A kind of injector and engine and aircraft

Abstract

An injector, an engine, and an aircraft provided by the present invention include: a casing with a number of injection chambers built in, and a number of injection channels and a number of guide ports communicated with the injection chamber. The port is suitable for feeding fluid into the injection cavity; the elastic layer is arranged along the injection channel and is suitable for elastic deformation under the pressure of the fluid. The diversion port introduces material flow such as propellant into the injection chamber, and the material flow flows out from the injection channel, and sprays and atomizes outside the shell. By setting an elastic layer in the injection channel, the injection flow can The inner diameter of the channel, that is, the injection flow area changes in a positive correlation with the material flow pressure. When the injection pressure is high, the flow area will increase, reducing the injection pressure drop at high flow rates, and reducing part of the pressure compared to the fixed flow channel inner diameter. Loss, reduce the pressure of the supply system upstream of the injector, and reduce the requirements of the fuel supply system of the device equipped with the injector, such as an engine or a rocket.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to an injector, an engine and an aircraft. Background technique [0002] The thrust chamber is an important component of the power generation of the liquid rocket engine. The rocket engine needs propellant to burn in the thrust chamber to generate the thrust that propels the rocket. The liquid propellant needs to be sprayed and atomized before entering the thrust chamber for combustion. The more fully the atomization, the higher the combustion efficiency. At present, the injection and atomization process mostly uses the injection nozzle on the injector. [0003] However, the propellant will produce a pressure loss during the injection process through the nozzle, and this pressure loss is positively correlated with the flow rate of the propellant. When the flow rate of the propellant increases with the increase of thrust and chamber pressure, the pressure of the propellant Losses wi...

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Problems solved by technology

[0003] However, the propellant will produce a pressure loss during the injection process through the nozzle, and this pressure loss is positively correlated with the flow rate of the propellant. When the flow rate of the propellant increases with the increase of thrust and chamber pressure, the pressure of the propellant losses will increase

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