Nozzle liquid mist distribution adjustable rocket engine jet faceplate and design method

A rocket engine and nozzle technology, which is applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems affecting the flame shape of the nozzle, combustion instability, etc.

Active Publication Date: 2019-02-22
PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The spatial distribution of nozzle liquid mist will affect the flame shape near the nozzle, thereby inducing combustion instability

Method used

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  • Nozzle liquid mist distribution adjustable rocket engine jet faceplate and design method
  • Nozzle liquid mist distribution adjustable rocket engine jet faceplate and design method
  • Nozzle liquid mist distribution adjustable rocket engine jet faceplate and design method

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Embodiment Construction

[0084] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific preferred embodiments.

[0085] Such as Figure 1 to Figure 6 As shown, a rocket engine injection panel with adjustable nozzle liquid mist distribution includes a gas collection chamber base 10, a gas collection chamber middle plate 20, a gas collection chamber rear plate 30, a fuel chamber top cover 40, and a fire transfer tube 50 And several double swirl nozzles 60.

[0086] The center of the base of the gas-collecting chamber is provided with an air-collecting chamber 13 with an open top, and the gas-collecting chamber is provided with bottom steps and top-floor steps from the inside to the outside in sequence, and the center of the bottom plate of the gas-collecting chamber is provided with a fire-transfer tube installation hole 11 for fire transmission. The number of nozzle holes 12 equal to the number of double-swirl nozzles is evenly distrib...

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PUM

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Abstract

The invention discloses a nozzle liquid mist distribution adjustable rocket engine jet faceplate and a design method. The nozzle liquid mist distribution adjustable rocket engine jet faceplate comprises a gas collecting cavity base, a gas collecting cavity middle plate, a gas collecting cavity rear plate, a fuel cavity top cover, a fire transferring tube and a plurality of double-swirl nozzles, wherein a gas collecting cavity is divided into two oxygen cavities; a fuel cavity is formed between the fuel cavity top cover and the gas collecting cavity rear plate; the plurality of double-swirl nozzles are uniformly distributed along the circumference of the fire transferring tube; each double-swirl nozzle comprises a nozzle inner core, a nozzle inner layer and a nozzle outer layer; an inner mixing cavity is formed between the nozzle inner core and the nozzle inner layer; an outer mixing cavity is formed between the nozzle inner layer and the nozzle outer layer; the nozzle inner core is provided with a fuel jet hole; inner swirl holes are uniformly distributed on a nozzle middle layer along the circumference; and the nozzle outer layer is provided with a large through hole, an outer swirl hole and a jet hole; and the swirl direction of the outer swirl hole is opposite to the swirl direction of the inner swirl holes. The flow ratio of inner swirling eddy to outer swirling eddy can beadjusted by controlling the jet pressure drop of the inner swirl hole and the outer swirl hole, so that liquid mist of different distribution patterns is formed.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engines, in particular to a rocket engine injection panel with adjustable nozzle liquid mist distribution. Background technique [0002] The liquid rocket engine is the power unit of the space launch vehicle. In the combustion chamber of a liquid rocket engine, once the combustion heat release process is coupled with the natural acoustic frequency of the combustion chamber, high-frequency combustion instability will occur. High-frequency combustion instability will seriously damage the cooling liquid film on the inner wall of the combustion chamber, causing the wall of the combustion chamber to burn through. Propellants need to go through multiple sub-processes such as atomization, evaporation, and mixing before they can participate in combustion and heat release. These sub-processes are closely related to the combustion heat release process, which may lead to high-frequency combustion ins...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/52F02K9/60F02K9/96
CPCF02K9/52F02K9/60F02K9/96
Inventor 包恒林伟仝毅恒聂万胜王辉侯志勇
Owner PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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