Differential isolating diaphragm valve and multi-propellant parallel liquid supply system
A technology of isolation diaphragm and differential type, which is applied in the direction of jet propulsion device, machine/engine, rocket engine device, etc., can solve the problem that the isolation diaphragm valve cannot be opened reliably, and achieve the elimination of rupture and its mutual influence, Improve the efficiency of use, good effect of isolation and sealing
Active Publication Date: 2022-07-05
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
[0004] The present invention aims to solve the problem that the isolation diaphragm valves at the outlets of multiple propellant storage tanks cannot be reliably opened when the current liquid rocket engine propellant is supplied, and provides a differential type isolation diaphragm valve
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[0032] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments of the present invention and the accompanying drawings. Obviously, the described embodiments do not limit the present invention.
[0033] like figure 1 and figure 2 As shown, a differential type isolation diaphragm valve in this embodiment includes a valve body 1 and a differential piston 2 arranged in the valve body 1;
[0034] The top port 3 at the upper end of the valve body 1 is communicated with the outlet of the tank, the lower end of the valve body 1 is provided with an air pressure balance hole 4, and the side of the valve body 1 is provided with a side port 5;
[0035] The lower part of the differential piston 2 is a cylindrical core, which is used for sliding with the valve body 1; The upward medium pressure uses the downward pulling force formed by the pressure at the side interface 5 of the valve body on the cylindrical core to...
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The invention relates to an isolation diaphragm valve, in particular to a differential type isolation diaphragm valve to solve the problem that the isolation diaphragm valves at the outlets of multiple propellant storage tanks cannot be reliably opened when liquid rocket engine propellant is supplied. The technical scheme adopted by the present invention is as follows: a differential type isolation diaphragm valve includes a valve body and a differential piston; the top interface on the upper end of the valve body is communicated with the outlet of the tank; the lower end of the valve body is provided with an air pressure balance hole; A side interface is provided on one side; the lower part of the differential piston is a cylindrical core, and the upper part of the differential piston is an I-shaped core structure; the I-shaped core includes a large cone frustum, a cylindrical core and a small Conical frustum, a first gap for medium flow is formed between the circumference of the large frustum and the side interface, a second gap is set between the peripheral surface of the small frustum and the valve body, and an annular ring is fixed coaxially at the second gap. Diaphragm; the bottom of the annular diaphragm is provided with an annular groove; the invention also provides a multi-propellant parallel liquid supply system.
Description
technical field [0001] The invention relates to an isolation diaphragm valve, in particular to a differential type isolation diaphragm valve and a multi-propellant parallel liquid supply system. Background technique [0002] The isolation diaphragm valve is an important valve component in the liquid rocket engine propellant storage and supply unit, and is generally installed at the inlet or outlet of the storage tank. When the isolation diaphragm valve is set at the outlet of the tank, its function is to ensure reliable isolation of the propellant in the tank before the system pressurization works. . [0003] The components of the propellant include oxidant and fuel, etc. The oxidant and fuel of many existing liquid power systems have adopted two-tank, three-tank and other parallel liquid supply schemes, but due to the current common isolation diaphragm valve rupture pressure difference There is a certain dispersion difference. During the pressurization process of the syst...
Claims
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IPC IPC(8): F02K9/58F02K9/60
Inventor 朱建国宁建华王吉平宋振平闫旭宇李超张程程葛洋
Owner XIAN AEROSPACE PROPULSION INST