CN115265799A - Finite element-based turbine blade reflection radiation error correction method - Google Patents

Finite element-based turbine blade reflection radiation error correction method Download PDF

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CN115265799A
CN115265799A CN202211038382.8A CN202211038382A CN115265799A CN 115265799 A CN115265799 A CN 115265799A CN 202211038382 A CN202211038382 A CN 202211038382A CN 115265799 A CN115265799 A CN 115265799A
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丁铭
吉洁
王波涛
颜冰
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Beihang University
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
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    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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Abstract

A turbine blade reflection radiation error correction method based on finite elements includes the steps of building a ComsolMultiphysics environment to construct a turbine blade geometric model corresponding to actual testing by obtaining prior parameters, configuring interfaces required by simulation software, inputting corresponding parameters to obtain m x n groups of simulation results under n temperature points with temperature step v in a temperature measurement equipment working temperature interval at m positions with angle step u in a blade rotation position interval of a measured moving blade, obtaining reflection radiation quantities of different positions and temperature intervals, obtaining correction radiation quantities of different positions and temperature intervals, correcting errors by utilizing radiation quantity data and correction radiation quantities actually measured by a high-temperature detector, and obtaining measured turbine blade surface temperature with reflection radiation errors eliminated by utilizing Planck radiation formula to solve temperature reversely for corrected radiation quantities. The method can correct the radiation temperature measurement error of the turbine blade influenced by the reflected radiation in a high-temperature environment.

Description

Finite element-based turbine blade reflection radiation error correction method
Technical Field
The invention belongs to the technical field of radiation temperature measurement of turbine blades, and particularly relates to a finite element-based method for correcting reflection radiation errors of turbine blades.
Background
The turbine blade is one of the core components of the aircraft engine, works in the severe environment of high temperature, high pressure, high rotating speed and strong shock, once the surface temperature exceeds the bearing limit of the blade material, the safety operation of the aircraft is greatly threatened, and the real-time monitoring and failure prevention of the health state of the aircraft can be realized by accurately obtaining the surface temperature distribution of the blade. Radiation temperature measurement is used as a novel temperature measurement technology, has high measurement precision, wide temperature measurement range and strong reliability, and provides the best choice for obtaining the temperature distribution on the surface of the turbine blade.
The radiation temperature measurement is to obtain the radiation quantity of the surface of the blade at a specific temperature and then calculate the target temperature according to the Planck blackbody radiation law. However, in the complex environment of the turbine blade, the radiation quantity acquired by the probe is not only self, but also includes the radiation projected to the measured blade by the background, the front and rear stages of guide vanes and the same stage of adjacent blades. The U.S. Puff company Atkinson and Strange reported that the reflected energy in the first stage high pressure turbine blades may exceed 75% in some cases. Obviously, the radiation energy is incident to the target surface and reflected, and is received by the high-temperature detector together with the target radiation amount, which brings great influence to the measurement result and seriously affects the precision of radiation temperature measurement, so that the correction of the reflected radiation error is necessary.
Disclosure of Invention
The invention provides a turbine blade reflection radiation error correction method based on finite elements aiming at the defects or shortcomings in the prior art, which comprises the steps of obtaining prior parameters, building a Commol Multiphysics environment to construct a turbine blade geometric model corresponding to actual testing, configuring an interface required by simulation software, inputting corresponding parameters, obtaining m multiplied by n groups of simulation results under n temperature points with the temperature step being v in a temperature measuring equipment working temperature interval at m positions with the temperature step being u in a blade rotation position interval of a measured moving blade, obtaining reflection radiation quantities of different positions and temperature intervals, obtaining correction radiation quantities of different positions and temperature intervals, correcting errors by utilizing radiation quantity data and the correction radiation quantities actually measured by a high-temperature detector, and obtaining the measured turbine blade surface temperature with the reflection radiation errors eliminated by utilizing the Planck black body radiation formula to solve the temperature for the corrected radiation quantities.
The technical solution of the invention is as follows:
a finite element-based turbine blade reflected radiation error correction method is characterized by comprising the following steps:
step 1, acquiring prior parameters according to actual working conditions of turbine blades to set simulation parameters;
step 2, building a Commol Multiphysics environment, and constructing a turbine blade geometric model corresponding to the actual test;
step 3, configuring interfaces required by simulation software, inputting corresponding parameters, and obtaining m multiplied by n groups of simulation results at n temperature points with the temperature step length v in the working temperature interval of the temperature measuring equipment at m positions with the angle step length u in the blade rotating position interval of the measured moving blade, wherein m and n are positive integers;
step 4, calculating the reflected radiation B of n temperature points at each of m positions sij I =1,2,. Ang, n; j =1,2,. ·, m; i is the serial number of the temperature point, and j is the serial number of the position;
step 5, obtaining the corrected radiation amount of n temperature intervals under m positions
Figure BDA0003819700340000021
Step 6, correcting errors by utilizing the actual measured radiation quantity data and corrected radiation quantity of the high-temperature detector;
and 7, reversely solving the temperature of the corrected radiation quantity by using a Planck black body radiation formula to obtain the surface temperature T of the measured turbine blade with the reflection radiation error eliminated.
The turbine blade in step 1 includes movable vane, preceding stage stator, and back stage stator, including following parameter in step 1: blade temperature, ambient temperature, blade emissivity, selected wavelength, and wavelength bandwidth.
The turbine blade geometric model in step 2 comprises three centered movable blades, six preceding stage guide vanes in front and six following stage guide vanes in back.
In the step 3, because the turbine blades rotate periodically, the influence of the position change in one gap of the preceding stage guide vane on the measured radiation is focused; the blade rotation position interval specifically refers to a position from which the detected movable blade is just aligned with one preceding stage guide blade to a position from which the detected movable blade rotates to the next preceding stage guide blade adjacent to the preceding stage guide blade and is aligned with the preceding stage guide blade; the working temperature range of the temperature measuring equipment particularly refers to the range of the radiation temperature measuring equipment, and the upper limit of the range is larger than the highest temperature of the surface of the measured blade.
The step 4 comprises the following steps: delta B ji ＝B sij -B tij Wherein Δ B ji Is a difference of simulation theory, B tij Is a theoretical value derived from the planck black body radiation formula.
The step 5 comprises the following steps: taking Δ B from the qth temperature point of the n temperature points at each position j(q-p) To Δ B jq Average value of (1), the result is recorded as
Figure BDA0003819700340000022
Wherein q is an integer no less than 2, p =1, 2. p is a radical of formula<q。
The step 6 comprises the following steps: measuring the radiation B measured by a high-temperature detector m The radiation B simulated at the corresponding position si And sequentially making differences, and recording the simulation temperature corresponding to the minimum value of the result as T a Corrected radiation quantity B c ＝B m -B si 。
The step 7 comprises the following steps:
Figure BDA0003819700340000023
wherein C 1 ＝3.7418×10 -16 W*m 2 ，C 2 ＝1.4388×10 - 2 And m × K, λ is the selected wavelength, Δ λ is the wavelength bandwidth, and ε is the measured blade emissivity.
The invention has the following technical effects: 1. the finite element-based turbine blade reflection radiation error correction method can correct turbine blade radiation temperature measurement errors in practical application, and therefore radiation temperature measurement accuracy is improved. 2. The turbine blade reflection radiation error correction method based on the finite element is accurate and efficient in analysis process and free of complex equipment and structures by means of the finite element method. 3. According to the turbine blade reflection radiation error correction method based on the finite element, the adopted geometric model is close to the actual working condition, the result has higher reliability, and the correction result is more reliable.
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FIG. 1 is a flow chart illustrating a finite element-based turbine blade reflected radiation error correction method according to the present invention. Fig. 1 includes a step L1 of obtaining a prior parameter; l2, building a simulation environment to construct a geometric model; l3, configuring simulation software to solve to obtain a simulation result of a specific position and temperature; step L4, calculating the reflected radiation quantity; step L5, solving the corrected radiation amount; l6, correcting errors; and L7, reversely solving the surface temperature.
FIG. 2 is a turbine blade geometry model incorporating a bucket and a front and rear two stage vane in accordance with the present invention.
The reference numbers are listed below: 1-moving blades; 11-a measured movable blade; 12-first movable vane; 2-preceding stage guide vanes; 21-No. four preceding stage guide vanes; 22-No. three preceding stage guide vanes; 3-rear stage guide vanes.
Detailed Description
The invention is explained below with reference to the figures (fig. 1-2) and examples.
FIG. 1 is a flow chart illustrating a finite element-based turbine blade reflected radiation error correction method according to the present invention. FIG. 2 is a geometric model of a turbine blade comprising a bucket and two stages of vanes. Referring to fig. 1 to 2, a finite element-based turbine blade reflected radiation error correction method is characterized by comprising the following steps: step 1, acquiring prior parameters according to the actual working conditions of the turbine blade to set simulation parameters; step 2, building a Commol Multiphysics environment, and constructing a turbine blade geometric model corresponding to the actual test; step 3, configuringInputting corresponding parameters by an interface required by simulation software to obtain m multiplied by n groups of simulation results at n temperature points with the temperature step length v in a working temperature interval of temperature measurement equipment at m positions with the angle step length u in a blade rotating position interval of the measured moving blade, wherein m and n are positive integers; step 4, calculating the reflected radiation B of n temperature points at each of m positions sij I =1,2,. N; j =1,2,. ·, m; i is the serial number of the temperature point, and j is the serial number of the position; step 5, obtaining the corrected radiation amount of n temperature intervals under m positions
Figure BDA0003819700340000031
Step 6, correcting errors by utilizing the actual measured radiation quantity data and corrected radiation quantity of the high-temperature detector; and 7, reversely solving the temperature of the corrected radiation amount by using a Planck black body radiation formula to obtain the surface temperature T of the measured turbine blade without the reflection radiation error.
The turbine blade in step 1 includes movable vane 1, preceding stage stator 2, and back stage stator 3, including following parameter in step 1: blade temperature, ambient temperature, blade emissivity, selected wavelength, and wavelength bandwidth. The geometric model of the turbine blade in step 2 includes three centered movable blades (including the centered measured movable blade 11, the upper movable blade 12, and the lower movable blade), six preceding guide blades (including the third preceding guide blade 22 and the adjacent fourth preceding guide blade 21 below the third preceding guide blade), and six following guide blades. In the step 3, because the turbine blades rotate periodically, the influence of the position change in one gap of the preceding stage guide vane on the measured radiation is focused; the blade rotation position interval specifically refers to a position from which the detected movable blade is just aligned with one preceding stage guide blade to a position from which the detected movable blade rotates to the next preceding stage guide blade adjacent to the preceding stage guide blade and is aligned with the preceding stage guide blade; the working temperature range of the temperature measuring equipment particularly refers to the range of the radiation temperature measuring equipment, and the upper limit of the range is larger than the highest temperature of the surface of the measured blade.
The step 4 comprises the following steps: delta B ji ＝B sij -B tij Wherein Δ B ji Is a difference of simulation theory, B tij Is composed of Planck black-body spokeAnd (4) deducing the obtained theoretical value by using an equation. The step 5 comprises the following steps: taking Δ B from the qth temperature point of the n temperature points at each position j(q-p) To Δ B jq Average value of (2), the result is recorded
Figure BDA0003819700340000041
Wherein q is an integer of 2 or more, p =1, 2.., n-1; p is a radical of formula<q is calculated. The step 6 comprises the following steps: measuring the radiation B measured by the high temperature detector m The radiation B simulated at the corresponding position si And sequentially making differences, and recording the simulation temperature corresponding to the minimum value of the result as T a Corrected radiation quantity B c ＝B m -B si 。
The step 7 comprises the following steps:
Figure BDA0003819700340000042
wherein C is 1 ＝3.7418×10 -16 W*m 2 ，C 2 ＝1.4388×10 -2 And m × K, λ is the selected wavelength, Δ λ is the wavelength bandwidth, and ε is the measured blade emissivity.
The invention provides a finite element-based turbine blade reflection radiation error correction method, which is based on Comsol Multiphysics multi-physical field simulation software and is particularly suitable for radiation temperature measurement error correction of reflection influence of adjacent hot end components of a turbine blade in a high-temperature environment. The guide vane in the aero-engine is relatively static, so that the surface temperature of the vane is easy to obtain, the background temperature is also easy to measure, and the surface temperature of the moving vane rotating at a high speed is relatively complicated to accurately obtain. The invention aims to eliminate the influence of reflected radiation generated by front and rear guide vanes, same-stage movable vanes and background temperature, so that the temperatures of the front and rear guide vanes and the background are known.
The invention provides a finite element-based turbine blade reflection radiation error correction method, which is particularly suitable for correcting radiation temperature measurement errors caused by turbine blade reflection radiation in a high-temperature environment.
A finite element-based turbine blade reflected radiation error correction method is shown in a flow chart of fig. 1 and comprises the following steps:
l1, acquiring prior parameters according to actual working conditions to set simulation parameters;
l2, building a simulation environment and a turbine blade radiation temperature measurement error geometric model;
l3, configuring simulation software according to simulation conditions and solving the simulation software to obtain m multiplied by n groups of simulation results of the measured moving blade with the step length of u (°) in the rotating position interval (m positions) of the blade under the condition that the step length of v (K) in the working temperature interval (n temperatures) of the temperature measuring equipment;
l4, calculating the reflected radiation B of n temperature intervals at m positions sij (i＝1,2,...,n；j＝1,2,...,m)；
L5, obtaining the corrected radiation quantity of n temperature intervals at m positions
Figure BDA0003819700340000051
L6, correcting errors of the result measured by combining the high-temperature radiation detector;
and L7, reversely solving the surface temperature T according to the corrected radiation quantity.
The following describes the radiation temperature measurement error correction of a turbine blade including a first-stage moving blade and a front-and-rear-stage guide blade as an example.
In the embodiment of the present invention, the parameters in step L1 include, but are not limited to, the temperature of the front and rear stage guide vanes of the measured blade, the ambient temperature, the emissivity of the blade, the selected wavelength, and the wavelength bandwidth; as a possible implementation mode, the temperature of the front stage guide vane is 1300K, the temperature of the rear stage guide vane is 1000K, the background temperature is 1000K, the emissivity of the blade is 0.7, and the wavelength is selected to be 1550nm +/-15 nm.
In the embodiment of the present invention, the geometric model in step L2 includes three moving blades 1, six front stage guide blades 2, and six rear stage guide blades 3.
In the embodiment of the present invention, in step L3, due to the periodic rotation of the turbine blades, the influence of the position change of the preceding stage guide vanes 2 within one gap (the third preceding stage guide vane 22 to the fourth preceding stage guide vane 21) (as a possible implementation, the gap is about 7 °) on the measured radiation is focused; the blade rotation position interval specifically refers to a position from which the detected movable blade 11 is just aligned with the front stage guide blade 21 of the fourth number to a position from which the detected movable blade 11 rotates to the next front stage guide blade 22 of the third number adjacent to the front stage guide blade 21 and is aligned with the front stage guide blade, and at this time, the detected movable blade 11 is located at the position of the movable blade 12 of the first number; the m positions are uniformly distributed between a third preceding stage guide vane 22 and a fourth preceding stage guide vane 21; the measurable temperature interval specifically refers to the range of radiation temperature measurement equipment, and generally speaking, the upper limit of the range is larger than the highest temperature of the surface of the measured blade; the n temperatures are uniformly distributed in the measurable temperature interval; the simulation result comprises the radiant quantity of the surface of the blade to be measured and the temperature inversely solved by the radiant quantity. As a possible implementation mode, the rotating position interval of the blade is 0-7 degrees, and the measurable temperature interval is 300-1300K.
In the embodiment of the present invention, the method for calculating the reflected radiation in step L4 specifically includes: corresponding the radiation values B obtained by simulation of m positions sij (i =1,2.. N; j =1,2.. N., m) is respectively associated with a theoretical value B derived from the Planck black body radiation formula tij (i =1,2, n, j =1,2, n, m) and the result is noted as Δ B ji (i =1,2,. Cndot., n; j =1,2,. Cndot., m). As a possible implementation, m is 7 and n is 11.
In the embodiment of the present invention, the method for calculating the corrected radiation amount in step L5 specifically includes: taking Delta B from the qth (q ≧ 2) temperature point of the n temperature points at each position j(q-p) (p＝1,2,...,n-1；p<q; j =1, 2.. Multidot.m) to Δ B jq (j =1, 2...., m) and the results are reported as
Figure BDA0003819700340000052
As a possible embodiment, q is 4 and p is 4.
In the embodiment of the present invention, the error correction method in step L6 specifically includes: measuring the radiation B measured by the high temperature detector m The radiation B simulated at the corresponding position si (i =1,2, \8230;, n) were sequentially differenced, and the simulation temperature corresponding to the minimum value of the results was denoted as T a Corrected radiation quantity B c ＝B m -B si (i＝a)。
In the embodiment of the present invention, the inverse solution formula of the surface temperature in step L7 is:
Figure BDA0003819700340000061
wherein C 1 ＝3.7418×10 -16 W*m 2 ，C 2 ＝1.4388×10 -2 And m is K, lambda is the selected wavelength, delta lambda is the wavelength bandwidth, and epsilon is the measured blade emissivity.
A turbine blade reflection radiation error correction method based on finite elements is based on Commol Multiphysics simulation software and belongs to the technical field of turbine blade radiation temperature measurement. The method specifically comprises the following steps: acquiring prior parameters according to actual working conditions to set simulation parameters; constructing a Commol Multiphysics environment, and constructing a turbine blade geometric model corresponding to the actual test; configuring interfaces required by simulation software, and inputting corresponding parameters to obtain m multiplied by n groups of simulation results of a measured moving blade with the step length u in the rotating position interval (m positions) of the blade and the step length v in the working temperature interval (n temperatures) of temperature measuring equipment; calculating the reflected radiation quantity of different positions and temperature intervals; obtaining the correction radiation quantity of different positions and temperature intervals; correcting errors by utilizing the actual measured radiation quantity data and corrected radiation quantity of the high-temperature detector; and reversely solving the temperature by utilizing a Planck black body radiation formula on the corrected radiation quantity to obtain the surface temperature. The method can correct the radiation temperature measurement error of the turbine blade influenced by the reflected radiation in the high-temperature environment.
A turbine blade reflection radiation error correction method based on finite elements comprises the following steps:
step 1, acquiring prior parameters according to actual working conditions to set simulation parameters;
step 2, building a Commol Multiphysics environment, and building a turbine blade geometric model corresponding to the actual test;
step 3, configuring interfaces required by simulation software, inputting simulation parameters, and obtaining m multiplied by n groups of simulation results of the measured moving blade with the step length of u (°) in the rotating position interval (m positions) of the blade under the condition that the step length of v (K) in the working temperature interval (n temperatures) of the temperature measuring equipment;
step 4, calculating the reflected radiation B of n temperature intervals at m positions sij (i＝1,2,...,n；j＝1,2,...,m)；
Step 5, obtaining the corrected radiation amount of n temperature intervals under m positions
Figure BDA0003819700340000062
Step 6, correcting errors by utilizing the actual measured radiation quantity data and corrected radiation quantity of the high-temperature detector;
and 7, reversely solving the temperature by using a Planck black body radiation formula to obtain the surface temperature T for the corrected radiation quantity.
The parameters in the step 1 include, but are not limited to, the temperature of the front and rear stage guide vanes of the measured bucket, the ambient temperature, the emissivity of the bucket, the selected wavelength and the wavelength bandwidth.
The geometric model in the step 2 at least comprises three movable blades and six preceding stage guide vanes.
In the step 3, because the turbine blades rotate periodically, the influence of the position change in one gap of the preceding stage guide vane on the measured radiation is focused; the blade rotation position interval specifically refers to a position from which the detected movable blade is just aligned with one preceding stage guide blade to a position from which the detected movable blade rotates to and is aligned with the next preceding stage guide blade adjacent to the preceding stage guide blade; the working temperature range of the temperature measuring equipment specifically refers to the range of the radiation temperature measuring equipment, and generally speaking, the upper limit of the range is larger than the highest temperature of the surface of the measured blade; the m positions are uniformly distributed in the rotating position interval of the blade; the n temperatures are uniformly distributed in the working temperature interval of the temperature measuring equipment; the simulation result comprises the radiant quantity of the surface of the blade to be measured and the temperature inversely solved by the radiant quantity.
The method for obtaining the reflected radiation in the step 4 specifically includes: corresponding the radiation values B obtained by simulation of m positions sij (i =1,2.. N; j =1,2.. N., m) is respectively associated with a theoretical value B derived from the Planck black body radiation formula tij (i =1, 2.. Multidot.n; j =1, 2.. Multidot.m) and the result is noted as Δ B ji (i＝1,2,...,n；j＝1,2,...,m)。
The method for obtaining the corrected radiation amount in the step 5 specifically comprises the following steps: taking Delta B from the qth (q ≧ 2) temperature point of n temperature points at each position j(q-p) (p＝1,2,...,n-1；p<q; j =1,2, 1, m) to Δ B jq (j =1, 2...., m) and the results are reported as
Figure BDA0003819700340000071
The error correction method in the step 6 specifically includes: measuring the radiation B measured by a high-temperature detector m The radiation B simulated at the corresponding position si (i =1,2, \8230;, n) were successively differenced, and the simulated temperature corresponding to the minimum value of the results was denoted as T a Corrected radiation quantity B c ＝B m -B si (i＝a)。
The inverse solution formula of the surface temperature in the step 7 is as follows:
Figure BDA0003819700340000072
wherein C is 1 ＝3.7418×10 -16 W*m 2 ，C 2 ＝1.4388×10 -2 And m is K, lambda is the selected wavelength, delta lambda is the wavelength bandwidth, and epsilon is the measured blade emissivity.
Those skilled in the art will appreciate that the invention may be practiced without these specific details. It is pointed out here that the above description is helpful for the person skilled in the art to understand the invention, but does not limit the scope of protection of the invention. Any and all equivalents, modifications, and/or omissions to the system described above may be made without departing from the spirit and scope of the invention.

Claims (8)

1. A turbine blade reflection radiation error correction method based on finite elements is characterized by comprising the following steps:
step 1, acquiring prior parameters according to actual working conditions of turbine blades to set simulation parameters;
step 2, building a Commol Multiphysics environment, and constructing a turbine blade geometric model corresponding to the actual test;
step 3, configuring interfaces required by simulation software, inputting corresponding parameters, and obtaining m multiplied by n groups of simulation results at n temperature points with the temperature step length v in the working temperature interval of the temperature measuring equipment at m positions with the angle step length u in the blade rotating position interval of the measured moving blade, wherein m and n are positive integers;
step 4, calculating the reflected radiation B of n temperature points at each of m positions sij I =1,2,. N; j =1,2,. Said, m; i is the serial number of the temperature point, and j is the serial number of the position;
step 5, obtaining the corrected radiation amount of n temperature intervals under m positions
Figure FDA0003819700330000011
Step 6, correcting errors by utilizing the actual measured radiation quantity data and corrected radiation quantity of the high-temperature detector;
and 7, reversely solving the temperature of the corrected radiation quantity by using a Planck black body radiation formula to obtain the surface temperature T of the measured turbine blade with the reflection radiation error eliminated.
2. The finite element-based turbine blade reflected radiation error correction method of claim 1, wherein the turbine blade in step 1 comprises a moving blade, a preceding stage guide blade, and a succeeding stage guide blade, and the following parameters are included in step 1: blade temperature, ambient temperature, blade emissivity, selected wavelength, and wavelength bandwidth.
3. The finite element-based turbine blade reflected radiation error rectification method of claim 1, wherein the turbine blade geometric model in step 2 comprises three centered buckets, six preceding stage vanes, and six succeeding stage vanes.
4. The finite element-based turbine blade reflected radiation error correction method of claim 1, wherein in step 3, due to the periodic rotation of the turbine blade, the influence of the position change in one gap of the preceding stage guide vane on the measured radiation is focused; the blade rotation position interval specifically refers to a position from which the detected movable blade is just aligned with one preceding stage guide blade to a position from which the detected movable blade rotates to and is aligned with the next preceding stage guide blade adjacent to the preceding stage guide blade; the working temperature range of the temperature measuring equipment particularly refers to the range of the radiation temperature measuring equipment, and the upper limit of the range is larger than the highest temperature of the surface of the measured blade.
5. The finite element-based turbine blade reflected radiation error correction method of claim 1, wherein the step 4 comprises: delta B ji ＝B sij -B tij Wherein Δ B ji Is a difference of simulation theory, B tij Is a theoretical value derived from the planck black body radiation formula.
6. The finite element-based turbine blade reflected radiation error correction method of claim 1, wherein the step 5 comprises: taking Delta B from the qth temperature point of the n temperature points at each position j(q-p) To Δ B jq Average value of (1), the result is recorded as
Figure FDA0003819700330000021
Wherein q is an integer no less than 2, p =1, 2. p is a radical of<q。
7. The finite element-based turbine blade reflected radiation error correction method of claim 1, wherein the step 6 comprises: measuring the radiation B measured by a high-temperature detector m The radiation B simulated at the corresponding position si And sequentially making differences, and recording the simulation temperature corresponding to the minimum value of the result as T a Corrected radiation quantity B c ＝B m -B si 。
8. A finite element-based turbine blade reflected radiation error correction method as claimed in claim 1, wherein the step 7 comprises:
Figure FDA0003819700330000022
wherein C is 1 ＝3.7418×10 -16 W*m 2 ，C 2 ＝1.4388×10 -2 And m × K, λ is the selected wavelength, Δ λ is the wavelength bandwidth, and ε is the measured blade emissivity.
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