Aero-engine hot end component non-contact temperature field distance error calibration method

A technology for aero-engine and hot-end components, which is applied in the field of non-contact dynamic temperature field distance error calibration of hot-end components, can solve the problems of high technical indicators, difficult development and application of calibration methods, and harsh working environment of aero-engine temperature measuring instruments.

Active Publication Date: 2021-09-03
UNIV OF ELECTRONICS SCI & TECH OF CHINA
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Problems solved by technology

The development and application of calibration methods are very difficult due to the harsh working environment, various influencing factors, and high technical indicators of aircraft engine temperature measuring instruments.

Method used

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  • Aero-engine hot end component non-contact temperature field distance error calibration method
  • Aero-engine hot end component non-contact temperature field distance error calibration method
  • Aero-engine hot end component non-contact temperature field distance error calibration method

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Embodiment Construction

[0029] In order to illustrate the technical solutions of the implementation examples of the present invention more clearly, the examples are further described in detail below in conjunction with the accompanying drawings. The content described here is only for explaining the present invention, and is not intended to limit the present invention.

[0030] The technical route of the distance error calibration method is as follows: figure 1 As shown, the voltage data obtained by the experiment is converted into the corresponding temperature and then compared with the standard temperature of the black body furnace, and then the distance compensation is completed through the BP neural network algorithm to obtain the calibration value. Perform a secondary comparison of the calibration value with the reference value and analyze whether the error is within an acceptable range. If the error is large and not within the acceptable range, then continue to optimize until the requirement is ...

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Abstract

The invention discloses an aero-engine hot end component non-contact temperature field distance error calibration method, and belongs to the technical field of aero-engine temperature measurement. Due to the facts that the actual testing environment and the calibration environment of the aero-engine cannot be completely consistent and the distance cannot be kept unchanged, a calibrated original curve is affected, and when the experimental testing environment is changed, the whole system needs to be compensated and corrected. A mathematical model of a system compensation function is explored, and a radiation quantity attenuation function is defined as a linear form based on a two-point calibration method and in combination with a BP neural network algorithm. The standard temperature of the blackbody furnace is taken as a reference, two points of an experiment are selected for compensation and correction, and the temperature measurement precision is improved.

Description

technical field [0001] The invention belongs to the technical field of aero-engine temperature measurement, and discloses a non-contact dynamic temperature field distance error calibration method for hot end components. Background technique [0002] During the development of high-performance, high-thrust-to-weight ratio engine technology, the precise measurement of the temperature of the hot-end parts of the engine plays an increasingly prominent role in the guarantee and maintenance tasks of mechanical equipment such as turbines. As the combustion temperature increases, the internal environment of the engine becomes harsher, and various parameters change more drastically. In order to improve the working reliability of the blade and prolong its life, it is necessary to accurately measure, study and analyze the temperature distribution of the turbine blade, analyze its surface temperature field, and understand its thermal stress distribution, so as to improve the blade materi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01J5/52G06N3/08
CPCG01J5/52G06N3/084
Inventor 王超陈梦朝张泽展喻培丰牛夷姜晶
Owner UNIV OF ELECTRONICS SCI & TECH OF CHINA
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