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Turbine blade strain field full-field measurement method based on dual-mode fusion

A technology of turbine blades and measurement methods, which is applied in the directions of measurement devices, optical radiation measurement, radiation pyrometry, etc., can solve the problems of difficult installation and wiring, obstacles to the stress and strain state of turbine rotor blades, and low upper limit of strain field application temperature. Strain situation accurate effect

Active Publication Date: 2021-06-22
UNIV OF ELECTRONICS SCI & TECH OF CHINA
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Problems solved by technology

The measurement of blade strain and the reconstruction of the strain field are the key points and difficulties in the field of aeroengine turbine blade testing. At present, the method of using high-temperature strain gauges belongs to the contact point-to-point measurement method, which has difficulties in installation and wiring, and it is difficult to reconstruct the strain field and the application temperature. The problem of low upper limit seriously hinders the research on the stress-strain state of turbine rotor blades under high temperature and high pressure environment

Method used

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  • Turbine blade strain field full-field measurement method based on dual-mode fusion
  • Turbine blade strain field full-field measurement method based on dual-mode fusion
  • Turbine blade strain field full-field measurement method based on dual-mode fusion

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Embodiment Construction

[0032] Such as figure 1 As shown, the dual-mode probe 1 enters the interior of the engine through the reserved hole of the engine casing wall 3, and the inside of the engine casing wall 3 mainly includes the engine shaft 4 and the turbine blades 5, and the turbine blades 5 are exposed to high temperature and high pressure. High-speed rotation in a gas environment, thereby driving the rotation of the engine shaft 4, the dual-mode probe 1 will put the probe used for sensing into the engine, and the probe will cooperate with the light hole through a reflector , transmitting the optical information of the blade along the probe tube to the dual-mode optical path 2 at the rear end of the dual-mode probe 1 , the dual-mode optical path 2 mainly includes an imaging optical path 8 and an infrared optical path 1 .

[0033] Aeroengine turbine blades work in an extreme environment of high temperature and high pressure, but the turbine blades are in the steady state of the engine. Due to th...

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Abstract

The invention provides a turbine blade strain field full-field measurement method based on dual-mode fusion, and belongs to the field of aero-engine turbine blade strain measurement and data processing thereof. Two measurement methods are fused, an imaging measurement mode and an infrared measurement mode are achieved, and digital image signals and infrared signals are collected at the same time through one probe and processed in an upper computer system in a centralized mode. According to the invention, a digital image technology and an infrared photoelectric measurement technology are combined, so that strain measurement of the turbine rotor blade is realized in a severe high-temperature and high-pressure environment of an aero-engine, and reconstruction of a blade strain field can be completed based on methods of data processing, picture splicing and the like; and the strain conditions of different regions, especially marginal regions, can be calculated more accurately.

Description

technical field [0001] The invention belongs to the field of strain measurement and data processing of turbine blades of aeroengines, and is used for the measurement of the full-field strain of the turbine blades and the reconstruction of the strain field. Background technique [0002] The strain state of the turbine rotor blade during the working process of the aero-engine is one of the key parameters for studying the mechanical properties of the engine turbine blade, evaluating the working state of the blade, and improving the blade structure. The measurement of blade strain and the reconstruction of the strain field are the key points and difficulties in the field of aeroengine turbine blade testing. At present, the method of using high-temperature strain gauges belongs to the contact point-to-point measurement method, which has difficulties in installation and wiring, and it is difficult to reconstruct the strain field and the application temperature. The problem of low ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06T7/00G06T7/13G06T7/181G06T3/40
CPCG06T7/0004G06T7/13G06T7/181G06T3/4007G06T2207/10048G06T2207/20221G06T7/33G06T2207/30164G01B11/16G01B2210/52G06T7/73G01J5/0088G06T7/0002G06T2207/20021
Inventor 喻培丰张泽展姜晶牛夷王超
Owner UNIV OF ELECTRONICS SCI & TECH OF CHINA
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