Adjustment structure and method for inherent frequencies of blades of overall blade disk of turbine

An integral blisk and natural frequency technology, applied in the direction of blade support components, engine components, machines/engines, etc., can solve problems affecting aerodynamic performance, small range, long design and processing cycle, etc., to achieve easy control of dimensional accuracy, process The effect of good performance and practical value of large projects

Active Publication Date: 2015-01-28
AECC SICHUAN GAS TURBINE RES INST
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Problems solved by technology

[0004] Purpose of the present invention: In order to solve the problems of the existing technology such as the small range of the natural frequency adjustment method of the turbine blisk blade, the long design and processing cyc

Method used

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  • Adjustment structure and method for inherent frequencies of blades of overall blade disk of turbine
  • Adjustment structure and method for inherent frequencies of blades of overall blade disk of turbine
  • Adjustment structure and method for inherent frequencies of blades of overall blade disk of turbine

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[0018] The present invention will be further described in detail below through specific embodiments:

[0019] See also figure 1 , figure 2 with image 3 ,among them, figure 1 It is a schematic diagram of the natural frequency adjustment structure of the integrated turbine blisk blade of the present invention. figure 2 Yes figure 1 Schematic diagram of A direction, image 3 Yes figure 2 Section B-B. There is a slit 3 of a certain width between each blade of the integrated turbine blisk 1 of the present invention. The slit forms a certain angle α with the axis of the engine. The radial depth of the slit is determined by the frequency value that needs to be adjusted. The width is 0.2~0.4, and the depth is 3~7mm from the rim. The greater the frequency of adjustment, the greater the depth value. The included angle range can better contain the root leaf shape. The end of each slit is processed with an anti-cracking hole 4. The crack arrest hole is circular with a diameter of 3 ...

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Abstract

The invention belongs to the overall blade disk technology of turbines and relates to an adjustment structure and method for the inherent frequencies of blades of the overall blade disk of a turbine. Firstly, the initial inherent frequencies of the blades of the overall blade disk of the turbine are measured; then, according to the measured frequencies, the excitation frequency of periodic pulsation of airflow or the result of dynamic stress measurement is combined and the blade frequency needing to be adjusted is calculated, so that the inherent frequency of each stage of the blades can have safe resonance frequency margin; then, according to the blade frequency needing to be adjusted, the space between every two blades of the overall blade disk is slotted, and the radial depth of each slot is determined according to the requirements of adjusting the frequency; a stop hole is formed in each slot bottom, and a pin is mounted in each stop hole. The structure and the method effectively reduce the inherent frequencies of the blades and change the stiffness, modes of vibration and vibration stress distribution of the blades, and the blades do not resonate or the important mode of vibration of resonance of the blades is tuned out the range of working speed. The structure and the method are simple and easy to operate and significant in frequency modulation effect, are easy to control size precision, and can meet actual requirements.

Description

technical field [0001] The invention belongs to the technology of turbine blisks, and relates to a structure and method for adjusting the natural frequency of a turbine integral blisk blade. Background technique [0002] With the continuous improvement of the performance of small aero-engines, the working load of the overall blade disk of the turbine is getting higher and higher, and the working conditions of the blades are getting worse and worse, resulting in the turbine rotor blades being subjected to the periodic excitation force of the uneven flow field. Obviously, the forced vibration of the overall blisk blade of the turbine will cause the high cycle fatigue failure of the overall blisk blade due to the large resonance stress. Therefore, in order to avoid the overall blisk blade from resonating during the working process, the natural frequency of each order of the blisk blade is adjusted to avoid the excitation frequency of the airflow, so as to eliminate the resonanc...

Claims

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Application Information

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IPC IPC(8): F01D5/16
CPCF01D5/10F01D5/34
Inventor 贺进李晓明谢强李超李世峰孙飞龑于进学
Owner AECC SICHUAN GAS TURBINE RES INST
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