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Rocket engine injection panel capable of researching spraying relation among multiple nozzles

A rocket engine and multi-nozzle technology, which is applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems affecting the atomization characteristics of nozzles, and achieve the effect of important engineering application value, compact structure, and good stability

Pending Publication Date: 2022-05-31
PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, there are many studies on the atomization characteristics of a single nozzle, but in the actual process of engine operation, nozzles are often distributed in groups on the injection panel according to certain rules, and the relationship between sprays will affect the overall nozzle atomization characteristics

Method used

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  • Rocket engine injection panel capable of researching spraying relation among multiple nozzles
  • Rocket engine injection panel capable of researching spraying relation among multiple nozzles
  • Rocket engine injection panel capable of researching spraying relation among multiple nozzles

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Embodiment Construction

[0051] The present invention will be described in further detail below with reference to the accompanying drawings and specific preferred embodiments.

[0052] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "left side", "right side", "upper", "lower part", etc. are based on the orientation or positional relationship shown in the drawings, only For the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a particular orientation, be constructed and operate in a particular orientation, "first", "second", etc. importance, and therefore should not be construed as a limitation to the present invention. The specific dimensions used in this embodiment are only for illustrating the technical solution, and do not limit the protection scope of the present invention.

[0053] like figure...

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Abstract

The invention discloses a rocket engine injection panel capable of researching the spraying relation among multiple nozzles. The rocket engine injection panel comprises a top cover, a middle connecting plate, a base and a plurality of liquid center type gas-liquid coaxial nozzles. A sealed liquid collecting cavity is formed between the top cover and the middle connecting plate; a sealed gas collecting cavity is formed between the base and the middle connecting plate; each liquid center type gas-liquid coaxial nozzle comprises a liquid inner nozzle and a peripheral gas nozzle; all the peripheral gas nozzles are vertically arranged in the base corresponding to the gas collecting cavity; each liquid inner nozzle comprises a liquid spraying pipe and a liquid storage chamber; a plurality of liquid inlet holes are uniformly distributed in the liquid storage chamber along the circumferential direction; the liquid spraying pipes are coaxially inserted into the corresponding peripheral gas nozzles, and circular seam-shaped gas direct-flow spraying channels are formed between the outer wall faces of the liquid spraying pipes and the corresponding peripheral gas nozzles. According to the invention, the atomization characteristic of a single nozzle can be researched, and the influence on the atomization characteristic by the mutual spraying relation among a plurality of nozzles can be researched by adjusting the number of the nozzles and the distance between the nozzles.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engine spray combustion, in particular to a rocket engine injection panel capable of studying the spray relationship among multiple nozzles. Background technique [0002] Liquid rocket engines are the main power plant for space vehicles and aircraft. Combustion instability is characterized by periodic changes in pressure oscillations and heat release, which directly determine the stability of the combustion chamber and engine. Combustion instability is believed to be the result of the coupling of dynamic processes (atomization, evaporation, mixing and chemical reactions) with the acoustic oscillations of the combustion chamber. The nozzle is the link between the supply system and the combustion chamber. Its atomization effect greatly affects the evaporation, mixing and combustion of the subsequent fuel, and has an important impact on the study of engine combustion instability. [0003] At ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/52
CPCF02K9/52
Inventor 黄卫东曹炜仝毅恒高玉超姜传金谢远楚威任永杰徐伯起杨云帆闫常春闫康聂万胜
Owner PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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