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Method for detecting dangerous part at front edge of aero-engine blade

An aero-engine and blade leading edge technology, applied in computer-aided design, special data processing applications, instruments, etc.

Active Publication Date: 2019-08-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, at this stage, there is still a lack of a strict detection method for the dangerous part of the leading edge of the aeroengine blade.

Method used

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  • Method for detecting dangerous part at front edge of aero-engine blade
  • Method for detecting dangerous part at front edge of aero-engine blade
  • Method for detecting dangerous part at front edge of aero-engine blade

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Embodiment Construction

[0021] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0022] to combine figure 1 As shown, the present invention provides a method for judging the dangerous position of the leading edge of an aeroengine blade, and the specific implementation steps are as follows:

[0023] (1) Blade dynamic stress test: The dynamic stress test of the aeroengine blade is carried out on the engine test bench. During the test run of the aeroengine according to the operating speed, the strain data monitored by the strain gauge at the measuring point is used to analyze the collected dynamic strain signals. processing to obtain the actual natural frequency f of the blade under working conditions d , and the true vibration stress σ of the measuring point in the resonance state t [1]; In this step, the method of monitoring strain data by measuring point strain gauges can refer to the specific implementation of ...

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Abstract

The invention discloses a method for detecting a dangerous part at the front edge of an aero-engine blade. The method comprises the steps of carrying out a dynamic stress test in an aero-engine working state test run, carrying out finite element modal calculation on blades, extracting a vibration stress simulation result under a modal corresponding to a dynamic stress test result, and the like. The stress level of each part of the front edge of the aero-engine blade under the working load can be detected, the dangerous part of the front edge of the aero-engine blade and the possible damage size during service can be accurately obtained, and data support can be provided for design of foreign object damage resistance of the aero-engine blade and formulation of a foreign object damage repairprinciple.

Description

technical field [0001] The invention relates to the field of detection of aeroengine blades. Background technique [0002] When an aero-engine is in service near the ground, it will inevitably inhale hard objects such as stones and metal fragments. These foreign hard objects will hit the leading edge of the aero-engine fan or compressor blade at a relative speed of 100m / s-350m / s, causing severe impact damage. The impact damage of this foreign hard object is called "foreign object damage" (abbreviated as FOD, Foreign ObjectDamage). [0003] The fatigue strength of damaged blades will be greatly reduced, and unpredictable fatigue fractures will occur during the service of the engine, resulting in serious flight accidents. In the current stage of aeroengine blade design, the damage tolerance design of foreign object damage has become an indispensable part. The working load of an aeroengine blade is the coupling effect of the steady-state stress generated by the centrifugal f...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23G06F30/15G06F2119/06
Inventor 赵振华张钧贺陈伟
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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