A low-temperature fluid variable-condition pump delivery system

Abstract

The invention provides a cryogenic fluid variable-working-condition pumping pressure type conveying system which is formed by connecting a pressure reducer 1, an electromagnetic valve 2, a pore plate 3, a valve 4, a vaporizer 5, a valve 6, a regulating valve 7, a temperature sensor 8, a pressure sensor 9, a filter 10, a terminal 11, a flowmeter 12, a regulating valve 13, a valve 14, a valve 15, a variable frequency motor 16, a centrifugal pump 17, a valve 18, a container 19 and a pipeline. The cryogenic fluid variable-working-condition pumping pressure type conveying system is used for conveying cryogenic fluid in a pumping pressure manner, and accurate control of conveying flow of cryogenic fluid is realized through accurately controlling pressurizing gas flow and pump frequency and combining aperture of the regulating valves. Outer air source pressurization and vaporizer pressurization are adopted. The pressure reducer, the electromagnetic valve, the vaporizer, the centrifugal pump, the variable frequency motor and the regulating valves constitute an accurate pressure control assembly, and the accurate pressure control assembly regards conveying flow, pressurized air flow, pump inlet pressure and the like as measurement and control objects. The variable flow control technology contained in the cryogenic fluid variable-working-condition pumping pressure type conveying system can be used in the field of projects adopting cryogenic fluid conveying and needing variable flows.

Description

technical field [0001] The invention relates to a variable flow conveying technology of cryogenic fluid, which is applied to the test of cryogenic liquid rocket power system and other fields of cryogenic liquid conveying. Background technique [0002] The power system test is the largest ground test before the flight test of a newly developed rocket. It is the test of the power system closest to the flight state, and it is a key link in the development process of the launch vehicle. At present, the development trend of domestic and foreign launch vehicles is non-toxic and non-polluting, and most of them use low-temperature propellants, such as liquid oxygen / kerosene and liquid oxygen / liquid hydrogen. The power system test is to simulate the actual rocket launch process to the greatest extent. The filling process is based on the requirements of the launch site test and launch process, and the rocket body storage tank is filled with low-temperature propellant. The characteris...

AI Technical Summary

Problems solved by technology

The characteristics of the low-temperature propellant filling system are: ①There are many working conditions, and the tank scale, filling pressure and flow rate of different tests are different, and it covers a wide flow range; There are many test systems, and the entire filling process must strictly follow the test process and filling indicators, any failure may lead to the failure of the entire test

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