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A turbine blade temperature field image processing method

A technology of image processing and turbine blades, applied in image data processing, temperature distribution map, image enhancement, etc., can solve the problems of temperature field image distortion, measured value error, etc., and achieve low cost, no safety hazard, and scalability strong effect

Active Publication Date: 2019-04-30
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] At present, the infrared temperature measurement system provides an image of the temperature field based on the premise that the rotational speed is known. In actual situations, the engine rotational speed cannot be completely and accurately measured within the test time. After comparison and observation, under the maximum operating state of the engine, when the rotational speed occurs 1 / When the constant offset is 10000, the temperature field image will be significantly distorted
[0003] The common means of measuring speed is multi-stage gears. The disadvantage of this scheme is: when using multi-stage gears to measure the speed of high-pressure turbine, due to the vibration between gears, electromagnetic interference, design defects of tachometer phase-locked loop, etc., the measured value has certain deviations. small error

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  • A turbine blade temperature field image processing method
  • A turbine blade temperature field image processing method
  • A turbine blade temperature field image processing method

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Embodiment Construction

[0035] The application will be further described in detail below with reference to the drawings and embodiments. It is understandable that the specific embodiments described here are only used to explain the related application, but not to limit the application. In addition, it should be noted that, for ease of description, only parts related to the present application are shown in the drawings.

[0036] It should be noted that the embodiments in the application and the features in the embodiments can be combined with each other if there is no conflict. Hereinafter, the present application will be described in detail with reference to the drawings and in conjunction with embodiments.

[0037] figure 1 It is a schematic flow chart of the image processing method for the temperature field of a turbine blade provided by an embodiment of the present application, such as figure 1 As shown, the method includes the following steps:

[0038] Step 1: Display and analysis of temperature fie...

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Abstract

The invention provides a turbine blade temperature field image processing method. The turbine blade temperature field image processing method comprises the first step of displaying and analyzing temperature field data, the second step of segmenting a temperature field image, the third step of detecting the edge of the temperature field image, the fourth step of processing the temperature field image and the fifth step of evaluating a temperature field image processing result.

Description

Technical field [0001] This application relates to the technical field of aeroengines, and specifically provides a method for processing turbine blade temperature fields. Background technique [0002] At present, the infrared temperature measurement system provides temperature field images based on the premise that the speed is known. In actual conditions, the engine speed cannot be measured completely and accurately within the test time. After comparison and observation, under the maximum working state of the engine, when the speed occurs 1 / At a constant offset of 10,000, the temperature field image will be significantly distorted. [0003] The common method for measuring speed is multi-stage gears. The disadvantage of this scheme is that when multi-stage gears are used to measure the speed of high-pressure turbines, the measured value has a certain value due to the vibration between gears, electromagnetic interference, and design defects of the tachometer phase-locked loop Mino...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06T7/12G06T7/13G06T7/181G01J5/00
CPCG06T7/12G06T7/13G06T7/181G01J5/00G06T2207/10048G01J5/485
Inventor 栾世杰徐春雷田吉祥薛秀生何乃库张龙程昊
Owner AECC SHENYANG ENGINE RES INST