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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 pressure of the storage tank, the invention provides a gas-liquid parallel drive pre-charging system and method for starting at high altitude and low inlet pressure

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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