Thermal test device for real supply conditions of gas-pneumatic thrust chamber injectors

Abstract

The invention relates to the field of liquid rocket engines, in particular to a thermal test device for real supply conditions of an injector of a gas-pneumatic thrust chamber, so as to solve the problem that the existing thermal tests of the thrust chamber and its injector are aimed at the mixed combustion of liquid propellants Or the thrust chamber injector of gas-liquid mixed combustion, the test method and test device cannot be used in the hot test of the thrust chamber injector of gas-gas mixed combustion. The device includes a thrust chamber test piece unit, an oxygen-rich gas generator unit and a fuel-rich gas generator unit. The thrust chamber test piece unit includes the thrust chamber test piece, the thrust chamber test piece is used to install the injector under test, the oxygen-enriched gas generator unit includes the oxygen-enriched gas generator, the fuel-rich gas generator unit includes the rich-burn gas generator, The outlets of the oxygen-enriched gas generator and the fuel-rich gas generator are respectively connected to the thrust chamber test piece, and are used to supply oxygen-enriched gas and fuel-rich gas to the thrust chamber test piece.

Description

technical field [0001] The invention relates to the field of liquid rocket engines, in particular to a heat test device for real supply conditions of injectors in gas-pneumatic thrust chambers. Background technique [0002] The thrust chamber is the core component of a liquid rocket engine, and the performance and reliability of its injector have a major impact on the thrust chamber and even the entire engine. Therefore, in the development of liquid rocket engines, it is necessary to carry out thermal test research on thrust chamber injectors. [0003] The thrust chamber of the full-flow supplementary combustion cycle engine works by gas-gas mixed combustion, and the working medium is oxygen-enriched and combustion-enriched gas without liquid propellant. In the prior art, the thermal test of the thrust chamber and its injector is carried out for the thrust chamber injector of liquid propellant mixed combustion or gas-liquid mixed combustion, and neither the test method nor ...

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Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the existing thrust chamber and its injector heat test are all carried out for the thrust chamber injector of liquid propellant mixed combustion or gas-liquid mixed combustion, and the test method and test device cannot be used. In view of the problems in the thermal test of the thrust chamber injector of gas-gas mixed combustion, a thermal test device for the real supply conditions of the gas-gas thrust chamber injector is provided

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