Modular rocket engine propellant offset jetting panel capable of achieving threaded connection

A rocket engine and propellant technology, which is applied to rocket engine devices, jet propulsion devices, machines/engines, etc., to facilitate assembly and maintenance, reduce processing difficulty, and achieve uneven distribution

Active Publication Date: 2018-02-09
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

There is no injection panel specially designed for the research

Method used

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  • Modular rocket engine propellant offset jetting panel capable of achieving threaded connection
  • Modular rocket engine propellant offset jetting panel capable of achieving threaded connection
  • Modular rocket engine propellant offset jetting panel capable of achieving threaded connection

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Embodiment Construction

[0033] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0034] Such as figure 1 As shown, the rocket engine injection panel of the present invention adopts a modular form, including an end cover 1 , a nozzle assembly, a spark plug 2 and a propellant guide panel 4 . Wherein, the end cover 1 and the propellant deflector panel 4 are arranged sequentially and pressed together, as figure 2 shown. The spark plug 2 passes through the center hole of the end cap 1 and the propellant guide panel 4 in sequence, and the ignition end penetrates the outer end surface of the propellant guide panel 4 .

[0035] A sealing ring 7 is arranged between the propellant deflector panel 4 and the end cover 1 to form a sealed cavity for containing oxidant or fuel after being compressed; the end cover 1 is provided with an inlet 14 for passing the oxidant or fuel into the sealed cavity. Fuel; propellant deflector panel 4 is axially d...

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PUM

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Abstract

The invention discloses a modular rocket engine propellant offset jetting panel capable of achieving threaded connection. Center direct-current pieces, periphery rotational flow pieces and a propellant flow guide panel of a coaxial centrifugal nozzle are subjected to modular design, the processing difficulty can be lowered, and assembling and maintaining are facilitated. Based on the modular design of the nozzle assembly, the center direct-current pieces are designed to be in two types with center through holes and without center through holes, the periphery rotational flow pieces are also designed to be in two types with rotational flow holes and without rotational flow holes, and thus four types of different jetting modes can be realized when the nozzle assembly is assembled. The nozzlecan be combined by users according to the actual demands, the difference of all the nozzle jetting modes of the jetting panel can be achieved, and therefore uneven propellant distribution can be realized. When being used for studying the instable mechanism of liquid-propellant rocket engine combustion, the modular rocket engine propellant offset jetting panel solves the problem of low probabilityhappening to high-frequency instable combustion of a scale model gaseous oxygen/kerosene rocket engine.

Description

technical field [0001] The invention belongs to the technical field of liquid rocket engines, and in particular relates to a screw-connected modular rocket engine propellant offset injection panel. Background technique [0002] During the working process of large rocket engines, it is easy to induce self-excited high-frequency combustion instability, which is still a difficult problem restricting the development of liquid rocket engines. In order to study the mechanism of high-frequency combustion instability, the most direct way is to conduct experimental research on a full-scale engine, but it is often accompanied by high research costs and a long period of time. Therefore, considering economy and timeliness, the scale model engine is an ideal test device. According to the experimental research of Purdue University [Measurement and Analysis of Combustion Response to Transverse Combustion Instability], it shows that the scaled model engine needs more energy to produce comb...

Claims

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Application Information

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IPC IPC(8): F02K9/44F02K9/52F02K9/42F02K9/60
CPCF02K9/42F02K9/44F02K9/52F02K9/60
Inventor 石天一聂万胜郭康康陈朋苏凌宇刘瑜王辉
Owner PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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