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A Method of Correcting the Natural Frequency of Aeroengine Fan Blades

A technology of aero-engines and fan blades, which is applied in the direction of machines/engines, liquid fuel engines, mechanical equipment, etc. It can solve the problems of difficult frequency difference of blades and failure to meet the frequency matching requirements, and achieve the effect of reducing production costs

Active Publication Date: 2019-09-10
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a method for correcting the natural frequency of an aeroengine fan blade, so as to solve the problem that the blade frequency difference is difficult to exceed 15HZ in the actual production process and cannot meet the frequency matching requirements

Method used

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  • A Method of Correcting the Natural Frequency of Aeroengine Fan Blades
  • A Method of Correcting the Natural Frequency of Aeroengine Fan Blades
  • A Method of Correcting the Natural Frequency of Aeroengine Fan Blades

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Embodiment Construction

[0022] The method for correcting the natural frequency of the fan blade of an aero-engine has the following steps:

[0023] (1) Determination of frequency distribution requirements for the entire blade of the fan rotor

[0024] The frequency arrangement of fan rotor blades has a great relationship with the vibration of the engine, and fatigue cracks due to vibration are one of the common faults of the blades. Therefore, the design drawings put forward the following requirements for the frequency distribution of the entire blade of the fan rotor: the arrangement of the entire blade; the frequency difference between adjacent blades; the arrangement position of pairs of blades with different frequency differences; the maximum frequency difference of the entire blade, etc. . The fan rotor blades of an engine are made of titanium alloy TC6, the part numbers are SA1 and SA2, and there are 17 pieces for a single unit, totaling 34 pieces. The profile requirements of the fan rotor bl...

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Abstract

The invention discloses a correction method of inherent frequency of aeroengine fan blades. The correction method comprises the following steps: I, determining an arrangement mode of whole blades, determining a frequency difference between adjacent blades, determining an arrangement position of paired blades with different frequency differences, and determining the maximum frequency difference ofthe whole blades, thereby determining a requirement for frequency distribution for the whole blades of a fan rotor; II, calculating an inherent vibration frequency value of the blades; III, carrying out selection and judgment on frequency values of profile grouping calculation according to an arrangement requirement for frequency selection of a single blade and a frequency difference value of adjacent blades to find out a group meeting the frequency arrangement requirement; and IV, adjusting the contour thickness of a corresponding section of the profile of a blade body to realize the frequency selection requirement of the whole blades.

Description

technical field [0001] The invention belongs to the field of manufacturing fan blades of aero-engines, in particular to a method for correcting the natural frequency of fan blades of aero-engines. Background technique [0002] The fan rotor blade is an important part of an aero-engine. It not only requires stricter dimensional accuracy, but also proposes frequency detection and technical requirements related to the performance of a single frequency requirement according to specific requirements. The fan rotor blades of a certain type of engine are made of titanium alloy TC6, the part numbers are SA1 and SA2, and there are 17 pieces for a single unit, totaling 34 pieces. The design drawings require that the blades SA1 and SA2 are arranged in a "sawtooth shape", the frequency difference between adjacent blades is not less than 9Hz, the paired blades with a frequency difference of not less than 15HZ should be arranged at intervals, and the maximum frequency difference of the en...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/66F04D29/38G06F17/50
CPCF04D29/388F04D29/661F05D2230/18G06F30/17G06F30/23
Inventor 魏萍卢晓星雷海峰张义德李承彬赵赟汤婷婷梁忠效
Owner AECC AVIATION POWER CO LTD
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