Simulation experiment device for aero-engine suction object on-line static monitoring system

A simulation experiment device and aero-engine technology, applied in the direction of engine testing, measuring devices, electrostatic field measurement, etc., can solve the problems of reducing fatigue life, blade damage, blade fracture, etc., and achieve low-cost effects

Inactive Publication Date: 2013-04-24
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The former may occur during take-off or low-altitude flight, because the impact object is large, which will cause great damage to the engine, and even cause a major failure. In severe cases, it will cause a plane crash; Notches and pits o

Method used

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  • Simulation experiment device for aero-engine suction object on-line static monitoring system
  • Simulation experiment device for aero-engine suction object on-line static monitoring system
  • Simulation experiment device for aero-engine suction object on-line static monitoring system

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Embodiment Construction

[0020] Below in conjunction with accompanying drawing, the present invention is described in further detail:

[0021] As shown in the figure: the simulation experiment device of the on-line electrostatic monitoring system for aeroengine inhalation, including the airway extension tube 1, the particle injection device 2, the inlet ring sensor 3, 4, the aviation turbojet engine 4, and the ECU electronic control unit 5. Fuel pump 6, fuel control solenoid valve 7, oil tee 8, terminal monitoring display 9, start adjustment system 10, tail nozzle extension pipe 11, exhaust cooling device 12, installation platform 13.

[0022] The air inlet extension pipe 1 is connected to the air intake end of the aviation turbojet engine 4, and the particle injection device 2 communicates with the air inlet extension pipe 1 through the injection port on the air inlet extension pipe 1, and the upper part of the air inlet extension pipe 1 section layout monitoring device; one end of the tail nozzle ex...

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Abstract

The invention relates to a simulation experiment device for an aero-engine suction object on-line static monitoring system. An air inlet extension pipe is connected with an air inlet end of an aviation turbojet engine, a particle injection device is communicated with the air inlet extension pipe through an injection port in the air inlet extension pipe, and the air inlet extension pipe is provided with monitoring devices in a subsection mode. One end of an exhaust nozzle extension pipe is connected with a jet end of the aviation turbojet engine, and the other end of the exhaust nozzle extension pipe is connected with a tail gas cooling device. The air inlet extension pipe, the particle injection device, the aviation turbojet engine, the exhaust nozzle extension pipe and the tail gas cooling device are fixed on a mounting platform. The simulation experiment device can provide warning information at an early stage when the engine sucks abnormal particles and impeller damage breakdowns happen, effectively simulate engine gas path environment, and provide a low-cost and high-simulation effective experiment platform for research of the aero-engine suction object on-line static monitoring system.

Description

technical field [0001] The invention relates to an engine, and more particularly relates to an electrostatic monitoring system and a simulation experiment device for inhaled matter in an aero-engine intake duct. The invention belongs to the field of aero-engine condition monitoring and fault diagnosis. Background technique [0002] When the aero-engine is working, the fan and compressor blades are often impacted by foreign objects (such as birds, gravel, etc.) sucked by the high-speed airflow, causing damage. This foreign object (Foreign Object) is often referred to as FO. Existing studies divide FO into two categories: soft impact (birds, ice, etc.) and hard impact (gravel, small metal objects, etc.). The former may occur during take-off or low-altitude flight, because the impact object is large, which will cause great damage to the engine, and even cause a major failure. In severe cases, it will cause a plane crash; Notches and pits occur locally, resulting in residual ...

Claims

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Application Information

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IPC IPC(8): G01M15/00G01R29/12
Inventor 左洪福付宇刘鹏鹏王燕山张梅菊刘德峰谷风强宋文慧
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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