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Fluid flow resistance adjusting device

A technology of adjusting device and flow resistance, applied in the aerospace field, can solve the problems of blocked orifice, no working medium filtering device, poor operability, etc., to ensure the stability of flow resistance, make up for defects and instability, and be suitable high sex effect

Active Publication Date: 2018-10-16
SHANGHAI INST OF SPACE PROPULSION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Because the orifice plate cannot be disassembled after installation, the operability is poor, and there is no working medium filter device, there is a risk of the orifice being blocked

Method used

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Embodiment Construction

[0029] The present invention will be described in further detail below in conjunction with the abstract accompanying drawings.

[0030] Such as Figure 1-Figure 7 As shown, the embodiment of the present invention provides a fluid flow resistance adjustment device, including a lock-shaped structure, a flow resistance adjustment orifice, and a seal and filter assembly. The flow resistance adjustment orifice includes an orifice body 1, an O-ring seal Groove 2, working fluid radial inlet hole 5, working fluid axial inlet hole 9 and throttling small hole 14; the sealing and filtering assembly includes square welding piece 1 3, square filter screen 4, square welding piece 2 6, annular Filter screen 7, annular welding piece 8, O-ring 11; Described locking structure comprises lock bottom passage 12 and guide boss 13; The front end of described orifice plate body 1 is connected with guide boss 13 through lock bottom passage 12, can Through the lock-shaped structure composed of the bot...

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PUM

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Abstract

The invention discloses a fluid flow resistance adjusting device which comprises a lock-shaped structure, a flow resistance adjusting pore plate and a sealing and filtering assembly. The flow resistance adjusting pore plate comprises a pore plate body, an O-shaped ring sealing groove, a working medium radial entering hole, a working medium axial entering hole and a throttling small hole. The sealing and filtering assembly comprises a first square soldering lug, a square filter net, a second square soldering lug, an annular filter net, an annular soldering lug and an O-shaped ring. The lock-shaped structure comprises a lock bottom channel and a guide boss. The diameter of a pore inside the pore plate is set to enable the pore plate to have different flow resistance characteristics, and therefore pressure adjusting requirements of an upstream pipeline system of a liquid engine and an electric thruster are met. The device integrates the functions of flow resistance adjusting, working medium filtering and detaching and can be placed in a pipeline connector according to using requirements, the space in the connector is sufficiently utilized, additional final assembly layout is not needed, the structure is compact, and the device has the advantages of being small in size, low in weight, high in reliability, convenient to install and detach, high in handleability and wider in application range.

Description

technical field [0001] The invention relates to the aerospace field, in particular to a fluid flow resistance adjusting device. Background technique [0002] When the electric thruster is discharging, the pressure of the working fluid at the cathode and anode inlets of the thruster must be the rated pressure to ensure the normal operation of the electric thruster. At present, the working fluid storage and supply system of aerospace electric propulsion usually adopts the micro-channel method to adjust the pressure of the working medium at the inlet of the cathode and anode, such as capillary, etching flow channel and other schemes. Due to the defects and instability of the manufacturing process, the actual flow resistance and There is a certain difference in the design value, which cannot meet the rated pressure requirements of the cathode and anode inlets of the electric thruster at the same time. [0003] When the chemical engine is ignited, the combustion chamber also nee...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/057F02C7/055F02C9/16F02C9/20F02C9/32F03H1/00
Inventor 熊森康亮杰肖开阳赵杨苗鹏宋娜刘鹏
Owner SHANGHAI INST OF SPACE PROPULSION