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Method and system for measuring rotor blade dynamic strain field based on blade tip timing

A technology of rotor blades and measurement methods, applied to vibration measurement in solids, vibration testing, measuring devices, etc., can solve the problems of low survival rate, reliability and continuous working time

Active Publication Date: 2020-10-27
XI AN JIAOTONG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

For a long time, aeroengine blades have achieved dynamic strain measurement by pasting strain gauges on the surface of rotor blades, which can only measure dynamic strain at limited positions on limited blades, and their reliability and continuous working time are low, especially in high temperature environments. A large number of strain gauges are arranged on the blade, often only a few strain gauges can obtain effective information, and the survival rate is extremely low

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  • Method and system for measuring rotor blade dynamic strain field based on blade tip timing
  • Method and system for measuring rotor blade dynamic strain field based on blade tip timing
  • Method and system for measuring rotor blade dynamic strain field based on blade tip timing

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Embodiment Construction

[0048] The following will refer to the attached Figure 1 to Figure 8(b) Specific examples of the present invention are described in more detail. Although specific embodiments of the invention are shown in the drawings, it should be understood that the invention may be embodied in various forms and is not limited to the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present invention and to fully convey the scope of the present invention to those skilled in the art.

[0049] It should be noted that certain terms are used in the specification and claims to refer to specific components. Those skilled in the art should understand that they may use different terms to refer to the same component. The specification and claims do not use differences in nouns as a way of distinguishing components, but use differences in functions of components as a criterion for distinguishing. "Includes" or "comprises" mentioned througho...

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Abstract

The invention discloses a rotor blade dynamic strain field measurement method and system based on blade tip timing. The method includes the following steps: establishing a three-dimensional finite element model of the rotor blade to be measured, and extracting the modal of the three-dimensional finite element model. parameters; determine the number of blade tip timing sensors and the circumferential installation position; establish the mapping relationship between the blade single-point displacement and the full-field dynamic strain; obtain the rotor blade tip single-point displacement based on the blade tip timing sensor, and the single-point displacement The mapping relationship obtains the dynamic strain measurement of the rotor blade at any position and in any direction. The method provided by the invention only uses the limited measuring points at the blade end to realize the reconstruction of the overall dynamic strain field of the rotor blade, and can realize the measurement of the normal strain and shear strain of the rotor blade surface and all internal nodes under multi-modal vibration, and the calculation process is simple. Easy to measure online.

Description

technical field [0001] The invention belongs to the technical field of non-contact vibration testing of rotating machinery rotor blades, in particular to a method and system for measuring dynamic strain field of rotor blades based on blade tip timing. Background technique [0002] The integrity of high-speed rotor blades directly affects the safe operation of the overall structure of the aero-engine. Affected by factors such as harsh working environment and strong alternating loads, it is easy to generate vibration fatigue cracks during service and cause serious accidents. High cycle fatigue caused by excessive blade vibration is the main failure mode of aeroengine blades. Blade high cycle fatigue is mainly caused by dynamic stress caused by various aerodynamic loads and mechanical loads, and a large number of cycles can accumulate fatigue cracks in a short period of time, especially when the blade resonates, dynamic stress can easily lead to blade fatigue failure. In the d...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01B21/32G01M7/02
CPCG01B21/32G01M7/025G01H1/003G01B11/16F01D17/06F05D2270/808F05D2240/307F05D2260/81G01M5/0016G01M5/0066G01M5/0041G01M7/00F01D5/14
Inventor 乔百杰陈雪峰敖春燕何卫锋杨来浩
Owner XI AN JIAOTONG UNIV