Supplying device of small-flow and high-temperature gas propellant

Abstract

The invention discloses a supplying device of a small-flow and high-temperature gas propellant, which belongs to the field of a gas supply system of a rocket engine. The device disclosed by the invention comprises a small combustion room, a sound speed nozzle assembly, a heat exchanger and a gas nozzle testing fitting, wherein one part of hydrogen-enriched gas generated by the small combustion room is supplied to the gas nozzle testing fitting to meet testing requirements, and the other part of the hydrogen-enriched gas generated is supplied to the heat exchanger to be used for heating oxygen and meeting the testing requirements; and the two parts of flow are controlled by the sound speed nozzle assembly. Under a certain flow, the temperature of the hydrogen-enriched gas can be adjusted by adjusting the ratio of hydrogen to oxygen, thereby realizing the purpose of adjusting the temperature. Under a certain mixing ratio condition, the flow adjustment is realized by enhancing or reducing the flows of the hydrogen and the oxygen. The temperature of the oxygen is controlled by adjusting the flow of the heated hydrogen-enriched gas.

Description

technical field [0001] The invention relates to a low-flow high-temperature gas propellant supply device, which belongs to the field of rocket engine gas supply systems. Background technique [0002] The full flow afterburning cycle engine system is currently the highest performing afterburning system. In the full-flow post-combustion cycle engine system, the propellants of all flow rates are combusted through two pre-combustion chambers, hydrogen-rich and oxygen-rich, to form hydrogen-rich gas and oxygen-rich gas to drive their respective turbines, and then enter the thrust chamber for supplementary combustion. The chamber inlet propellant is gas with relatively high temperature. Compared with the normal temperature hydrogen / oxygen propellant, its temperature is higher, the volume flow rate is larger, and the composition of the propellant at the entrance of the main combustion chamber changes. These changes will bring new effects on the combustion and the heat load of the ...

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Problems solved by technology

[0004] The purpose of the present invention is to solve the technical problems of the generation of small-flow hydrogen-rich gas, the temperature control of small-flow hydrogen-rich gas, and the heating of oxygen temperature, and provide a simple, easy-to-operate small-flow gas that can adjust the temperature and flow according to the needs of the test. Test rig for hydrogen-rich gas and oxygen for gas nozzle tests

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