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