Turbine blade radiation temperature measurement error correction method based on reflected radiation model

Abstract

The invention provides a turbine blade radiation temperature measurement error correction method based on a reflected radiation model, and the method comprises the steps: building a reflected radiation model through considering the reflected radiation of a preceding-stage guide blade, an adjacent moving blade and a combustion chamber wall surface at the same time; calculating a radiation angle coefficient between turbine blades and a radiation angle coefficient between wall surfaces of a combustion chamber by using a surrounding channel integral method; temperature distribution of the surface of the turbine blade and the wall surface of the combustion chamber at different temperatures is obtained through comsol simulation; and designing a multiple reflection radiation formula, accurately calculating the reflection radiation of the hot end part, and obtaining a corrected radiation temperature measurement result through inversion. According to the method, reflection radiation of a front-stage guide vane, adjacent movable vanes and a combustion chamber wall surface is considered, a surrounding channel integral method is adopted, surface element shielding between blade surfaces is considered, and a turbine blade surface radiation angle coefficient is calculated; the wall surface of the combustion chamber is increased, the reflection radiation of the hot end component is considered, a multiple reflection radiation formula is designed, the accurate reflection radiation of the hot end component is obtained, the reflection radiation calculation error is reduced, and the turbine blade radiation temperature measurement precision is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine blade radiation temperature measurement, in particular, to the technical field of reflection radiation model; specifically, to a turbine blade radiation temperature measurement error correction method based on the reflection radiation model. Background Art

[0002] As a key component of aircraft engines, turbine blades are subjected to extreme high temperatures and pressures. When the temperature before the turbine exceeds the tolerance limit of the blades, the turbine blades will face the threat of oxidation, corrosion and fission, which will seriously shorten their service life and pose a direct threat to the safe operation of aircraft engines.

[0003] Temperature is an important parameter that reflects the working state of turbine blades. Therefore, the measurement of turbine blade inlet temperature is crucial and is related to the safety and reliability of engine use. Radiation temperature measurement is a widely used non-contact temperature measurement method and is often used to measure the temperature of turbine blades.

[0004] However, due to the harsh temperature measurement environment and complex temperature measurement conditions, the reflected radiation of the hot end components of the engine will affect the radiation temperature measurement results of the turbine blades. When performing radiation temperature measurement, the radiation received by the radiation pyrometer includes not only the radiation from the target surface, but also the radiation reflected from the hot end components to the target surface, which makes the radiation temperature measurement results higher.

[0005] The reflected radiation model is established based on the angular coefficient of radiation heat transfer between two surfaces during the radiation heat transfer process. Combined with the surface temperature of the turbine blade, the amount of reflected radiation received by the target surface is calculated based on Planck's law. The reflected radiation is then removed from the total radiation received by the radiation pyrometer, and the corrected radiation temperature measurement result is finally inverted.

[0006] At present, although some progress has been made in the research on the reflected radiation model of turbine blades, the reflected radiation of the combustion chamber wall has not been considered. The reflected radiation of the hot end components obtained is still not accurate enough, the reflected radiation error is still large, and the accuracy of the radiation temperature measurement of the turbine blades is low. Summary of the invention

[0007] In view of this, the purpose of the present invention is to develop a method for correcting the error of radiation temperature measurement of turbine blades based on a reflected radiation model, while considering the reflected radiation of the preceding guide vanes, adjacent moving blades and the combustion chamber wall, adopting the contour integration method, fully considering the facet shielding between the blade surfaces, and calculating the radiation angular coefficient of the turbine blade surface; on the basis of the existing reflected radiation model of turbine blades, the combustion chamber wall is added, the reflected radiation of the hot end components is considered, and a multiple reflection radiation formula is designed, combined with Planck's law, to obtain accurate reflected radiation of the hot end components, the reflected radiation of the hot end components is eliminated from the total radiation obtained in the radiation temperature measurement, a more accurate reflected radiation is calculated, and the final corrected radiation temperature measurement value is obtained by inversion, thereby reducing the reflected radiation calculation error and improving the accuracy of the radiation temperature measurement of turbine blades.

[0008] The present invention provides a method for correcting turbine blade radiation temperature measurement errors based on a reflected radiation model, comprising the following steps:

[0009] S1. Considering the reflected radiation of the front-stage guide vanes, adjacent moving blades and the combustion chamber wall, a reflected radiation model of the turbine blades is established;

[0010] S2. Based on the reflected radiation model of the turbine blades, the radiation angle coefficient between the turbine blades and the combustion chamber wall is calculated using the contour integration method;

[0011] S3, using Comsol to simulate the geometric model of the turbine blade to obtain the temperature distribution of the turbine blade surface and the combustion chamber wall at different temperatures;

[0012] Comsol is used to simulate the geometric model of turbine blades. By setting the heat source to different temperatures and selecting the physical fields of convection and heat transfer for research and analysis, the temperature distribution of each turbine blade surface and combustion chamber wall under different ambient temperatures is obtained.

[0013] S4. Design multiple reflection radiation formulas to accurately calculate the reflected radiation of the hot end components, and obtain the corrected radiation temperature measurement results through inversion.

[0014] Furthermore, the method for establishing the reflected radiation model of the turbine blade in step S1 includes:

[0015] At the same time, the reflected radiation from the front-stage guide vanes (such as the first-stage guide vanes), adjacent moving blades and the combustion chamber wall is considered. When performing radiation temperature measurement on the turbine blades, the influence of reflected radiation from the hot end components is considered. The target surface measured by the radiation pyrometer The total radiant emittance obtained for:

[0016] (1)

[0017] Considering the radiation angle coefficient between each surface, the target surface The total radiant emittance obtained Rewritten as:

[0018] (2)

[0019] Formula (1) (2) is the surface and the surface to be tested A single reflection between is the blackbody radiation emittance at the same temperature as the target surface, The surface to be tested The emissivity, is the reflectivity, and , The surface to be tested To the surface The radiation angle coefficient, It is the reflected radiation introduced by the hot end components.

[0020] Furthermore, the method for calculating the radiation angle coefficient between turbine blades and combustion chamber wall by using contour integration method in step S2 comprises the following steps:

[0021] S21. Before calculating the radiation angle coefficient, the turbine blade surface and the combustion chamber wall are discretized and analyzed. Based on the meshing function of Comsol, the combustion chamber wall is divided into triangular facets, considering the influence of facet size, surface curvature and calculation time.

[0022] Preferably, the curvature of the surface is 0.16 and the average area of ​​the surface element is 5.53 mm 2 .

[0023] S22. Calculate the radiation angle coefficient between each small facet after dividing the facet using the contour integration method. The calculation formula is:

[0024] (3)

[0025] In formula (3), For facet To Bin The angular coefficient of is the area of ​​the surface element, and Facet and The outline of , , is the coordinate element corresponding to each point on the contour. is the distance between the points on the contours of the two surfaces;

[0026] S23. Using the angle coefficient summation formula, integrate the radiation angle coefficients between the small facets to obtain the total radiation angle coefficient between the moving blade to be measured and the adjacent blade and the combustion chamber wall. The angle coefficient summation formula is:

[0027] (4)

[0028] In formula (4), For face right The angular coefficient of For facet The area of ​​the divided small surface element, is the area of ​​the surface element, For the small facets opposite The angular coefficient of .

[0029] The present invention uses the contour integration method to calculate the radiation angle coefficient, and converts the complex surface integral in the angle coefficient calculation into a line integral using Stokes' theorem. When performing numerical calculation, a lot of calculation time can be saved and an effective angle coefficient calculation result can be obtained.

[0030] Furthermore, in the process of calculating the radiation angle coefficient between the turbine blades and the combustion chamber wall, the step S2 further includes: assuming that all other surfaces except the turbine blade surface may cause shielding to the radiation heat transfer, performing shielding judgment on the other surfaces, and gradually eliminating shielding;

[0031] The method for determining the occlusion of the other surfaces includes: increasing the occlusion coefficient , establish a directed line segment from the centroid of the transmitting face element to the centroid of the receiving face element, and calculate the intersection of the vector of this directed line segment and any surface; if the intersection exists, then this surface is an occluding surface, =0, that is, the radiation angle coefficient between the two surface elements is zero; if the intersection does not exist, then =1, check the next surface; perform occlusion judgment on all face elements to obtain the final radiation angle coefficient between surfaces after removing the occlusion; occlusion coefficient It is expressed as:

[0032] ;

[0033] The calculation formula for the total radiation angle coefficient after adding occlusion judgment is:

[0034] (5).

[0035] Specifically, when heat transfer is performed by radiation on the surface of turbine blades, the radiation path may be affected by the occlusion of other surfaces, resulting in the blocking of radiation heat transfer between certain facets. In order to accurately calculate the radiation angle coefficient between turbine blade surfaces, a judgment mechanism must be introduced to identify whether there is occlusion between two facets. If there is occlusion, the radiation angle coefficient between the two facets should be considered zero.

[0036] Furthermore, the method for designing a multiple reflection radiation formula in step S4 includes:

[0037] With three surfaces , , ,in is the surface of the blade to be tested, , is the surface of the hot end component. When a single reflection is considered, the calculation expression of the single reflection radiation is:

[0038] (6)

[0039] When multiple reflections are considered, the calculation expression of multiple reflection radiation is:

[0040] (4)

[0041] In formula (6) and (7) , Hot end components , The radiant emittance of the surface, , Hot end components , the emissivity of the surface; The surface of the blade to be tested To the surface The radiation angle coefficient, The surface of the blade to be tested To the surface The radiation angle coefficient;

[0042] When there is When a surface is the surface of the blade to be measured. When a single reflection is considered, the calculation expression of the single reflection radiation is:

[0043] (8)

[0044] When multiple reflections are considered, the calculation expression of multiple reflection radiation is:

[0045] (9)

[0046] In formula (8) and (9), , Hot end components , The radiant emittance of a surface, , … Hot end components , The emissivity of the surface.

[0047] When the turbine blades conduct radiation heat transfer in a high temperature environment, the radiation reflected by the surrounding blades and walls to the surface of the blade to be measured is not just a single reflection, but multiple reflections. The radiation emitted by each surface is repeatedly reflected between multiple surfaces and finally reflected by the surface of the blade to be measured. The radiation temperature measurement system receives this part of the radiation. Therefore, the present invention proposes a calculation formula for multiple reflection radiation.

[0048] Furthermore, the method of obtaining the corrected radiation temperature measurement result by inversion in step S4 includes:

[0049] The calculated reflected radiation is removed from the total radiation obtained by the radiation pyrometer, and the corrected radiation temperature measurement result is inverted based on the monochromatic temperature measurement method and Planck's law.

[0050] The present invention also provides a computer-readable storage medium having a computer program stored thereon, and when the program is executed by a processor, the steps of the turbine blade radiation temperature measurement error correction method based on the reflected radiation model as described above are implemented.

[0051] The present invention also provides a computer device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the steps of the turbine blade radiation temperature measurement error correction method based on the reflected radiation model as described above are implemented.

[0052] Compared with the prior art, the present invention has the following beneficial effects:

[0053] The turbine blade radiation temperature measurement error correction method and system based on the reflected radiation model provided by the present invention adopts the contour integration method through appropriate facet division, comprehensively considers the facet occlusion problem, and eliminates the radiation angle coefficient between two facets with facet occlusion through occlusion judgment, so as to obtain a fast and effective radiation angle coefficient calculation result; on the basis of the existing turbine blade reflection radiation model, the combustion chamber wall is added, and the reflected radiation of the hot end components is fully considered. In the process of calculating the reflected radiation, the multiple reflections of the radiation emitted by each surface between the surfaces are considered, and the formula for calculating the multiple reflected radiation is designed, which fully takes into account the influence of multiple reflections on the reflected radiation calculation, and can calculate a more accurate reflected radiation amount, reduce the reflected radiation calculation error, and effectively improve the accuracy of the turbine blade radiation temperature measurement. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the following detailed description of the preferred embodiment.The drawings are only for the purpose of illustrating the preferred embodiments and are not to be construed as limiting the invention.

[0055] In the attached picture:

[0056] Figure 1 It is a schematic diagram of a flow chart of error correction of radiation temperature measurement of turbine blades based on a reflected radiation model according to an embodiment of the present invention;

[0057] Figure 2 It is a simulation result diagram of an embodiment of the present invention;

[0058] Figure 3 It is a flow chart of the turbine blade radiation temperature measurement error correction method based on the reflected radiation model of the present invention;

[0059] Figure 4 A flow chart of a method for calculating the radiation angle coefficient between turbine blades and combustion chamber walls using the contour integration method of the present invention;

[0060] Figure 5 The figure is a schematic diagram of the structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0061] Exemplary embodiments will be described in detail herein, examples of which are shown in the accompanying drawings. When the following description refers to the drawings, the same numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present disclosure. Instead, they are merely examples of devices and products consistent with some aspects of the present disclosure as detailed in the appended claims.

[0062] The terms used in this disclosure are for the purpose of describing specific embodiments only and are not intended to limit the disclosure. The singular forms of "a", "said" and "the" used in this disclosure and the appended claims are also intended to include plural forms unless the context clearly indicates otherwise. It should also be understood that the term "and / or" used herein refers to and includes any or all possible combinations of one or more associated listed items.

[0063] It should be understood that although the terms first, second, third, etc. may be used in the present disclosure to describe various information, such information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of the present disclosure, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Depending on the context, the word "if" as used herein may be interpreted as "at the time of" or "when" or "in response to determining".

[0064] The embodiments of the present invention are described in further detail below.

[0065] The embodiment of the present invention provides a method for correcting the error of turbine blade radiation temperature measurement based on a reflected radiation model. Figure 3 As shown, the following steps are included:

[0066] S1. Considering the reflected radiation of the front-stage guide vanes, adjacent moving blades and the combustion chamber wall, a reflected radiation model of the turbine blades is established;

[0067] Methods for modeling reflected radiation from turbine blades include:

[0068] At the same time, the reflected radiation from the front-stage guide vanes (such as the first-stage guide vanes), adjacent moving blades and the combustion chamber wall is considered. When performing radiation temperature measurement on the turbine blades, the influence of reflected radiation from the hot end components is considered. The target surface measured by the radiation pyrometer The total radiant emittance obtained for:

[0069] (1)

[0070] Considering the radiation angle coefficients between the surfaces, the total radiation emittance obtained by the target surface j is Rewritten as:

[0071] (2)

[0072] Formula (1) (2) is the surface and the surface to be tested A single reflection between is the blackbody radiation emittance at the same temperature as the target surface, The surface to be tested The emissivity, is the reflectivity, and , The surface to be tested To the surface The radiation angle coefficient, It is the reflected radiation introduced by the hot end components.

[0073] S2. Based on the reflected radiation model of the turbine blades, the radiation angle coefficient between the turbine blades and the combustion chamber wall is calculated using the contour integration method;

[0074] For a method of calculating the radiation angle coefficient between turbine blades and combustion chamber walls using contour integration, see Figure 4 As shown, the following steps are included:

[0075] S21. Before calculating the radiation angle coefficient, the turbine blade surface and the combustion chamber wall are discretized and analyzed. Based on the meshing function of Comsol, the combustion chamber wall is divided into triangular facets, considering the influence of facet size, surface curvature and calculation time.

[0076] In this embodiment, the curvature of the surface is selected to be 0.16, and the average area of ​​the surface element is 5.53 mm 2 .

[0077] S22. Calculate the radiation angle coefficient between each small facet after dividing the facet using the contour integration method. The calculation formula is:

[0078] (3)

[0079] In formula (3), For facet To Bin The angular coefficient of is the area of ​​the surface element, and Facet and The outline of , , is the coordinate element corresponding to each point on the contour. is the distance between the points on the contours of the two surfaces;

[0080] S23. Using the angle coefficient summation formula, integrate the radiation angle coefficients between the small facets to obtain the total radiation angle coefficient between the moving blade to be measured and the adjacent blade and the combustion chamber wall. The angle coefficient summation formula is:

[0081] (4)

[0082] In formula (4), For face right The angular coefficient of For facet The area of ​​the divided small surface element, is the area of ​​the surface element, For the small facets opposite The angular coefficient of .

[0083] This embodiment uses the contour integration method to calculate the radiation angle coefficient, and converts the complex surface integral in the angle coefficient calculation into a line integral using Stokes' theorem. When performing numerical calculations, a lot of calculation time can be saved and an effective angle coefficient calculation result can be obtained.

[0084] In the process of calculating the radiation angle coefficient between the turbine blades and the combustion chamber wall, it also includes: assuming that all other surfaces other than the turbine blade surface may cause shielding to the radiation heat transfer, performing shielding judgment on the other surfaces, and gradually eliminating shielding;

[0085] The method for determining the occlusion of the other surfaces includes: increasing the occlusion coefficient , establish a directed line segment from the centroid of the transmitting face element to the centroid of the receiving face element, and calculate the intersection of the vector of this directed line segment and any surface; if the intersection exists, then this surface is an occluding surface, , that is, the radiation angle coefficient between the two surface elements is zero; if the intersection does not exist, then , check the next surface; perform occlusion judgment on all face elements to obtain the final inter-surface radiation angle coefficient after removing the occlusion; the occlusion coefficient K is expressed as:

[0086] ;

[0087] The calculation formula for the total radiation angle coefficient after adding occlusion judgment is:

[0088] (5).

[0089] When heat transfer is carried out by radiation on the surface of turbine blades, the radiation path may be affected by the occlusion of other surfaces, resulting in the blocking of radiation heat transfer between some face elements. In order to accurately calculate the radiation angle coefficient between turbine blade surfaces, a judgment mechanism must be introduced to identify whether there is occlusion between two face elements. If there is occlusion, the radiation angle coefficient between the two face elements should be considered to be zero.

[0090] S3, using Comsol to simulate the geometric model of the turbine blade to obtain the temperature distribution of the turbine blade surface and the combustion chamber wall at different temperatures;

[0091] Comsol is used to simulate the geometric model of turbine blades. By setting the heat source to different temperatures and selecting the physical fields of convection and heat transfer for research and analysis, the temperature distribution of each turbine blade surface and combustion chamber wall under different ambient temperatures is obtained.

[0092] like Figure 2 As shown, the turbine blade model is simulated using Comsol, in which the silicon molybdenum rod is used as the heat source. The temperature in the high-temperature furnace is controlled by setting its temperature, and the temperature distribution on the turbine blade surface and the combustion chamber surface at this temperature is obtained.

[0093] S4. Design multiple reflection radiation formulas to accurately calculate the reflected radiation of the hot end components, and obtain the corrected radiation temperature measurement results through inversion.

[0094] Methods for obtaining corrected radiation temperature measurement results through inversion include:

[0095] The calculated reflected radiation is removed from the total radiation obtained by the radiation pyrometer, and the corrected radiation temperature measurement result is inverted based on the monochromatic temperature measurement method and Planck's law.

[0096] When only a single reflection is considered, the single reflection radiation formula (5) is used to calculate the reflected radiation as follows:

[0097]

[0098] When multiple reflections are considered, the multiple reflection radiation formula (6) is used to calculate the multiple reflection radiation.

[0099] The total radiation is calculated as follows:

[0100]

[0101] In this embodiment, the total radiation at two wavelengths of 1550nm and 1650nm is calculated by COMSOL simulation to be 0.077254 W / m 2 and 0.10875 W / m 2 , the total radiation under this condition is taken as the true total radiation.

[0102] The total radiation at two wavelengths of 1550nm and 1650nm is calculated using the single reflection formula to be 0.05626W / m 2 and 0.080183897 W / m 2 The errors from the true total radiation are -27.18% and -26.27%.

[0103] The total radiation at two wavelengths of 1550nm and 1650nm is calculated using the multiple reflection formula to be 0.077990679 and 0.110689594. The errors from the true total radiation are 0.95% and 1.78%, which effectively reduces the error in the calculation of reflected radiation.

[0104] The turbine blade radiation temperature measurement error correction method and system based on the reflected radiation model of this embodiment uses appropriate facet division and contour integration method to comprehensively consider the facet occlusion problem, and through occlusion judgment, eliminates the radiation angle coefficient between two facets with facet occlusion, so as to obtain a fast and effective radiation angle coefficient calculation result; on the basis of the existing turbine blade reflected radiation model, the combustion chamber wall is added to fully consider the reflected radiation of the hot end components. In the process of calculating the reflected radiation, the multiple reflections of the radiation emitted by each surface between the surfaces are considered, and the formula for calculating the multiple reflected radiation is designed, which fully takes into account the influence of multiple reflections on the reflected radiation calculation, and can calculate a more accurate reflected radiation amount, reduce the reflected radiation calculation error, and effectively improve the accuracy of the turbine blade radiation temperature measurement.

[0105] Figure 1 The basic process of turbine blade radiation temperature measurement error correction based on the reflected radiation model in this embodiment is shown.

[0106] An embodiment of the present invention further provides a computer device, Figure 5 is a schematic diagram of the structure of a computer device provided by an embodiment of the present invention; see the accompanying drawings Figure 5 As shown, the computer device includes: an input system 23, an output system 24, a memory 22 and a processor 21; the memory 22 is used to store one or more programs; when the one or more programs are executed by the one or more processors 21, the one or more processors 21 implement the turbine blade radiation temperature measurement error correction method based on the reflected radiation model as provided in the above embodiment; wherein the input system 23, the output system 24, the memory 22 and the processor 21 can be connected via a bus or other means, Figure 5 The example of connecting through bus is taken in the following.

[0107] The memory 22 is a readable and writable storage medium of a computing device, which can be used to store software programs and computer executable programs, such as the corresponding program instructions of the turbine blade radiation temperature measurement error correction method based on the reflected radiation model described in the embodiment of the present invention; the memory 22 can mainly include a program storage area and a data storage area, wherein the program storage area can store an operating system and at least one application required for a function; the data storage area can store data created according to the use of the device, etc.; in addition, the memory 22 can include a high-speed random access memory, and can also include a non-volatile memory, such as at least one disk storage device, a flash memory device, or other non-volatile solid-state storage device; in some instances, the memory 22 can further include a memory remotely arranged relative to the processor 21, and these remote memories can be connected to the device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0108] The input system 23 may be used to receive input digital or character information, and to generate key signal input related to user settings and function control of the device; the output system 24 may include display devices such as display screens.

[0109] The processor 21 executes various functional applications and data processing of the device by running the software programs, instructions and modules stored in the memory 22, that is, implements the above-mentioned turbine blade radiation temperature measurement error correction method based on the reflected radiation model.

[0110] The computer device provided above can be used to execute the turbine blade radiation temperature measurement error correction method based on the reflected radiation model provided in the above embodiment, and has corresponding functions and beneficial effects.

[0111] The embodiment of the present invention also provides a storage medium containing computer executable instructions, which are used to execute the turbine blade radiation temperature measurement error correction method based on the reflected radiation model as provided in the above embodiment when executed by a computer processor. The storage medium is any of various types of memory devices or storage devices, and the storage medium includes: installation media, such as CD-ROM, floppy disk or tape system; computer system memory or random access memory, such as DRAM, DDR RAM, SRAM, EDO RAM, Rambus RAM, etc.; non-volatile memory, such as flash memory, magnetic media (such as hard disk or optical storage); registers or other similar types of memory elements, etc.; the storage medium may also include other types of memory or a combination thereof; in addition, the storage medium may be located in a first computer system in which the program is executed, or may be located in a different second computer system, which is connected to the first computer system via a network (such as the Internet); the second computer system may provide program instructions to the first computer for execution. The storage medium includes two or more storage media that may reside in different locations (for example, in different computer systems connected via a network). The storage medium may store program instructions (for example, specifically implemented as a computer program) that can be executed by one or more processors.

[0112] Of course, the storage medium containing computer executable instructions provided in an embodiment of the present invention, whose computer executable instructions are not limited to the turbine blade radiation temperature measurement error correction method based on the reflected radiation model as described in the above embodiment, can also execute related operations in the turbine blade radiation temperature measurement error correction method based on the reflected radiation model provided in any embodiment of the present invention.

[0113] So far, the technical solutions of the present invention have been described in conjunction with the preferred embodiments, but it is easy for those skilled in the art to understand that the protection scope of the present invention is obviously not limited to these specific embodiments. Without departing from the principle of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present invention.

[0114] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for correcting turbine blade radiation temperature measurement errors based on a reflected radiation model, characterized in that: The following steps are involved: S1. Considering the reflected radiation of the front-stage guide vanes, adjacent moving blades and the combustion chamber wall, a reflected radiation model of the turbine blades is established; S2. Based on the reflected radiation model of the turbine blades, the radiation angle coefficient between the turbine blades and the combustion chamber wall is calculated using the contour integration method; S3, using Comsol to simulate the geometric model of the turbine blade to obtain the temperature distribution of the turbine blade surface and the combustion chamber wall at different temperatures; S4. Design multiple reflection radiation formulas to accurately calculate the reflected radiation of the hot end components, and obtain the corrected radiation temperature measurement results through inversion.

2. The method for correcting the error of turbine blade radiation temperature measurement based on the reflected radiation model according to claim 1 is characterized in that: The method for establishing the reflected radiation model of the turbine blade in step S1 comprises: At the same time, the reflected radiation from the front-stage guide vanes, adjacent moving blades and combustion chamber walls is considered. When measuring the temperature of the turbine blades, the influence of the reflected radiation from the hot end components is considered. The target surface measured by the radiation pyrometer The total radiant emittance obtained for: （1） Considering the radiation angle coefficient between the surfaces, the target surface The total radiant emittance obtained Rewritten as: （2） Formula (1) (2) is the surface and the surface to be tested A single reflection between is the blackbody radiation emittance at the same temperature as the target surface, The surface to be tested The emissivity, is the reflectivity, and , The surface to be tested To the surface The radiation angle coefficient, It is the reflected radiation introduced by the hot end components.

3. The turbine blade radiation temperature measurement error correction method based on the reflected radiation model according to claim 1 is characterized in that: The method for calculating the radiation angle coefficient between turbine blades and combustion chamber wall by using contour integration method in step S2 comprises the following steps: S21. Before calculating the radiation angle coefficient, the turbine blade surface and the combustion chamber wall are discretized and analyzed. Based on the meshing function of Comsol, the combustion chamber wall is divided into triangular facets, considering the influence of facet size, surface curvature and calculation time. S22. Calculate the radiation angle coefficient between each small facet after dividing the facet using the contour integration method. The calculation formula is: （3） In formula (3), For facet To Bin The angular coefficient of is the area of ​​the surface element, and Facet and The contour of the image, dx, dy, dz are the coordinate micro-elements corresponding to the positions of the points on the contour, is the distance between the points on the contours of the two surfaces; S23. Using the angle coefficient summation formula, integrate the radiation angle coefficients between the small facets to obtain the total radiation angle coefficient between the moving blade to be measured and the adjacent blade and the combustion chamber wall. The angle coefficient summation formula is: （4） In formula (4), is the angular coefficient of surface A to surface B, For facet The area of ​​the divided small surface element, is the area of ​​the surface element, For the small facets opposite The angular coefficient of .

4. The method for correcting turbine blade radiation temperature measurement error based on the reflected radiation model according to claim 3 is characterized in that: In the process of calculating the radiation angle coefficient between the turbine blades and the combustion chamber wall, the step S2 further includes: assuming that all other surfaces other than the turbine blade surface may cause shielding to the radiation heat transfer, performing shielding judgment on the other surfaces, and gradually eliminating shielding; The method for determining occlusion of the other surfaces includes: increasing the occlusion coefficient K, establishing a directed line segment from the centroid of the transmitting face element to the centroid of the receiving face element, and calculating the intersection of the vector of the directed line segment and any surface; if the intersection exists, the surface is an occlusion surface, =0, that is, the radiation angle coefficient between the two surface elements is zero; if the intersection does not exist, then =1, check the next surface; perform occlusion judgment on all face elements to obtain the final inter-surface radiation angle coefficient after removing the occlusion; occlusion coefficient It is expressed as: ； The calculation formula for the total radiation angle coefficient after adding occlusion judgment is: （5）。 5. The method for correcting turbine blade radiation temperature measurement error based on the reflected radiation model according to claim 1, characterized in that: The method for designing the multiple reflection radiation formula in step S4 includes: With three surfaces , , ,in is the surface of the blade to be tested, , is the surface of the hot end component. When a single reflection is considered, the calculation expression of the single reflection radiation is: （6） When multiple reflections are considered, the calculation expression of multiple reflection radiation is: （7） In formula (6) and (7) , Hot end components , The radiant emittance of the surface, , Hot end components , the emissivity of the surface; The surface of the blade to be tested To the surface The radiation angle coefficient, The surface of the blade to be tested To the surface The radiation angle coefficient; When there is When the surface is the surface of the blade to be measured. When a single reflection is considered, the calculation expression of the single reflection radiation is: （8） When multiple reflections are considered, the calculation expression of multiple reflection radiation is: （9） In formula (8) and (9), , … Hot end components , The radiant emittance of a surface, , … Hot end components , The emissivity of a surface.

6. The method for correcting turbine blade radiation temperature measurement error based on the reflected radiation model according to claim 1, characterized in that: The method for obtaining the corrected radiation temperature measurement result by inversion in step S4 includes: The calculated reflected radiation is removed from the total radiation obtained by the radiation pyrometer, and the corrected radiation temperature measurement result is inverted based on the monochromatic temperature measurement method and Planck's law.

7. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, the steps of the turbine blade radiation temperature measurement error correction method based on the reflected radiation model described in any one of claims 1 to 6 are implemented.

8. A computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the program, the steps of the turbine blade radiation temperature measurement error correction method based on the reflected radiation model as described in any one of claims 1 to 6 are implemented.

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