Diagnostic method for gas path faults of aero-engine based on sliding mode theory

A technology for aero-engine and fault diagnosis, applied in electrical digital data processing, special data processing applications, instruments, etc., can solve problems such as huge engine maintenance and replacement costs, improve accuracy, enhance reliability, reduce false alarm rate and The effect of false negatives

Inactive Publication Date: 2016-10-26
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

The cost of engine repair and replacement is huge, accounting f

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  • Diagnostic method for gas path faults of aero-engine based on sliding mode theory
  • Diagnostic method for gas path faults of aero-engine based on sliding mode theory
  • Diagnostic method for gas path faults of aero-engine based on sliding mode theory

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Embodiment Construction

[0029] Taking the gas path fault diagnosis problem of a certain type of turboshaft engine as an example, the technical solution of the present invention will be described in detail in conjunction with the accompanying drawings:

[0030] Such as figure 1 Shown is the structural diagram of the turboshaft engine, the turboshaft engine includes components: intake port i; compressor ii; combustion chamber iii; gas turbine iv; power turbine v; exhaust pipe vi; Disturbance section 0; inlet inlet section 1; inlet outlet section (compressor inlet section) 2; compressor outlet section (combustion chamber inlet section) 3; combustion chamber outlet section (gas turbine inlet section) 4; gas turbine Exit section (power turbine inlet section) 5; power turbine outlet section (tail nozzle inlet section) 6; tail nozzle outlet section 7;

[0031] Step 1, according to the turboshaft engine structure figure 1 According to the component-level modeling method, the model of each component of the ...

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Abstract

The invention discloses a diagnostic method for gas path faults of an aero-engine based on the sliding mode theory. The method comprises following steps: intelligently correcting a non-linear part-stage model of the aero-engine based on an artificial bee colony algorithm; obtaining a self-adaptive liner model of the aero-engine based on error feedback sliding mode control; designing an expansion interface estimation sliding mode observer, and achieving fault diagnosis, separation and reconstruction of an engine sensor; achieving fault diagnoses of gas path faults of the engine. The diagnostic method for gas path faults of the aero-engine based on the sliding mode theory has following beneficial effects: as for the gas path faults of aero-engine, a correction method for a high-precision part-stage mode for the engine is put forward with the purpose of improving reliability and safety of a system; a new way of thinking for a self-adaptive linear model for the engine is put forward for providing a new strategy of gas path faults of the aero-engine; difficulties of gas path faults of the aero-engine and sensor faults are solved so that an effective and highly-reliable fault diagnoses method is put forward.

Description

technical field [0001] The invention belongs to fault diagnosis technology, and relates to an aeroengine model establishment and fault diagnosis method. Background technique [0002] The aeroengine is the heart of the aircraft, and its health status is of great significance to ensure flight safety and reduce maintenance costs. Ensuring flight safety through technical means is a very important content in the aviation industry, and has always been highly valued by aviation developed countries. According to statistics, engine failures account for a large proportion of flight failures and often cause catastrophic accidents. The cost of engine maintenance and replacement is huge, accounting for more than 60% of the regular maintenance costs of aircraft. Timely detection and accurate positioning of engine failures, elimination of potential safety hazards caused by engine failures, and ensuring safe, economical and reliable operation of aircraft are realistic problems that airlin...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/367
Inventor 肖玲斐杜彦斌胡继祥陈宇寒
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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