High-frequency combustion instability coverall process simulation test automatic regulating system and method

An unstable and simulated test technology, applied in machines/engines, rocket engine devices, jet propulsion devices, etc., can solve the problems of high-frequency combustion instability, poor safety performance, high cost, and improve the level of automatic operation and parameters. Stable and guaranteed effect of parameters

Active Publication Date: 2010-12-08
NO 11 INST OF NO 6 ACADEMY OF CHINA AEROSPACE SCI & TECH
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Problems solved by technology

[0004] The purpose of the present invention is to provide an automatic adjustment system and method for the whole process simulation test of high-frequency combustion instability, which

Method used

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  • High-frequency combustion instability coverall process simulation test automatic regulating system and method
  • High-frequency combustion instability coverall process simulation test automatic regulating system and method
  • High-frequency combustion instability coverall process simulation test automatic regulating system and method

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Embodiment Construction

[0033] Technical scheme of the present invention is realized like this:

[0034] High-frequency combustion instability whole process simulation test automatic adjustment system, including control system, burner, heat exchanger, alcohol vaporizer, combustion chamber.

[0035] The combustion chamber is the head of the engine in real size, and its oxidant inlet and fuel inlet are connected to the heat exchanger and the alcohol vaporizer respectively. The oxidant and fuel are pure hot air at 350-450°C and alcohol vapor at a temperature of about 400°C. The remaining oxygen coefficient ranges from 0.6 to 1.1 during work. The hot air is provided by the heat exchanger, and after the cold air is heated by the heat exchanger, the hot air with a pressure of about 5MPa is formed and supplied to the combustion chamber. A sonic orifice DPH4, a pressure measuring point P5 and a temperature measuring point T2 are set at the oxidant inlet of the combustion chamber, and a sonic orifice DPH3, a...

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Abstract

The invention relates to high-frequency combustion instability coverall process simulation test automatic regulating system and method. The system comprises a control system, a combustor, a heat exchanger, an alcohol vaporizer and a combustion chamber, wherein the control system is used for regulating working conditions in the combustion chamber by a parameter input and flow regulating valve; the combustion chamber is an engine head with real size, an oxidant inlet and a fuel inlet of the combustion chamber are respectively communicated with the heat exchanger and the alcohol vaporizer, the oxidant inlet of the combustion chamber is provided with a sound velocity pore plate, a pressure measuring point and a temperature measuring point; the fuel inlet of the combustion chamber is provided with a sound velocity pore plate, a pressure measuring point and a temperature measuring point; and a cold air inlet of the heat exchanger is provided with a cold air flow regulating valve, and a heatsource of the heat exchanger is a combustor. The invention solves the technical problems of high cost, long period and poor safety property caused by adopting a real engine and a real working condition in the traditional simulation test, is very low in test cost, and lowers economic and labor costs.

Description

technical field [0001] The invention relates to the technical field of high-frequency combustion test technology of a liquid rocket engine combustion chamber, in particular to a test system and method that adopts a whole-process automatic adjustment of working conditions to stimulate a high-frequency unstable combustion process in a target combustion chamber. It can be used in the research of combustion stability of liquid rocket engines. Background technique [0002] High-frequency unstable combustion of liquid rocket engines is the most destructive unstable combustion, which is a problem involved in every engine and a key problem that needs to be solved in engine development. During the development of the liquid rocket engine, it can be used for the selection of the design scheme of the thrust chamber mixing head and the verification test of the combustion stability margin, and it can also be used for the verification test of the engine failure analysis and design improvem...

Claims

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Application Information

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IPC IPC(8): F02K9/96
Inventor 边东伟杜天恩王建军张晓军牛晓辙李文军
Owner NO 11 INST OF NO 6 ACADEMY OF CHINA AEROSPACE SCI & TECH
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