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Integrated force-bearing and flow-equalizing top cover device

An integrated, rectifying device technology, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve the problems of high nozzle mixing ratio, related to thrust chamber combustion efficiency, stability, nozzle ablation, etc., to achieve Avoid structural damage, avoid propellant leakage and structural damage, and reduce the effect of fluid velocity

Active Publication Date: 2021-12-03
BEIJING AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The pressure distribution of the flow field inside the cavity composed of the top cover, etc. affects the uniformity of the flow distribution entering the nozzles of the injector, which is directly related to the working performance of the thrust chamber such as combustion efficiency and stability, and even when the flow distribution is uneven. The local mixing ratio of the nozzle is high, resulting in nozzle ablation

Method used

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  • Integrated force-bearing and flow-equalizing top cover device
  • Integrated force-bearing and flow-equalizing top cover device
  • Integrated force-bearing and flow-equalizing top cover device

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Embodiment Construction

[0028] The present invention proposes an integrated load-bearing and current-equalizing top cover device, such as figure 1 As shown, it includes butt flange 1, inlet section 2, top cover 3, bearing device 4, rectifying device 5 and support rib 6;

[0029] The port of the docking flange 1 is the propellant inlet, and the docking flange 1 is connected to the top cover 3 through the inlet section 2, and radial support ribs 6 are arranged around the inlet section 2, as shown in figure 2 As shown, the butt flange 1, the inlet section 2 and the top cover 3 are respectively connected; the upper end of the top cover is connected with the bearing device 4 for thrust transmission; the lower end of the top cover 3 is connected with the rectification device 5 for ensuring that the propellant entering each nozzle Evenly distributed. The cross-section of the top cover 3 is double-humped, and the central cavity is a circular platform with a central hole, which is used for connection and in...

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PUM

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Abstract

The invention provides an integrated force-bearing and flow-equalizing top cover device, which comprises a butt flange, an inlet section, a top cover, a force-bearing device, a rectifying device and supporting ribs; a port of the butt flange is a propellant inlet, the butt flange is connected with the top cover through an inlet section, the radial supporting ribs are arranged around the inlet section, and the supporting ribs are connected with the butt flange, the inlet section and the top cover respectively; the upper end of the top cover is connected with the force-bearing device for transmitting thrust; the lower end of the top cover is connected with the rectifying device for ensuring uniform distribution of propellants entering nozzles; the cross section of the top cover passing through the axis is in a double-peak shape, and a center concave cavity is a circular-truncated-cone-shaped platform with a center hole and used for connection and installation of an igniter; the top cover is provided with a radial window for operating and installing the igniter or leading out an igniter cable; and the top cover is also provided with a hoisting hole for hoisting. The integrated force-bearing and flow-equalizing top cover device provided by the invention can bear internal pressure, can transmit thrust, is high in pressure and flow distribution uniformity, and is integrally formed without welding.

Description

technical field [0001] The invention relates to an integrated force-bearing and flow-equalizing top cover device, which can be used in the fields of aerospace, thermal energy engineering and combustion technology. Background technique [0002] The thrust chamber of a liquid rocket engine works under high temperature, high pressure and complex vibration environment. The head of the thrust chamber mainly includes structures such as bearing seats, top covers, injectors, collectors, etc. As the engine thrust chamber, the number of parts is the largest and the structure is the most complex. , the most welded / connected parts, its structural reliability is directly related to the reliability of the thrust chamber work. [0003] After the thrust chamber converts the chemical energy of the fuel into heat energy, it is ejected through the nozzle to generate thrust. The thrust is transmitted to the gimbal through the bearing seat of the thrust chamber head, and almost all the thrust i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/62
CPCF02K9/62
Inventor 刘倩丁兆波潘刚王洋洲张亚孔维鹏潘亮孙纪国郑孟伟谢恒
Owner BEIJING AEROSPACE PROPULSION INST
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