Adjustable pintle injector and rocket engine

Abstract

The invention provides an adjustable pintle inspirator and a rocket engine. The adjustable pintle inspirator comprises a displacement control rod, an adjustable pintle inspirator body and an adjustable pintle inspirator body, the displacement control rod is sleeved with the upper end cover, and the first end of the upper end cover is connected with the first end of the displacement control rod in a screwed mode; a displacement cavity is formed between the second end part of the upper end cover and the second end part of the displacement control rod; the injector upper bottom sleeves the second end part of the upper end cover and is fixedly connected with the second end part of the upper end cover; the air nozzle is coaxial with the displacement control rod and is positioned below the second end part of the displacement control rod; the first end part of the liquid nozzle sleeves the second end part of the displacement control rod and is fixedly connected with the displacement control rod, the second end part of the liquid nozzle sleeves the gas nozzle, and an inner rotational flow cavity is formed between the second end part of the liquid nozzle and the gas nozzle; and the nozzle mounting seat sleeves the second end part of the liquid nozzle, and an outer rotational flow cavity is formed between the nozzle mounting seat and the liquid nozzle. According to the scheme, the injection pressure drop of the injector in the engine throttling process can be adjusted, and the phenomenon that the pressure drop is sharply increased along with flow increase is relieved.

Description

Technical field [0001] The invention relates to the field of rocket engines, and in particular to an adjustable needle injector and a rocket engine. Background technique [0002] In recent years, with the continuous development of recyclable rocket technology, higher and higher requirements have been placed on the thrust adjustment capabilities of liquid rocket engines. Through engine thrust adjustment, the power requirements such as overload control, ballistic optimization, and recovery control during rocket launch are met. In this process, the flow rate of the liquid rocket engine changes with the thrust. For a traditional fixed-structure injector, as the propellant flow rate increases (decreases), the injector pressure drop increases rapidly as the square of the flow rate. (reduce). When the engine thrust adjustment range is large, the injection pressure drop of this type of injector will change significantly, which is not conducive to stable combustion in the thrust ch...

AI Technical Summary

Problems solved by technology

In order to meet the needs of structural adjustment, traditional pintle injectors are mostly designed as two-component coaxial annular nozzles, which are essentially straight-line injectors. The atomization form of the propellant is impact atomization. During the flow adjustment process However, due to the influence of the structural accuracy of the injector and the atomization form, it is difficult to maintain a stable propellant atomization effect, and it is difficult to achieve high-efficiency combustion in the combustion chamber within the full range of operating conditions.

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