Large flow liquid oxygen supercooling method based on supersonic ejector

Abstract

The invention discloses a large flow liquid oxygen supercooling method based on a supersonic ejector. The large flow liquid oxygen supercooling method comprises the steps that a heat exchanger used inconventional saturated liquid nitrogen supercooling liquid oxygen is used as a primary heat exchanger, and the liquid oxygen with a supercooling flow rate greater than 4500 L/min can be supercooled from 92K to 80K; a secondary heat exchanger is arranged at the downstream position of the primary heat exchanger to supercool the liquid oxygen which is supercooled to 80K and with the supercooling flow rate greater than 4500L/min to below 67K; the secondary heat exchanger is filled with liquid nitrogen in a saturated state, the temperature of the liquid nitrogen in the secondary heat exchanger isno more than 64K, and an air outlet of the secondary heat exchanger is connected with an ejected airflow inlet of the supersonic ejector; an ejector airflow inlet of the supersonic ejector is connected to a gas outlet of a gas generator; the supersonic ejector sequentially includes a mixing section, a super-expansion section and a sub-expansion section which are arranged coaxially in the directionof the airflow; and the mixing section is a conical isobaric mixing chamber with a contracted cross section. The large flow liquid oxygen supercooling method can meet the needs of rapid cooling and filling of large-flow liquid oxygen before launching such as CZ-5. In addition, the pumping capacity of the supersonic ejector can be matched with the load, and more security and reliability are achieved.

Description

technical field [0001] The invention relates to the field of aerospace low-temperature launch vehicles, in particular to a large-flow liquid oxygen supercooling method based on a supersonic ejector. Background technique [0002] With the vigorous development of my country's aerospace industry, new requirements are put forward for the carrying capacity of launch vehicles. In order to improve the carrying capacity and meet the implementation needs of future large-scale space stations and lunar exploration projects, the Long March 5, 6 and 7 launch vehicles using cryogenic liquid propellants have been put into use one after another. At present, the low-temperature propellants used in launch vehicles are all in a saturated state, and most of their thermodynamic states are near the boiling point, with insufficient thermophysical properties, especially low density and sensible cooling per unit volume. When the mass of the cryogenic propellant is constant, the low density will lea...

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Problems solved by technology

[0009] As the link between the base and the industrial sector, the applicant, through the cooperation of the colleges, the base, and the industrial sector, aimed at the fact that the domestic vacuum compressor technology level is difficult to meet the needs of large-flow liquid oxygen rapid subcooli

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