Aerial engine air passage electrostatic monitoring system and analog experiment apparatus

An aero-engine and monitoring system technology, which is applied in the direction of engine testing, measuring devices, electrostatic field measurement, etc., can solve problems such as the difficulty of realizing online real-time monitoring and the inability to provide early warning information

Inactive Publication Date: 2008-07-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0003] The present invention aims at the shortcomings that the existing monitoring technology is difficult to realize online real-time monitoring, and cannot pro

Method used

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  • Aerial engine air passage electrostatic monitoring system and analog experiment apparatus
  • Aerial engine air passage electrostatic monitoring system and analog experiment apparatus

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Embodiment Construction

[0021] Fig. 1 is a composition block diagram of an aero-engine air circuit static monitoring system of the present invention. It installs the electrostatic sensor in the exhaust nozzle of the aero-engine to monitor the change of the electrostatic field generated by the charged particles in the engine gas path, and the current change signal induced by the electrostatic sensor is input to the signal conditioning circuit, and the input current is adjusted by the signal conditioning circuit After the signal is amplified and filtered, the signal is obtained by the signal acquisition card and sent to the computer for analysis and processing, so as to realize the purpose of online monitoring of the gas circuit of the aeroengine.

[0022] Fig. 2 is a schematic diagram of the composition of the simulation test device of the aeroengine gas circuit static monitoring system of the present invention. Including oil burner 1, electrostatic powder sprayer 2, gas circuit electrostatic monitori...

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Abstract

A gas-path electrostatic monitor system of an aero-engine and a simulation test device belong to the field of gas-path stage monitor and fault diagnosis of the aero-engine. The monitor system comprises an electrostatic sensor, a signal conditioning circuit, a signal collection card and a computer. The simulation test device comprises a fuel oil burner (1), an electrostatic duster, the gas-path electrostatic monitor system, a flange (3), a first pipe (4), a rub-impact device (5), a second pipe (6), a third pipe (8), an exhaust pipe (9), an axial fan (10), a medium-pressure fan (11), a rub-impact device support platform (12) and a bracket (13). The invention can monitor the state of the engine and provide fault alarm information by monitoring the general electrostatic charge level of the gas path of the engine by the electrostatic monitor arranged at the nozzle at the tail portion of the engine. The constructed simulation test device simulates the gas-path operation state of the engine and the direct results of normal faults, thus providing a simulation test platform for early study of gas-path electrostatic monitor system of the aero-engine.

Description

technical field [0001] The invention monitors the change of the overall charge level of the air path of the aeroengine to monitor the working state of the air path components of the aeroengine on-line in real time, provides early warning information for the early failure of the air path components of the engine, and improves the health status management ability of the engine. The constructed test device is used to simulate the air path environment of the aero-engine tail nozzle, and the simulation experiment at normal temperature and high temperature is carried out by using electrostatic powder sprayer, fan, pipeline and test system. The invention belongs to the field of aero-engine condition monitoring and fault diagnosis. Background technique [0002] In the complex mechanical system of an aero-engine, air path components become the main source of failure due to its harsh working environment. Research on how to monitor the working status of engine air path components is an...

Claims

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Application Information

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IPC IPC(8): G01M15/00G01R29/12
Inventor 左洪福文振华李耀华王华冯丽娜
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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