Gas-gas thrust chamber injector real supply condition thermal test device

Abstract

The invention relates to the field of liquid rocket engines, particularly relates to a gas-gas thrust chamber injector real supply condition thermal test device, and aims to solve the problem that existing thrust chambers and injectors thereof are subjected to a thermal test aiming at liquid propellant blending combustion or gas-liquid blending combustion thrust chamber injectors, and both a test method and a test device cannot be used in a thermal test of a thrust chamber injector for gas-gas blending combustion. Both a test method and a test device cannot be used in a hot test of a thrust chamber injector for gas-gas blending combustion. The device comprises a thrust chamber test piece unit, an oxygen-enriched gas generator unit and a fuel-enriched gas generator unit, wherein the thrust chamber test piece unit comprises a thrust chamber test piece, the thrust chamber test piece is used for installing a tested injector, the oxygen-enriched gas generator unit comprises an oxygen-enriched gas generator, the fuel-enriched gas generator unit comprises a fuel-enriched gas generator, outlets of the oxygen-enriched gas generator and the fuel-enriched gas generator are connected with the thrust chamber test piece separately, and the oxygen-enriched gas generator and the fuel-enriched gas generator are used for supplying oxygen-enriched gas and fuel-enriched 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, an...

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