CN116502469B - Turbine blade temperature correction method and device based on temperature test data - Google Patents
Turbine blade temperature correction method and device based on temperature test data Download PDFInfo
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Abstract
The invention relates to the technical field of turbine blade design of aeroengines, and discloses a turbine blade temperature correction method and device based on temperature test data, which are used for partitioning turbine blades and obtaining corrected simulation node temperature values in each partition based on temperature measurement data of temperature measurement points, wherein the corrected simulation node temperature values are more close to an actual temperature field in a use environment, so that the turbine blade temperature simulation precision and reliability are improved, blade strength assessment can be carried out more accurately, important support is provided for turbine blade design and even development of the whole engine, and the turbine blade temperature correction method and device have good engineering practical value; the method also realizes the direct high-fidelity application of the limited test data in the turbine blade temperature simulation, has low economic cost, improves the utilization efficiency and the value of the limited temperature measurement data, and greatly reduces the consumption of additional basic research resources and time cost.
Description
Technical Field
The invention relates to the technical field of turbine blade design of aeroengines, and discloses a turbine blade temperature correction method and device based on temperature test data.
Background
With the extremely high performance pursuit of modern aircraft engines, turbine components, particularly turbine blades, face significant challenges with turbine front-of-turbine temperatures far exceeding the melting point temperature of the superalloy materials, and air-cooled turbine blade design is one of the key technologies for engine design. The air cooled turbine blade design mainly includes aerodynamic design, cooling design, structural design, temperature field simulation, and strength assessment. The temperature field simulation result is used as an important input of strength evaluation, the accuracy of the simulation result directly influences the reliability of the strength evaluation result, and the temperature field simulation result is very important for the design of the air-cooled turbine blade and even the development of the whole engine.
The existing air-cooled turbine blade temperature field simulation methods mainly comprise two methods: firstly, gas-heat coupling simulation is carried out by using commercial or self-organized software, and secondly, the method is a step-by-step decoupling simulation method of the blade inner and outer flow and the temperature field.
Because the working environment of the turbine blade is bad, the temperature of the blade is measured, and particularly, the temperature of the turbine blade in the working state of an engine is extremely difficult to measure, test data accumulation is insufficient, and engineering designers are difficult to improve the temperature simulation precision of the blade by using limited test data. And the designers at the present stage mainly start from the principle level, and through a large amount of basic researches, the core algorithm is improved, so that the high-precision simulation result which is consistent with the reality can be given. This process generally requires a significant amount of time and resource costs, which is extremely unfriendly to engineering fast-paced, highly reliable engine development.
Disclosure of Invention
The invention aims to provide a turbine blade temperature correction method and device based on temperature test data, which improves the simulation precision and reliability of the turbine blade temperature and ensures that the blade strength evaluation can be carried out more accurately; the method also realizes the direct high-fidelity application of the limited test data in the turbine blade temperature simulation, has low economic cost, improves the utilization efficiency and the value of the limited temperature measurement data, and greatly reduces the consumption of additional basic research resources and time cost.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
a turbine blade temperature correction method based on temperature test data, comprising:
acquiring temperature test data of each temperature measuring point of the turbine blade under test conditions;
performing grid division on the turbine blade simulation model to obtain an initial simulation temperature field of the turbine blade under test conditions, wherein the initial simulation temperature field comprises grid simulation node coordinates of the turbine blade simulation model and simulation temperature values corresponding to simulation nodes;
dividing a turbine blade simulation model into a plurality of partitions;
traversing the temperature measuring points in each partition and the simulation nodes in each partition, wherein in the partition containing the temperature measuring points, the temperature measuring points are used as circle centers, and the simulation nodes in the preset radius range are marked as test area nodes; marking simulation nodes outside a preset radius range in a non-test area by taking the temperature measuring point in the subarea containing the temperature measuring point as a circle center, and marking simulation nodes in the subarea without the temperature measuring point as simulation nodes in the non-test area;
according toCalculating the +.>Temperature value corrected by each test area node +.>Wherein->For the->Temperature test data of each temperature measuring point, +.>For the->The test area nodes to->Distance between temperature measuring points, < >>The number of the temperature measuring points in the corresponding subarea;
temperature value of simulation node of non-test area is adoptedCorrection is carried out, wherein->Is->Corrected temperature value of simulation node of each non-test area,/->Is->Simulation temperature values of simulation nodes of the non-test area, < ->Is the distance +>Nearest +.>Simulation temperature values of the individual test zone nodes, +.>Is->And the temperature value corrected by each test area node.
Further, the temperature test data is a temperature value of a discrete temperature measuring point on the turbine blade under test conditions obtained by using a temperature thermocouple or a temperature measuring crystal.
Further, the method of partitioning a turbine blade simulation model into a plurality of partitions includes: the turbine blade is divided into a blade basin area and a blade back area by adopting a blade body central line.
Further, the turbine blade comprises at least two cavities, the blade basin is divided into a plurality of corresponding blade basin secondary partitions by adopting the central profile of the partition plate between the adjacent cavities, and the blade back is divided into a plurality of corresponding blade back secondary partitions.
In order to achieve the technical effects, the invention also provides a turbine blade temperature correction device based on temperature test data, which comprises:
the data acquisition module is used for acquiring temperature test data of each temperature measuring point of the turbine blade under test conditions;
the simulation module is used for carrying out grid division on the turbine blade simulation model and obtaining an initial simulation temperature field of the turbine blade under the test condition; the initial simulation temperature field comprises grid simulation node coordinates of a turbine blade simulation model and simulation temperature values corresponding to simulation nodes;
the partition module is used for dividing the turbine blade simulation model into a plurality of partitions;
the simulation node dividing module is used for traversing the temperature measuring points in each partition and the simulation nodes in each partition, and in the partition containing the temperature measuring points, the temperature measuring points are used as circle centers, and the simulation nodes in the preset radius range are marked as test area nodes; marking simulation nodes outside a preset radius range in a non-test area by taking the temperature measuring point in the subarea containing the temperature measuring point as a circle center, and marking simulation nodes in the subarea without the temperature measuring point as simulation nodes in the non-test area;
an analysis and correction module for followingCalculating the +.>Temperature value corrected by each test area node +.>Wherein->For the->Temperature test data of each temperature measuring point, +.>For the->The test area nodes to->Distance between temperature measuring points, < >>The number of the temperature measuring points in the corresponding subarea; the temperature value of the simulation node of the non-test area adopts +.>Correction is carried out, wherein->Is->Corrected temperature value of simulation node of each non-test area,/->Is->Simulation temperature values of simulation nodes of the non-test area, < ->Is the distance +>Nearest +.>Simulation temperature values of the individual test zone nodes, +.>First->And the temperature value corrected by each test area node.
Further, the data acquisition module comprises a temperature thermocouple or a temperature measuring crystal, and the temperature thermocouple or the temperature measuring crystal is arranged on the surface of the turbine blade or embedded in the turbine blade and is used for obtaining the temperature value of the discrete temperature measuring point on the turbine blade under the test condition.
Further, the partitioning module is configured to divide the turbine blade simulation model into at least a basin area and a back area.
Further, the partition module is further used for dividing the leaf basin into a plurality of corresponding leaf basin secondary partitions according to the central molded surface of the partition plate between the adjacent cavities, and the leaf back is divided into a plurality of corresponding leaf back secondary partitions.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, the turbine blade is partitioned, the corrected simulation node temperature values in each partition are obtained based on the temperature measurement data of the temperature measuring points, the corrected simulation node temperature values are more close to the actual temperature field in the use environment, the simulation precision and reliability of the turbine blade temperature are improved, the blade strength assessment can be more accurately carried out, important support is provided for the design of the turbine blade and even the development of the whole engine, and the method has good engineering practical value;
2. the invention also realizes the direct high-fidelity application of the limited test data in the turbine blade temperature simulation, has low economic cost, improves the utilization efficiency and the value of the limited temperature measurement data, and greatly reduces the consumption of additional basic research resources and time cost.
Drawings
FIG. 1 is a schematic illustration of a cross-sectional configuration of a turbine blade according to an embodiment;
FIG. 2 is an enlarged schematic view of portion A of FIG. 1;
FIG. 3 is a block diagram of a turbine blade temperature correction device based on temperature test data in an embodiment;
1, a temperature measuring point; 2. testing area nodes; 3. non-test area simulation nodes; 4. a leaf basin area; 5. a leaf back region; 6. a cavity; 7. a data acquisition module; 8. a simulation module; 9. a partition module; 10. a simulation node dividing module; 11. and an analysis and correction module.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Examples
Referring to FIGS. 1-3, a turbine blade temperature correction method based on temperature test data includes:
acquiring temperature test data of each temperature measuring point 1 of the turbine blade under test conditions;
performing grid division on the turbine blade simulation model to obtain an initial simulation temperature field of the turbine blade under test conditions, wherein the initial simulation temperature field comprises grid simulation node coordinates of the turbine blade simulation model and simulation temperature values corresponding to simulation nodes;
dividing a turbine blade simulation model into a plurality of partitions;
traversing the temperature measuring point 1 in each partition and the simulation nodes in each partition, wherein in the partition containing the temperature measuring point, the temperature measuring point 1 is used as a circle center, and the simulation nodes in a preset radius range are marked as test area nodes 2 (such as points in the circle in fig. 2); marking non-test area simulation nodes 3 by using the temperature measuring points in the subarea containing the temperature measuring points 1 as circle centers and the simulation nodes outside the preset radius range, and marking the simulation nodes in the subarea without the temperature measuring points as the non-test area simulation nodes 3;
according toCalculating the +.>Temperature value corrected by the individual test field node 2 +.>Wherein->For the->Temperature test data of individual temperature measuring points 1, +.>For the->The test area nodes 2 to->Distance of each temperature measuring point 1->The number of the temperature measuring points 1 in the corresponding subarea;
the temperature value of the non-test area simulation node 3 is adoptedCorrection is carried out, wherein->Is->Corrected temperature value of the individual non-test area emulation node 3, < >>Is->Simulation temperature value of the individual non-test area simulation node 3, is->Is the distance +>Nearest +.>Simulation temperature values of the individual test field nodes 2, < >>Is->And the temperature value corrected by each test area node 2.
In the embodiment, an initial simulation temperature value of grid simulation nodes on the turbine blade is obtained by carrying out grid division on a turbine blade simulation model; then, the turbine blade is partitioned according to the structure, and each simulation node is divided into a test area node 2 and a non-test area simulation node 3 according to the distribution position of the temperature measuring point 1 of the turbine blade under the test condition. The test area node 2 corrects the simulation temperature value according to the test temperature value of the temperature measuring point 1 in the corresponding partition to obtain a corrected temperature value of the test area node 2; and the simulation temperature value of the non-test area simulation node 3 is corrected according to the ratio of the temperature value of the nearest temperature measuring point 1 to the simulation temperature value of the temperature measuring point 1 as a correction coefficient, so as to obtain the corrected simulation temperature value of the non-test area simulation node 3. According to the turbine blade temperature correction method, the actual temperature field of the turbine blade is obtained based on the temperature measurement data of the temperature measuring point 1, the temperature simulation precision and reliability of the turbine blade are improved, the blade strength assessment can be carried out more accurately, important support is provided for the design of the turbine blade and even the development of the whole engine, and the turbine blade temperature correction method has good engineering practical value; the method also realizes the direct high-fidelity application of the limited test data in the turbine blade temperature simulation, has low economic cost, improves the utilization efficiency and the value of the limited temperature measurement data, and greatly reduces the consumption of additional basic research resources and time cost.
The temperature test data in this embodiment is the temperature value of the discrete temperature measuring point 1 on the turbine blade under test conditions obtained using a temperature thermocouple or a temperature measuring crystal. The temperature value can be temperature test data under the test condition of the turbine blade parts, and can also be temperature test data of the turbine blade under the working state of the engine. The preset radius can be valued according to the simulated temperature field distribution of the turbine blade or according to the number of the test area nodes 2 contained in the circle, for example, the number of the test area nodes contained in the circle is controlled to be 6-10.
Dividing the turbine blade simulation model into a plurality of partitions, comprising: the division of the turbine blade into a basin region 4 and a back region 5 takes place with the blade body center line. If at least two cavities 6 exist in the turbine blade, the center profile of the partition plate between the adjacent cavities 6 can be used for dividing the blade basin into a plurality of corresponding blade basin secondary partitions, and the blade back is divided into a plurality of corresponding blade back secondary partitions.
In addition, after the initial simulation temperature value and the corrected temperature value of the turbine blade test area node 2 and the initial simulation temperature value and the corrected temperature value of the non-test area simulation node 3 are obtained, temperature correction coefficients of the corresponding partition simulation nodes can be constructed, for example: temperature correction coefficient of test zone node 2Wherein->Is->Temperature correction coefficient of each test area node 2, temperature correction coefficient of test area node 2 +.>Wherein->Is->The temperature correction coefficients of the simulation nodes 3 in the non-test area are then constructed, and the temperature correction coefficient fields of all the simulation nodes are used as correction reference values of simulation temperatures of turbine blades in other heat exchange similar states, so that the accuracy of the simulation temperatures can be greatly improved, the application range of temperature measurement data in temperature simulation is realized, and support is provided for the intensity evaluation of high reliability of the turbine blades or the improved design of the blades.
Based on the same inventive concept, the present embodiment further provides a turbine blade temperature correction device based on temperature test data, referring to fig. 3, including:
the data acquisition module 7 is used for acquiring temperature test data of each temperature measuring point 1 of the turbine blade under test conditions; the data acquisition module 7 as in the present embodiment comprises a thermocouple or a crystal mounted on the surface of the turbine blade or embedded in the turbine blade for obtaining the temperature values of the discrete temperature measuring points 1 on the turbine blade under test conditions.
The simulation module 8 is used for carrying out grid division on the simulation model of the turbine blade, and obtaining an initial simulation temperature field of the turbine blade under test conditions; the initial simulation temperature field comprises grid simulation node coordinates of a turbine blade simulation model and simulation temperature values corresponding to simulation nodes; in this embodiment, the existing method may be used to obtain the initial simulation temperature field of the turbine blade under the test condition, for example, a step-by-step decoupling simulation method of the inner and outer flow+temperature fields may be used, or a gas-heat coupling simulation method may be used, or other methods capable of obtaining the initial simulation temperature field under the test condition.
A partition module 9, the partition module 9 being configured to divide the turbine blade simulation model into a plurality of partitions; the turbine blade simulation model may be divided into at least a basin area 4 and a back area 5 according to the structure of the turbine blade itself as in the present embodiment. In the case of a turbine blade comprising at least two cavities 6, the blade basin can also be divided into a plurality of corresponding blade basin secondary sections according to the central profile of the partition between adjacent cavities 6, and the blade back into a plurality of corresponding blade back secondary sections.
The simulation node dividing module 10 is configured to traverse the temperature measuring point 1 in each partition and the simulation nodes in each partition, and in the partition containing the temperature measuring point, the temperature measuring point 1 is the center of a circle and the simulation nodes in the preset radius range are marked as the nodes 2 of the test area (such as the points in the circle in fig. 2); marking non-test area simulation nodes 3 by using the temperature measuring points in the subarea containing the temperature measuring points 1 as circle centers and the simulation nodes outside the preset radius range, and marking the simulation nodes in the subarea without the temperature measuring points as the non-test area simulation nodes 3;
an analysis correction module 11, the analysis correction module 11 is used for followingCalculating the +.>Temperature value corrected by the individual test field node 2 +.>Wherein->For the->Temperature test data of individual temperature measuring points 1, +.>For the->The test area nodes 2 to->Distance of each temperature measuring point 1->The number of the temperature measuring points 1 in the corresponding subarea; the temperature value of the non-test area simulation node 3 is +.>Correction is carried out, wherein->Is->Corrected temperature value of the individual non-test area emulation node 3, < >>Is->Simulation temperature value of the individual non-test area simulation node 3, is->Is the distance +>Nearest +.>Simulation temperature values of the individual test field nodes 2, < >>Is->And the temperature value corrected by each test area node 2.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (8)
1. A turbine blade temperature correction method based on temperature test data, comprising:
acquiring temperature test data of each temperature measuring point of the turbine blade under test conditions;
performing grid division on the turbine blade simulation model to obtain an initial simulation temperature field of the turbine blade under test conditions, wherein the initial simulation temperature field comprises grid simulation node coordinates of the turbine blade simulation model and simulation temperature values corresponding to simulation nodes;
dividing a turbine blade simulation model into a plurality of partitions;
traversing the temperature measuring points in each partition and the simulation nodes in each partition, wherein in the partition containing the temperature measuring points, the temperature measuring points are used as circle centers, and the simulation nodes in the preset radius range are marked as test area nodes; marking simulation nodes outside a preset radius range in a non-test area by taking the temperature measuring point in the subarea containing the temperature measuring point as a circle center, and marking simulation nodes in the subarea without the temperature measuring point as simulation nodes in the non-test area;
according toCalculating the +.>Temperature value corrected by each test area node +.>Wherein->For the->Temperature test data of each temperature measuring point, +.>For the->The test area nodes to->Distance between temperature measuring points, < >>The number of the temperature measuring points in the corresponding subarea;
temperature value of simulation node of non-test area is adoptedCorrection is carried out, wherein->Is->Corrected temperature value of simulation node of each non-test area,/->Is->Simulation temperature values of simulation nodes of the non-test area, < ->Is the distance ofNearest +.>Simulation temperature values of the individual test zone nodes, +.>Is->And the temperature value corrected by each test area node.
2. The method for correcting the temperature of a turbine blade based on temperature test data according to claim 1, wherein the temperature test data is a temperature value of a discrete temperature measurement point on the turbine blade under test conditions obtained using a temperature thermocouple or a temperature measurement crystal.
3. The method for turbine blade temperature correction based on temperature test data according to claim 1, wherein the method for dividing the turbine blade simulation model into a plurality of partitions comprises: the turbine blade is divided into a blade basin area and a blade back area by adopting a blade body central line.
4. A method of temperature correction of a turbine blade based on temperature test data as claimed in claim 3 wherein the turbine blade includes at least two cavities therein, the basin being divided into a plurality of corresponding basin secondary sections by a central profile of a partition between adjacent cavities, the back being divided into a plurality of corresponding back secondary sections.
5. A turbine blade temperature correction device based on temperature test data, comprising:
the data acquisition module is used for acquiring temperature test data of each temperature measuring point of the turbine blade under test conditions;
the simulation module is used for carrying out grid division on the turbine blade simulation model and obtaining an initial simulation temperature field of the turbine blade under the test condition; the initial simulation temperature field comprises grid simulation node coordinates of a turbine blade simulation model and simulation temperature values corresponding to simulation nodes;
the partition module is used for dividing the turbine blade simulation model into a plurality of partitions;
the simulation node dividing module is used for traversing the temperature measuring points in each partition and the simulation nodes in each partition, and in the partition containing the temperature measuring points, the temperature measuring points are used as circle centers, and the simulation nodes in the preset radius range are marked as test area nodes; marking simulation nodes outside a preset radius range in a non-test area by taking the temperature measuring point in the subarea containing the temperature measuring point as a circle center, and marking simulation nodes in the subarea without the temperature measuring point as simulation nodes in the non-test area;
an analysis and correction module for followingCalculating the +.>Temperature value corrected by each test area node +.>Wherein->For the->Temperature test data of each temperature measuring point, +.>For the->The test area nodes to->Distance between temperature measuring points, < >>The number of the temperature measuring points in the corresponding subarea; the temperature value of the simulation node of the non-test area adopts +.>Correction is carried out, wherein->Is->Corrected temperature value of simulation node of each non-test area,/->Is->Simulation temperature values of simulation nodes of the non-test area, < ->Is the distance +>Nearest +.>Simulation temperature values of the individual test zone nodes, +.>First->And the temperature value corrected by each test area node.
6. The turbine blade temperature correction device based on temperature test data according to claim 5, wherein the data acquisition module comprises a thermocouple or a crystal mounted on the surface of the turbine blade or embedded in the turbine blade for obtaining temperature values of discrete temperature measurement points on the turbine blade under test conditions.
7. The turbine blade temperature correction device based on temperature test data of claim 5, wherein the partitioning module is configured to divide the turbine blade simulation model into at least a basin area and a back area.
8. The turbine blade temperature correction device based on temperature test data of claim 7, wherein the partition module is further configured to divide the blade basin into a plurality of corresponding blade basin secondary partitions and the blade back into a plurality of corresponding blade back secondary partitions according to a central profile of a partition between adjacent cavities.
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| 涡轮叶片表面温度场及综合冷却效果试验研究;邓丽君;《南京航空航天大学学报》;第53卷(第3期);442-448 * |
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