Gas-liquid parallel driving pre-pressurizing system and method started by high-altitude low inlet pressure

A technology of inlet pressure and pressurization system, which is applied in the direction of jet propulsion devices, machines/engines, rocket engine devices, etc., can solve the problems of aircraft carrying capacity reduction, main pump cavitation, etc., achieve volume and weight reduction, and small demand , the effect of low energy

Inactive Publication Date: 2019-02-22
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology

[0003] In order to solve the cavitation of the main pump and avoid the technical problem of reducing the carrying capacity of the aircraft caused by increasing the

Method used

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  • Gas-liquid parallel driving pre-pressurizing system and method started by high-altitude low inlet pressure

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Embodiment Construction

[0023] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0024] 1) System configuration

[0025] Such as figure 1 As shown, the gas-hydraulic parallel drive pre-charging system needs to set up relevant components to switch between gas and liquid driving media. The system includes a main pump 1, a pre-press pump 2, a pre-press turbine 3, a blender 5, a high-pressure gas supply system, a high-pressure gas check valve 11, a switching valve 12 and a check valve 13; the inlet and storage of the pre-press pump 2 The outlet of the tank is communicated, the outlet of the pre-compression pump 2 is connected to an inlet of the blender 5 through the first pipeline 7, and the outlet of the pre-compression turbine 3 is connected to the other inlet of the blender 5 through the second pipeline 8, and the The outlet of the mixer 5 is connected to the inlet of the main pump 1 through the third pipeline 9, and a part of the propellant at ...

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Abstract

The invention relates to a gas-liquid parallel driving pre-pressurizing system and method started by high-altitude low inlet pressure in order to solve the technical problems of main pump cavitation erosion and aircraft carrying capacity reduction caused by storage box pressure increasing. An inlet of a pre-pressurizing pump communicates with an outlet of a propellant storage box, and an outlet ofthe pre-pressurizing pump is connected to one inlet of a mixer through a first pipeline; an outlet of a pre-pressurizing turbine is connected to the other inlet of the mixer through a second pipeline, and an outlet of the mixer is connected to an inlet of a main pump through a third pipeline; part of a propellant at an outlet of the main pump is connected with an inlet of the pre-pressurizing turbine through a fourth pipeline, the flow is controlled through a throttle ring, and the other propellant at the outlet of the main pump enters downstream pipelines; and a high-pressure gas supply system is connected with the inlet of pre-pressurizing turbine through a fifth pipeline, a high-pressure gas one-way valve is arranged in the fifth pipeline, a switching valve is connected to the second pipeline, and a one-way valve is arranged in the fourth pipeline.

Description

technical field [0001] The invention relates to a gas-liquid parallel drive pre-charging system and method suitable for starting at high altitude and low inlet pressure. Background technique [0002] In pumped liquid rocket engines with large flow, high speed, and high head, the pre-pressurization system is usually used in the stable section to increase the inlet pressure of the main pump and prevent cavitation of the main pump. The pre-pressurization system generally includes a pre-press pump and a pre-press turbine arranged coaxially. The inlet of the pre-press pump communicates with the outlet of the storage tank, the outlet of the pre-press pump is connected with the inlet of the main pump, and the outlet of the pre-press turbine is mixed connected to the inlet of the main pump. The main pump is connected to the inlet of the pre-pressure turbine through another pipeline. In the stable working section, the pre-compression turbo pump is usually driven by the high-pressur...

Claims

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Application Information

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IPC IPC(8): F02K9/46
CPCF02K9/46
Inventor 王海燕邢理想龚南妮马楠李春红陈文张航
Owner XIAN AEROSPACE PROPULSION INST
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