A method for correcting the radiation temperature measurement error of turbine blades based on a reflection radiation model

Abstract

The present invention provides a method for correcting the radiation temperature measurement error of turbine blades based on a reflection radiation model, including: simultaneously considering the reflected radiation of the front-stage guide vane, adjacent moving blades, and the combustion chamber wall surface, establishing a reflection radiation model; using the contour integral method to calculate the radiation view factors between turbine blades and between the combustion chamber wall surfaces; obtaining the temperature distributions of the turbine blade surfaces and the combustion chamber wall surfaces at different temperatures by means of Comsol simulation; designing a multiple-reflection radiation formula to accurately calculate the reflected radiation of the hot-end components, and obtaining the corrected radiation temperature measurement result through inversion. The present invention considers the reflected radiation of the front-stage guide vane, adjacent moving blades, and the combustion chamber wall surface, adopts the contour integral method, considers the element occlusion between blade surfaces, and calculates the radiation view factors of the turbine blade surfaces; adds the combustion chamber wall surface, considers the reflected radiation of the hot-end components, designs a multiple-reflection radiation formula, obtains the accurate reflected radiation of the hot-end components, reduces the calculation error of the reflected radiation, and improves the accuracy of the radiation temperature measurement of turbine blades.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine blade radiation temperature measurement, and particularly to the technical field of reflection radiation models; specifically, it relates to a method for correcting the radiation temperature measurement error of turbine blades based on a reflection radiation model. Background Art

[0002] As a key component of an aeroengine, the turbine blade is subjected to extreme high temperature and high pressure. When the temperature in front of the turbine exceeds the tolerance limit of the blade, the turbine blade will face the threats of oxidation, corrosion and fission, seriously shortening its service life and posing a direct threat to the safe operation of the aeroengine.

[0003] Temperature is an important parameter reflecting the working state of the turbine blade. Therefore, the measurement of the inlet temperature of the turbine blade is crucial, which is related to the safety and reliability of the engine operation. The radiation temperature measurement method is a widely used non-contact temperature measurement method at present and is often used to measure the temperature of the turbine blade.

[0004] However, due to factors such as 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 result of the turbine blade. 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, making the radiation temperature measurement result on the high side.

[0005] The establishment of the reflection radiation model is based on the view factor of the radiation heat transfer between two surfaces in the radiation heat transfer process. Combining the surface temperature of the turbine blade, the reflected radiation received by the target surface is calculated based on Planck's law. Then, the reflected radiation in the total radiation received by the radiation pyrometer is removed, and finally, the corrected radiation temperature measurement result is inversely obtained.

[0006] At the present stage, although certain progress has been made in the research on the reflection radiation model of the turbine blade, 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 blade 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 radiation temperature measurement error of turbine blades based on the reflected radiation model. While considering the reflected radiation of the upstream guide vane, adjacent moving blades, and the combustion chamber wall, the contour integral method is adopted to fully consider the surface element occlusion between the blade surfaces, and the radiation shape factor of the turbine blade surface is calculated. On the basis of the existing reflected radiation model of the turbine blade, the combustion chamber wall is added, the reflected radiation of the hot end components is considered, a multiple-reflection radiation formula is designed, combined with Planck's law, to obtain the accurate reflected radiation of the hot end components, remove the reflected radiation of the hot end components from the total radiation obtained from the radiation temperature measurement, calculate the more accurate reflected radiation amount, and inversely obtain the final corrected radiation temperature measurement value, thereby reducing the calculation error of the reflected radiation and improving the accuracy of the turbine blade radiation temperature measurement.

[0008] The present invention provides a method for correcting the radiation temperature measurement error of turbine blades based on the reflected radiation model, including the following steps:

[0009] S1. While considering the reflected radiation of the upstream guide vane, adjacent moving blades, and the combustion chamber wall, establish a reflected radiation model of the turbine blade;

[0010] S2. Based on the reflected radiation model of the turbine blade, use the contour integral method to calculate the radiation shape factor between the turbine blades and between the combustion chamber walls;

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

[0012] Simulate the geometric model of the turbine blade using Comsol. By setting the heat source to different temperatures and selecting the physical fields of convection and heat transfer for research and analysis, the temperature distributions of each turbine blade surface and the combustion chamber wall at different ambient temperatures are obtained.

[0013] S4. Design a multiple-reflection radiation formula to accurately calculate the reflected radiation of the hot end components, and inversely obtain the corrected radiation temperature measurement result.

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

[0015] While considering the reflected radiation brought by the upstream guide vane (such as the first-stage guide vane), adjacent moving blades, and the combustion chamber wall, consider the influence of the reflected radiation of the hot end components when measuring the radiation temperature of the turbine blade. The target surface measured by the radiation pyrometer The total radiant exitance obtained is:

[0016] (1)

[0017] Considering the radiation shape factor between the surfaces, the target surface Total radiant emittance obtained Rewritten as:

[0018] (2)

[0019] Equations (1) and (2) are for single reflections between the surface and the target surface where is the blackbody radiant emittance at the same temperature as the target surface, is the emissivity of the target surface , is the reflectivity, and , is the target surface to the surface radiation view factor, is the reflected radiation introduced by the hot-end component.

[0020] Furthermore, the method for calculating the radiation view factor between turbine blades and the combustion chamber wall surface using the contour integration method in the S2 step includes the following steps:

[0021] S21. Before calculating the radiation view factor, discretize the turbine blade surface and the combustion chamber wall surface. Based on the meshing function of Comsol, considering the influence of the element size, surface curvature, and calculation time, divide the combustion chamber wall surface into triangular elements;

[0022] Preferably, select a surface curvature of 0.16 and an average element area of 5.53 mm 2 .

[0023] S22. Use the contour integration method to calculate the radiation view factor between each small element after dividing the elements. The calculation formula is:

[0024] (3)

[0025] In Equation (3), is the view factor from element to element , is the area of element , and are the contours of elements and respectively, is the coordinate differential corresponding to the position of each point on the contour, is the distance between the points on the contours of the two elements;

[0026] S23. Using the summation formula of view factors, integrate the radiative view factors between each small surface element to obtain the total radiative view factor between the moving blade to be measured, the adjacent blades, and the combustion chamber wall. The view factor summation formula is as follows:

[0027] (4)

[0028] In Equation (4), is the view factor of surface to surface , is the area of the small surface element divided from surface element , is the area of the surface element, is the small surface element divided from to surface .

[0029] The present invention uses the contour integral method to calculate the radiative view factor, transforms the complex surface integral in the view factor calculation into a line integral by using Stokes' theorem. When performing numerical calculations, a large amount of calculation time can be saved, and an effective view factor calculation result can be obtained.

[0030] Further, in the process of calculating the radiative view factor between the turbine blades and the combustion chamber wall in step S2, it further includes: assuming that all other surfaces outside the turbine blade surface may cause occlusion to the radiative heat transfer, performing occlusion judgment on the other surfaces, and gradually excluding the occlusion;

[0031] The method for performing occlusion judgment on the other surfaces includes: increasing the occlusion coefficient , establishing a directed line segment from the centroid of the emitting surface element to the centroid of the receiving surface element, and calculating the intersection point of the vector of this directed line segment and any surface; if the intersection point exists, this surface is the occluding surface, = 0, that is, the radiative view factor between the two surface elements is zero; if the intersection point does not exist, then = 1, and check the next surface; perform occlusion judgment on all surface elements to obtain the final radiative view factor between the surfaces after removing the occlusion; the occlusion coefficient is expressed as:

[0032] ;

[0033] The calculation formula for the total radiative view factor after adding the occlusion judgment is:

[0034] (5).

[0035] Specifically, when performing radiative heat transfer on the surface of a turbine blade, the radiative path may be affected by the occlusion of other surfaces, resulting in the interruption of radiative heat transfer between some surface elements. To accurately calculate the radiative view factor between the surfaces of a turbine blade, a judgment mechanism must be introduced to identify whether there is occlusion between two surface elements. If there is occlusion, the radiative view factor between these two surface elements should be considered zero.

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

[0037] Suppose there are three surfaces , where is the surface of the blade to be measured, is the surface of the hot-end component. When considering single reflection, the calculation expression for single-reflection radiation is:

[0038] (6)

[0039] When considering multiple reflections, the calculation expression for multiple-reflection radiation is:

[0040] (7)

[0041] In equations (6) and (7), , are the radiant emittances of the surface of the hot-end component respectively, , are the emissivities of the surface of the hot-end component respectively; is the radiative view factor from the surface of the blade to be measured to the surface , is the radiative view factor from the surface of the blade to be measured to the surface ; is the emissivity of the surface of the blade to be measured;

[0042] When there are N surfaces, is the surface of the blade to be measured. When considering single reflection, the calculation expression for single-reflection radiation is:

[0043] (8)

[0044] When considering multiple reflections, the calculation expression for multiple-reflection radiation is:

[0045] (9)

[0046] In equations (8) and (9), , …J N are the hot - end components respectively The radiant emittance of the surface 、 are the emissivities of the surfaces of the hot - end components respectively ; is the emissivity of the surface of the blade to be measured.

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

[0048] Further, the method for obtaining the corrected radiation thermometry result by inversion in step S4 includes:

[0049] Subtract the calculated reflected radiation from the total radiation obtained by the radiation pyrometer, and based on the monochromatic thermometry method and Planck's law, inversely obtain the corrected radiation thermometry result.

[0050] The present invention also provides a computer - readable storage medium, on which a computer program is stored. When the program is executed by a processor, the steps of the method for correcting the radiation thermometry error of a turbine blade based on a reflection - radiation model as described above are implemented.

[0051] The present invention also provides a computer device. The computer device includes a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, the steps of the method for correcting the radiation thermometry error of a turbine blade based on a reflection - radiation model as described above are implemented.

[0052] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0053] The method and system for correcting the radiation thermometry error of a turbine blade based on a reflection - radiation model provided by the present invention, through appropriate surface - element division, adopt the contour - integration method, comprehensively consider the surface - element occlusion problem, and through occlusion judgment, eliminate the radiation view factor between two surface - elements with surface - element occlusion, obtaining a fast and effective calculation result of the radiation view factor; on the basis of the existing reflection - radiation model of a turbine blade, the combustion chamber wall surface is added, fully considering the reflected radiation of the hot - end components. During the calculation of the reflected radiation, the problem of multiple reflections of the radiation emitted from each surface between each surface is considered, and a formula for calculating multiple - reflection radiation is designed, fully taking into account the influence of multiple reflections on the calculation of the reflected radiation, being able to calculate a more accurate amount of reflected radiation, reducing the calculation error of the reflected radiation, and effectively improving the accuracy of the radiation thermometry of the turbine blade. Description of the Drawings

[0054] By reading the following detailed description of the preferred embodiments, various other advantages and benefits will become apparent to those of ordinary skill in the art. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not considered to be a limitation of the present invention.

[0055] In the accompanying drawings:

[0056] Figure 1 is a schematic flow chart of the radiation temperature measurement error correction of turbine blades based on the reflection radiation model in an embodiment of the present invention;

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

[0058] Figure 3 is a flow chart of the method for correcting the radiation temperature measurement error of turbine blades based on the reflection radiation model of the present invention;

[0059] Figure 4 is a flow chart of the method for calculating the radiation view factor between turbine blades and the combustion chamber wall surface by using the contour integration method of the present invention;

[0060] Figure 5 is a schematic diagram of the composition of a computer device in an embodiment of the present invention. Detailed Embodiments

[0061] Here, the exemplary embodiments will be described in detail, and the examples are shown in the accompanying drawings. When the following description refers to the accompanying drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present disclosure. On the contrary, 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 the present disclosure are only for the purpose of describing specific embodiments and are not intended to limit the present disclosure. The singular forms "a", "the", and "said" used in the present disclosure and the appended claims are also intended to include the 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 of the associated listed items.

[0063] It should be understood that although the terms first, second, third, etc. may be used in this disclosure to describe various information, such information should not be limited to these terms. These terms are only used to distinguish information of the same type from each other. For example, without departing from the scope of this 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 "when" or "while" or "in response to determining".

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

[0065] The embodiments of the present invention provide a method for correcting the radiation temperature measurement error of turbine blades based on a reflection radiation model. Refer to Figure 3 as shown, which includes the following steps:

[0066] S1. Considering the reflection radiation of the front-stage guide vane, adjacent moving blades, and combustion chamber wall surface simultaneously, establish a reflection radiation model of the turbine blade;

[0067] The method for establishing the reflection radiation model of the turbine blade includes:

[0068] Considering the reflection radiation brought by the front-stage guide vane (such as the first-stage guide vane), adjacent moving blades, and combustion chamber wall surface simultaneously, and considering the influence of the reflection radiation of the hot-end components when measuring the radiation temperature of the turbine blade, the total radiant emittance obtained by the radiation pyrometer for the target surface is: For:

[0069] (1)

[0070] Considering the radiation view factor between surfaces, the total radiant emittance obtained by the target surface is rewritten as: For:

[0071] (2)

[0072] Equations (1) and (2) are the single reflections between surface and the target surface , where is the blackbody radiant emittance at the same temperature as the target surface, is the emissivity of the target surface , is the reflectivity, and , is the radiation view factor from the target surface to surface , is the reflection radiation introduced by the hot-end components.

[0073] S2. Based on the reflection radiation model of the turbine blade, use the contour integral method to calculate the radiation view factors between turbine blades and between the combustion chamber wall surfaces;

[0074] For the method of using the contour integral method to calculate the radiation view factors between turbine blades and between the combustion chamber wall surfaces, see Figure 4 as shown below, which includes the following steps:

[0075] S21. Before calculating the radiation view factor, perform a discretization analysis on the surface of the turbine blade and the combustion chamber wall surface. Based on the meshing function of COMSOL, considering the influence of the element size, surface curvature, and calculation time, divide the combustion chamber wall surface into triangular elements;

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

[0077] S22. Use the contour integral method to calculate the radiation view factors between the small elements after dividing the elements. The calculation formula is:

[0078] (3)

[0079] In formula (3), is the view factor from element to element , is the area of element , and are the contours of elements and respectively, is the coordinate differential corresponding to the position of each point on the contour, is the distance between the points on the contours of the two elements;

[0080] S23. Use the view factor summation formula to integrate the radiation view factors between the small elements to obtain the total radiation view factor between the measured moving blade and the adjacent blade and the combustion chamber wall surface. The view factor summation formula is:

[0081] (4)

[0082] In formula (4), is the view factor from surface to surface , is the area of the small element divided from element , is the area of the element, is the view factor from the divided small element to surface .

[0083] In this embodiment, the contour integral method is used to calculate the radiation view factor. The complex surface integral in the calculation of the view factor is transformed into a line integral by using Stokes' theorem. When performing numerical calculations, a large amount of calculation time can be saved, and an effective view factor calculation result can be obtained.

[0084] In the process of calculating the radiation view factor between turbine blades and the combustion chamber wall surface, it further includes: assuming that all other surfaces outside the turbine blade surface may cause occlusion to the radiative heat transfer, performing occlusion judgment on the said other surfaces, and gradually excluding the occlusion;

[0085] The method for performing occlusion judgment on the said other surfaces includes: increasing the occlusion coefficient , establishing a directed line segment from the centroid of the emitting surface element to the centroid of the receiving surface element, and calculating the intersection point of the vector of this directed line segment and any one surface; if the intersection point exists, then this surface is an occluding surface, , that is, the radiation view factor between the two surface elements is zero; if the intersection point does not exist, then , check the next surface; perform occlusion judgment on all surface elements to obtain the final radiation view factor between the surfaces after excluding occlusion; the occlusion coefficient is expressed as:

[0086] ;

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

[0088] (5).

[0089] When performing radiative heat transfer on the turbine blade surface, the radiation path may be affected by the occlusion of other surfaces, resulting in the interruption of radiative heat transfer between some surface elements. In order to accurately calculate the radiation view factor between turbine blade surfaces, a judgment mechanism must be introduced to identify whether there is occlusion between two surface elements. If there is occlusion, then the radiation view factor between these two surface elements should be regarded as zero.

[0090] S3. Simulate the geometric model of the turbine blade by using COMSOL to obtain the temperature distributions of the turbine blade surface and the combustion chamber wall surface at different temperatures;

[0091] Simulate the geometric model of the turbine blade by using COMSOL. By setting the heat source to different temperatures and selecting the physical fields of convection and heat transfer for research and analysis, the temperature distributions of each turbine blade surface and the combustion chamber wall surface at different ambient temperatures can be obtained.

[0092] As Figure 2As shown, the turbine blade model is simulated using COMSOL, where molybdenum disilicide rods are used as heat sources. By setting their temperatures, the temperature inside the high-temperature furnace is controlled to obtain the temperature distributions on the surfaces of the turbine blade and the combustion chamber at this temperature.

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

[0094] The method for obtaining the corrected radiation temperature measurement result through inversion includes:

[0095] Subtract the calculated reflected radiation from the total radiation obtained by the radiation pyrometer, and based on the monochromatic temperature measurement method and Planck's law, inversely obtain the corrected radiation temperature measurement result.

[0096] When only considering single reflection, use the single reflection radiation formula (5) to calculate the reflected radiation as follows:

[0097]

[0098] When considering multiple reflections, use the multiple reflection radiation formula (6) to calculate the multiple reflection radiation.

[0099] The calculated total radiation is as follows:

[0100]

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

[0102] The total radiation at two wavelengths of 1550 nm and 1650 nm calculated using the single reflection formula is 0.05626 W / 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 1550 nm and 1650 nm calculated using the multiple reflection formula is 0.077990679 and 0.110689594. The errors from the true total radiation are 0.95% and 1.78%. The calculation error of the reflected radiation is effectively reduced.

[0104] The method and system for correcting the radiation temperature measurement error of turbine blades based on the reflection radiation model in this embodiment divide appropriate surface elements, adopt the contour integral method, comprehensively consider the surface element occlusion problem, and through occlusion judgment, eliminate the radiation view factor between two surface elements with surface element occlusion, obtaining a fast and effective calculation result of the radiation view factor; on the basis of the existing reflection radiation model of turbine blades, the combustion chamber wall surface is added, fully considering the reflection radiation of hot end components. During the calculation of reflection radiation, the problem of multiple reflections of the radiation emitted by each surface between each surface is considered, and a formula for calculating multiple reflection radiation is designed, fully taking into account the influence of multiple reflections on the calculation of reflection radiation, being able to calculate a more accurate amount of reflection radiation, reducing the calculation error of reflection radiation, and effectively improving the accuracy of turbine blade radiation temperature measurement.

[0105] Figure 1 Fig. shows the basic process of correcting the radiation temperature measurement error of turbine blades based on the reflection radiation model in this embodiment.

[0106] An embodiment of the present invention also provides a computer device, Figure 5 which is a schematic structural diagram of a computer device provided by an embodiment of the present invention; see the attached 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 method for correcting the radiation temperature measurement error of turbine blades based on the reflection 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 by a bus or other means, Figure 5 taking the connection by bus as an example.

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

[0108] The input system 23 can be used to receive input digital or character information and generate key signal inputs related to the user settings and function controls of the device; the output system 24 can include display devices such as a display screen.

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

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

[0111] The embodiment of the present invention further provides a storage medium containing computer-executable instructions. The computer-executable instructions are used to execute the method for correcting the radiation temperature measurement error of turbine blades based on the reflection radiation model 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, including: installation media such as CD-ROMs, floppy disks, or tape systems; computer system memories or random access memories such as DRAM, DDR RAM, SRAM, EDO RAM, Rambus RAM, etc.; non-volatile memories such as flash memories, magnetic media (such as hard disks or optical storage); registers or other similar types of memory elements, etc.; the storage medium can also include other types of memories or combinations thereof; additionally, the storage medium can be located in the first computer system in which the program is executed, or can be located in a different second computer system, and the second computer system is connected to the first computer system through a network (such as the Internet); the second computer system can provide program instructions to the first computer for execution. The storage medium includes two or more storage media that can reside in different locations (such as in different computer systems connected through a network). The storage medium can store program instructions (such as specifically implemented as a computer program) executable by one or more processors.

[0112] Of course, for the storage medium containing computer-executable instructions provided in the embodiment of the present invention, the computer-executable instructions are not limited to the method for correcting the radiation temperature measurement error of turbine blades based on the reflection radiation model described in the above embodiment, and can also execute related operations in the method for correcting the radiation temperature measurement error of turbine blades based on the reflection radiation model provided in any embodiment of the present invention.

[0113] So far, the technical solution of the present invention has been described in conjunction with the preferred embodiments. However, it is easily understood by those skilled in the art 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 are only the preferred embodiments of the present invention and are not used to limit the present invention; for those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent substitution, 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; 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; is the emissivity of the blade surface to be measured; When there are N surfaces, 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 the surface; is the emissivity of the blade surface to be measured; 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.

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 target surface A single reflection between is the blackbody radiation emittance at the same temperature as the target surface, The target surface The emissivity, is the reflectivity, and , The target surface 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 For facet The area of 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; 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), For face opposite 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 .

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 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, the 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: ； The calculation formula for the total radiation angle coefficient after adding occlusion judgment is: （5）。 5. 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 4 are implemented.

6. A computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: 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 4 are implemented.

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