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Pintle injector for liquid rocket engine

A liquid rocket and engine technology, which is applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of poor atomization and mixing characteristics, achieve improved atomization and mixing characteristics, good atomization effect, The effect of improving combustion efficiency

Active Publication Date: 2021-08-24
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defects of poor atomization and mixing characteristics of pintle injectors in the prior art, thereby providing a liquid rocket engine that can improve atomization and mixing characteristics. pintle injector

Method used

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  • Pintle injector for liquid rocket engine
  • Pintle injector for liquid rocket engine
  • Pintle injector for liquid rocket engine

Examples

Experimental program
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Embodiment 1

[0042] to combine Figure 1-Figure 3 As shown, the pintle injector for liquid rocket motor provided by this embodiment includes:

[0043] The pintle body 3 is configured as a hollow tubular structure, and the pintle body 3 is suitable for passing through the first propellant;

[0044] The bottom cover 1 is sleeved on the outside of the pintle body 3, and the inside of the bottom cover 1 is suitable for passing the second propellant;

[0045] One end of the pintle body 3 is provided with several tangential holes 13 around, and a plurality of swirl holes 12 are arranged at the fitting position of the bottom cover 1 and the pintle body 3; The second propellant ejected from 12 is opposite to the rotation direction of the first propellant ejected from the tangential hole 13 and collides and mixes with each other.

[0046] preferably, with figure 1Taking the angle of view of the pintle body 3 as an example, the pintle body 3 is constructed as a hollow tubular structure, and its u...

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Abstract

The invention relates to the technical field of engines, in particular to a pintle injector for a liquid rocket engine. According to the pintle injector for the liquid rocket engine, a plurality of tangential holes are formed in the head of one end of a pintle body in a surrounding mode, and a plurality of rotational flow holes are formed in the attaching position of a bottom cover and the pintle body; thus, the rotation directions of a second propellant sprayed out of the rotational flow holes and a first propellant sprayed out of the tangential holes are opposite, and the second propellant and the first propellant are collided and mixed with each other; therefore, the atomization effect of the two propellants is better, and the mixing effect is more uniform; and thus, the atomization and mixing characteristics of the pintle injector for the liquid rocket engine are improved, and the combustion efficiency of the liquid rocket engine is improved.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a pintle injector for a liquid rocket engine. Background technique [0002] With the development of aerospace technology, reusable technology has emerged as the times require, making high-performance liquid rocket engines the future development direction. One of the indicators to measure the performance of liquid rocket engines is the specific impulse, which refers to the unit mass The thrust that the propellant can produce, the greater the specific impulse, the better the engine performance, and the key parameter that affects the specific impulse is the combustion efficiency of the propellant. Generally, the higher the combustion efficiency, the higher the specific impulse of the engine; the combustion efficiency of the liquid rocket engine Depends on the mixing and atomization characteristics of the propellant components, the better the propellant atomization, the more uniform ...

Claims

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Application Information

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IPC IPC(8): F02K9/52
CPCF02K9/52
Inventor 鲍启林刘岳曦高翔宇何佳丽
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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