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Rotating blade dynamic stress measuring method and system based on blade end timing

A technology of rotating blades and dynamic stress, which is applied in measuring force, measuring devices, measuring ultrasonic/sonic/infrasonic waves, etc., and can solve problems such as limited displacement and limited stress at the blade end

Inactive Publication Date: 2020-08-07
XI AN JIAOTONG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Aiming at the problems existing in the prior art, the present invention proposes a method and system for measuring the dynamic stress of rotating blades based on blade tip timing, which solves the problem that the blade tip timing technology can only measure the limited displacement and limited stress of the blade tip at present, and It has the advantage of simultaneously reconstructing the dynamic stress and equivalent stress of all elements on the surface and inside of the rotating blade

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  • Rotating blade dynamic stress measuring method and system based on blade end timing
  • Rotating blade dynamic stress measuring method and system based on blade end timing
  • Rotating blade dynamic stress measuring method and system based on blade end timing

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Embodiment Construction

[0043] The following will refer to the attached Figure 1 to Figure 7(c) 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 should not be 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.

[0044] 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. This specification and claims do not use differences in nouns as a way to distinguish components, but use differences in functions of components as a criterion for distinction. As mentioned throughout the specification...

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Abstract

The invention discloses a rotating blade dynamic stress measurement method and a rotating blade dynamic stress measurement system based on blade end timing. The rotating blade dynamic stress measurement method comprises the following steps of: establishing a three-dimensional finite element model of a to-be-measured rotating blade, and extracting modal parameters of the three-dimensional finite element model; determining a number and axial mounting positions of blade end timing sensors; constructing a conversion matrix of blade end finite position displacement and full-field dynamic stress, and establishing a conversion matrix of blade end finite position displacement to full-field equivalent stress; acquiring a blade end limited position displacement signal of the rotating blade based onthe blade end timing sensors; and acquiring dynamic stress of the rotating blade at any moment, at any position and in any direction based on the conversion matrix by the blade end limited position displacement signal, and acquiring equivalent stress of any unit of the rotating blade based on the conversion matrix by the blade end limited position displacement signal.

Description

technical field [0001] The invention belongs to the technical field of non-contact vibration testing of rotating blades of rotating machines, in particular to a method for measuring dynamic stress of rotating blades based on blade tip timing and a system thereof. Background technique [0002] As the core component of the aero-engine, the rotating blade plays an important role in the normal operation of the engine, and its integrity directly affects the safe operation of the overall structure of the aero-engine. Due to the influence of centrifugal force caused by high-speed rotation and the limitation of the material properties of the blade itself, the blade is prone to vibration fatigue cracks during service, resulting in failures such as fracture and missing corners. Studies have shown that high cycle fatigue caused by excessive blade vibration is the main failure mode of aeroengine blades. The high-cycle fatigue of the blade is mainly caused by the dynamic stress caused b...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/23G01H17/00G01L1/00G06F119/14
CPCG06F30/23G01H17/00G01L1/00G06F2119/14
Inventor 乔百杰陈雷敖春燕杨志勃陈雪峰
Owner XI AN JIAOTONG UNIV
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