Turbine blade tip heat exchange calculation method, electronic device and medium
By dividing the turbine blade tip region into heat transfer areas and constructing a flow network diagram, and using a one-dimensional pipe network flow calculation program, the problem of low efficiency in tip heat transfer calculation was solved, and efficient tip heat transfer calculation was achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2021-06-22
- Publication Date
- 2026-04-07
AI Technical Summary
In existing technologies, calculating heat transfer at the tip of turbine blades requires a large amount of manpower and computing resources, resulting in low computational efficiency.
The turbine blade tip region is divided into several heat transfer regions, a flow network diagram at the blade tip is constructed, and the flow heat transfer calculation results at the blade tip are extracted using a one-dimensional pipe network flow heat transfer calculation program.
It improves the calculation efficiency of tip heat transfer, reduces the workload of modeling and mesh generation, and meets the calculation accuracy requirements, making it suitable for the optimization and iteration of tip cooling design.
Smart Images
Figure CN115510569B_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of aero-engines, and particularly relates to a turbine blade tip heat exchange calculation method for aero-engines, an electronic device and a medium. BACKGROUND
[0002] With the development of modern aero-engine technology, the turbine inlet temperature is continuously increased. Therefore, the thermal load borne by the turbine is also continuously increased. The high-pressure turbine blade tip is one of the most easily damaged hot-end parts of an aero-engine, and the turbine blade tip cooling design is related to the efficiency, service life and safety of the whole machine, and has very important research value. To obtain an accurate temperature distribution of the blade tip to guide the blade tip cooling design, the heat exchange of the blade tip needs to be estimated.
[0003] The turbine blade tip usually adopts a structure without a crown, and can be generally divided into three types: a flat tip as shown in FIG. 1, a squealer tip as shown in FIGS. 2, 3, 4 and 5, and a winglet tip as shown in FIGS. 6 and 7. Figure 1 Figure 2a Figure 2b Figure 2c Figure 2d Figure 3a 3b
[0004] In the current engineering design, in order to evaluate the temperature field of the turbine blade tip or further develop the blade tip cooling design, the third type of boundary condition of the blade tip heat exchange, that is, the gas migration temperature (heat exchange temperature) and the heat exchange coefficient, should be calculated first. The heat exchange calculation of the blade tip usually adopts three-dimensional CFD (computational fluid dynamics) numerical simulation, which needs to be modeled, meshed and numerically calculated for the blade tip, which will consume a large amount of manual and computing resources. Moreover, the local modification and optimization of the blade tip, such as the slight adjustment of the geometric configuration parameters of the squealer tip, such as the squealer depth, the squealer width and the baffle rib, need to repeat the whole simulation calculation process of modeling, meshing and numerical calculation, which greatly reduces the calculation efficiency. SUMMARY
[0005] The present application aims to solve the technical problem that the blade tip heat exchange calculation in the prior art consumes a large amount of manual and computing resources and has low calculation efficiency, and provides a turbine blade tip heat exchange calculation method, an electronic device and a medium.
[0006] The present application solves the above technical problem by the following technical scheme:
[0007] According to an embodiment of the present application, a turbine blade tip heat exchange calculation method is provided, comprising:
[0008] dividing the turbine blade tip region into a plurality of heat exchange regions;
[0009] based on the several heat exchange regions, a tip flow network diagram of the turbine blade tip is built;
[0010] according to the tip flow network diagram, a tip flow heat exchange calculation input file is generated; and,
[0011] according to the tip flow heat exchange calculation input file, a one-dimensional pipe network flow heat exchange calculation program is run to extract tip flow heat exchange calculation results.
[0012] Optionally, the step of dividing the turbine blade tip region into several heat exchange regions comprises:
[0013] the tip shroud edge and the tip suction edge of the turbine blade tip are respectively divided into several arc lengths according to arc length;
[0014] a plurality of virtual lines are formed by connecting the endpoints of each arc length on the tip shroud edge and the tip suction edge;
[0015] the turbine blade tip region is divided into several heat exchange regions according to the plurality of virtual lines.
[0016] Optionally, in the step of building the tip flow network diagram of the turbine blade tip,
[0017] each heat exchange region of the tip flow network diagram comprises at least one axial flow heat exchange pipe element, at least two circumferential flow heat exchange pipe elements, at least one circumferential flow inlet and at least one circumferential flow outlet, and the tip flow network diagram further comprises at least one axial flow inlet and at least one axial flow outlet;
[0018] wherein the tip axial flow flows in from the at least one axial flow inlet, flows through all the axial flow heat exchange pipe elements respectively and flows out from the at least one axial flow outlet; the tip circumferential flow flows in from the corresponding circumferential flow inlet respectively, flows through the corresponding at least two circumferential flow heat exchange pipe elements, intersects with the tip axial flow between the at least two circumferential flow heat exchange pipe elements, and flows out from the corresponding circumferential flow outlet.
[0019] Optionally, the tip flow network diagram further comprises a loss element for simulating flow pressure loss;
[0020] the tip axial flow flows in from the at least one axial flow inlet, flows through the loss element, and then flows through all the axial flow heat exchange pipe elements respectively and flows out from the at least one axial flow outlet.
[0021] Optionally, in the step of generating the tip flow heat exchange calculation input file,
[0022] The boundary condition part of the blade tip flow heat exchange calculation input file comprises a geometric boundary condition and an aerodynamic boundary condition, the geometric boundary condition is used to define the blade tip axial flow geometric condition and the blade tip circumferential flow geometric condition, and the geometric boundary condition is also used to define the geometric parameters of the heat exchange pipe element, and the aerodynamic boundary condition is used to define the aerodynamic related parameters of the inlet and the outlet.
[0023] Optionally, the step of generating the blade tip flow heat exchange calculation input file comprises:
[0024] The logic architecture part is written according to the input format required by the one-dimensional pipe network flow heat exchange calculation program to generate the blade tip flow heat exchange calculation input file.
[0025] Optionally, the method further comprises:
[0026] The extracted blade tip flow heat exchange calculation result comprises the temperature and the heat exchange coefficient of the heat exchange pipe element, and the temperature and the heat exchange coefficient of the heat exchange pipe element are taken as the third type of boundary of the heat exchange region.
[0027] Optionally, the turbine blade tip comprises at least one of a flat tip, a grooved tip and a winglet tip.
[0028] According to an embodiment of the present application, an electronic device is provided, comprising a memory, a processor and a computer program stored in the memory and executable on the processor, and the processor implements the turbine blade tip heat exchange calculation method as described above when executing the computer program.
[0029] According to an embodiment of the present application, a computer readable storage medium is provided, which stores a computer program, and the computer program is executed by a processor to implement the turbine blade tip heat exchange calculation method as described above.
[0030] On the basis of common knowledge in the art, the preferred conditions can be combined at will, that is, to obtain each preferred embodiment of the present application.
[0031] The positive progress effect of the present application is that:
[0032] The turbine blade tip heat exchange calculation method, the electronic device and the medium provided by the present application model the flow process of the gas through the tip clearance as one-dimensional pipe network flow based on one-dimensional pipe network flow, and carry out tip heat exchange calculation by means of one-dimensional pipe network flow heat exchange calculation program. Since simulation pretreatment work such as tip three-dimensional modeling and grid division is not required, the turbine blade tip heat exchange calculation efficiency is greatly improved while the accuracy of the tip flow heat exchange calculation is ensured. BRIEF DESCRIPTION OF DRAWINGS
[0033] The features and advantages of the present application will be better understood after reading the detailed description of the embodiments of the present application in conjunction with the accompanying drawings. In the drawings, the components are not necessarily drawn to scale, and components of similar or identical function or structure can be designated with identical or similar reference numerals.
[0034] Figure 1 Structure diagram of a flat tip of a turbine blade.
[0035] Figure 2a Structure diagram of a first type of turbine blade concave tip.
[0036] Figure 2b Structure diagram of a second type of turbine blade concave tip.
[0037] Figure 2c Structure diagram of a third type of turbine blade concave tip.
[0038] Figure 2d Structure diagram of a fourth type of turbine blade concave tip.
[0039] Figure 3a Structure diagram of a first type of turbine blade winglet tip.
[0040] Figure 3b Structure diagram of a second type of turbine blade winglet tip.
[0041] Figure 4 Flow diagram of a turbine blade tip heat exchange calculation method according to a preferred embodiment of the present application.
[0042] Figure 5a First flow structure diagram of a turbine blade tip.
[0043] Figure 5b Second flow structure diagram of a turbine blade tip.
[0044] Figure 6 Flow heat exchange region division diagram of a turbine blade tip according to a preferred embodiment of the present application.
[0045] Figure 7 Flow network diagram of a turbine blade tip according to a preferred embodiment of the present application.
[0046] Figure 8 Comparison diagram showing heat exchange coefficient calculation results of each calculation domain of a turbine blade tip.
[0047] Figure 9 Comparison diagram showing gas migration temperature calculation results of each calculation domain of a turbine blade tip.
[0048] Figure 10A structure schematic diagram of an electronic device for implementing a turbine blade tip heat exchange calculation method according to another preferred embodiment of the present application. DETAILED DESCRIPTION
[0049] The present application is further illustrated by the following examples without limiting the present application to the examples.
[0050] In order to overcome the above-mentioned defects existing at present, the present embodiment provides a turbine blade tip heat exchange calculation method, which comprises the following steps:
[0051] The turbine blade is an important component in the gas turbine engine, which converts the high-temperature and high-pressure gas heat energy from the combustion chamber into mechanical energy. In order to ensure long-term stable operation in the extreme environment of high temperature and high pressure, high-efficiency cooling technology needs to be used to cool the turbine blade.
[0052] In the present embodiment, the turbine blade tip includes at least one of a flat tip, a grooved tip and a winglet tip, and the type of the turbine blade tip is not specifically limited, which can be adjusted and selected according to actual needs.
[0053] In the present embodiment, the flow heat exchange of the tip is modeled as one-dimensional pipe network flow, which greatly improves the tip heat exchange calculation efficiency while ensuring the accuracy of the tip flow heat exchange calculation.
[0054] Specifically, as an embodiment, as shown in Figure 4 The turbine blade tip heat exchange calculation method provided by the present embodiment mainly comprises the following steps:
[0055] Step 101, dividing the tip heat exchange region.
[0056] In the present step, the turbine blade tip region is divided into several heat exchange regions.
[0057] As a preferred embodiment, in the present step, the tip shroud edge and the tip suction edge of the turbine blade tip are respectively divided into several arc lengths according to the arc length; the end points of each arc length on the tip shroud edge and the tip suction edge are connected to form several virtual lines; and the turbine blade tip region is divided into several heat exchange regions according to the several virtual lines.
[0058] In the present embodiment, the number of heat exchange regions, arc lengths and virtual lines is not specifically limited, which can be adjusted and selected according to actual needs and scenes.
[0059] Specifically, as mentioned above, the turbine blade tip structure without crown includes flat tip as shown in Figure 1 , grooved tip as shown in Figure 2a , Figure 2b , Figure 2c and winglet tip as shown in Figure 2d and Figure 3a , 3b , and each of the tip structures mentioned above is mainly composed of groove 1 and rib edge 2, and the rib height e and rib width w are important structural parameters of the rib edge 2.
[0060] As shown in Figure 5a and Figure 5b , the leading edge point 7 at the leading edge position and the trailing edge point 8 at the trailing edge position divide the turbine blade tip edge into the tip blade pressure side 9 and the tip blade suction side 10, and the tip blade pressure side 9 is located at the top of the blade pressure surface 5, and the tip blade suction side 10 is located at the top of the blade suction surface 6. According to the pressure difference driving theory, the turbine blade tip flow combines the axial flow 3 from the leading edge point 7 to the trailing edge point 8 and the circumferential flow 4 from the tip blade pressure side 9 to the tip blade suction side 10, and therefore, according to the one-dimensional pipe network flow, the tip can be geometrically divided into several different heat exchange regions, and each heat exchange region is distributed with “pipe elements” for calculating the axial flow 3 and the circumferential flow 4 respectively, and the third type of boundary conditions of the tip region can be calculated through the one-dimensional pipe network flow calculation program Flowmaster or Flownet.
[0061] In this step, in order to obtain more detailed tip heat exchange coefficient and heat exchange temperature distribution, the tip region is divided into 5-7 heat exchange regions, and preferably, in the present embodiment, the tip region is divided into 7 heat exchange regions. Specifically, the tip blade pressure side 9 and the tip blade suction side 10 are respectively divided into 5-7 segments according to arc length, and preferably, in the present embodiment, the tip blade pressure side 9 and the tip blade suction side 10 are divided into 7 segments, and the connecting line of the end points of each segment arc length is used as the dividing boundary, that is, the virtual connecting line. Referring to Figure 6 , in the present embodiment, the tip is divided into 7 regions through the connecting line 11 of the end points of each segment arc length on the tip blade pressure side 9 and the tip blade suction side 10, that is, the heat exchange region 12, the heat exchange region 13, …, and the heat exchange region 18.
[0062] Step 102, building a tip flow network diagram.
[0063] In this step, based on the several heat exchange regions divided, the tip flow network diagram of the turbine blade tip is built.
[0064] Specifically, based on the 7 heat exchange regions of the tip divided in Figure 6 , the tip flow network diagram is built. As shown in Figure 7As shown in the tip flow network diagram, the axial flow inlet of the leading edge region joins the loss element 18 for simulating the flow pressure loss, and each heat exchange region includes 3 heat exchange tube elements 19, i.e., one axial flow heat exchange tube element and two circumferential flow heat exchange tube elements. According to the tip flow characteristics, the tip axial flow path starts from the axial flow inlet 20, flows through the loss element 18 and 7 axial flow heat exchange tube elements, and flows out from the axial flow outlet 28; the tip circumferential flow path starts from the 7 circumferential flow inlets 21, 22, …, 27, flows through the corresponding 2 circumferential flow heat exchange tube elements in sequence, intersects with the tip axial flow path between the tube elements, and then flows out from the 7 circumferential flow outlets 29, 30, …, 35 corresponding to the circumferential flow inlets.
[0065] Step 103, generating a tip flow heat exchange calculation input file.
[0066] In this step, according to the tip flow network diagram, a tip flow heat exchange calculation input file is generated.
[0067] As a preferred embodiment, in this step, the boundary condition part of the tip flow heat exchange calculation input file includes geometric boundary conditions and aerodynamic boundary conditions, the geometric boundary conditions are used to define the tip axial flow geometric conditions and the tip circumferential flow geometric conditions, and the geometric boundary conditions are also used to define the geometric parameters of the heat exchange tube elements, and the aerodynamic boundary conditions are used to define the aerodynamic related parameters of the inlets and outlets.
[0068] As a preferred embodiment, in this step, the logical architecture part of the tip flow heat exchange calculation input file is written according to the input format required by the one-dimensional tube network flow heat exchange calculation program.
[0069] Specifically, the tip flow heat exchange calculation input file includes a logical architecture part and a boundary condition part, the logical architecture part should be written according to the input format required by the tip flow calculation program, such as Flowmaster or Flownet, and the boundary condition part includes geometric boundary conditions and aerodynamic boundary conditions, and the writing method is as follows:
[0070] 1) Geometric boundary conditions: since each heat exchange region includes one axial flow heat exchange tube element for describing the tip axial flow and two circumferential flow heat exchange tube elements for describing the circumferential flow, the tube element inlet and outlet of the axial flow should be located as Figure 6The virtual connection 11 of the end point of each arc length on the tip shroud edge 9 and the tip suction edge 10, the inlet and outlet width of the tube element is the projection length of the end point virtual connection 11 in the tip region, and the flow length of the tube element can be the equal division length of the middle arc of the tip shroud edge 9 and the tip suction edge 10. The two tube elements of the circumferential flow can be divided into inlet tube elements and outlet tube elements, the inlet tube elements are located on the shroud side, and the circumferential flow inlets 21, 22, …, 27 are used as the inlets of the tube elements, respectively, and the outlets are located on the middle arc of the tip shroud edge 9 and the tip suction edge 10, the inlet width of the inlet tube element can be the equal division length of the tip shroud edge 9, and the outlet width can be the equal division length of the middle arc, and correspondingly, the outlet tube elements are located on the shroud side, the inlets are located on the middle arc of the tip shroud edge 9 and the tip suction edge 10, and the circumferential flow outlets 29, 30, …, 35 are used as the outlets of the tube elements, respectively, and the inlet width of the outlet tube element can be the equal division length of the middle arc, and the outlet width can be the equal division length of the tip suction edge 10. It should be pointed out that in the divided heat exchange region, if there are ribs as shown in Figure 2a to Figure 2d and Figure 3a and Figure 3b the rib edge 2, the corresponding tube element should be selected as the “rib tube” type, and the rib height e and the rib width w and other geometric parameters need to be input, and if the flat tip as shown in Figure 1 is used, the tube element should be selected as the “smooth tube” type, and the parameters of the rib do not need to be input.
[0071] 2) Aerodynamic boundary conditions: the total temperature and the total pressure of the 14 inlets and outlets, including the circumferential flow inlets 21, 22, …, 27 and the circumferential flow outlets 29, 30, …, 35, are taken from the turbine aerodynamic S2 data, in order to obtain more accurate tip flow heat exchange calculation results, the total temperature and the total pressure of the inlets and outlets should be the average values of the equal division arc length on the tip shroud edge 9 and the tip suction edge 10.
[0072] Step 104, running a one-dimensional tube network flow heat exchange calculation program.
[0073] In this step, the one-dimensional tube network flow heat exchange calculation program Flowmaster or Flownet is run, but the calculation program is not limited to this, and the corresponding selection can be made according to the actual situation.
[0074] Step 105, extracting the tip flow heat exchange calculation results.
[0075] In this step, the tip flow heat exchange calculation results extracted include the temperature and the heat exchange coefficient of the heat exchange tube element, and the temperature and the heat exchange coefficient of the heat exchange tube element are used as the third type of boundary of the heat exchange region.
[0076] The heat exchange coefficient is used to represent the heat exchange capacity between fluid and solid, and refers to the heat that can be transferred between the fluid and the wall per unit area per unit temperature difference and per unit time.
[0077] Specifically, the pipe element temperature and the heat exchange coefficient calculated in the heat exchange calculation result file are the third type of boundary of each heat exchange region of the blade tip. It should be noted that, in the blade tip flow, the circumferential flow is usually stronger than the axial flow, and therefore, the heat exchange parameters of the inlet pipe element and the outlet pipe element of the circumferential flow are more accurate in representing the third type of boundary condition of each heat exchange region.
[0078] The heat exchange temperature (gas migration temperature) and the heat exchange coefficient of each calculation region of the turbine blade tip calculated by the Flownet are shown in FIGS. Figure 8 、 Figure 9 , Figure 8 、 Figure 9 The horizontal coordinate (region number) in the above figures represents the 7 heat exchange regions of the blade tip from the leading edge to the trailing edge, which are represented by the numbers "1", "2",..., "7" in sequence. Figure 8 The vertical coordinate in the above figures represents the heat exchange coefficient. Figure 9 The vertical coordinate in the above figures represents the heat exchange temperature, and the heat exchange temperature and the heat exchange coefficient of each region are the average values of the parameters of the inlet pipe element and the outlet pipe element in each region.
[0079] The turbine blade tip heat exchange calculation method provided in the embodiment has the following beneficial effects:
[0080] 1) Compared with the traditional three-dimensional CFD numerical simulation method, the one-dimensional pipe network flow heat exchange calculation method for the turbine blade tip provided in the embodiment greatly improves the calculation efficiency without the need for simulation preprocessing work such as blade tip modeling and grid division. The calculation time for a single blade tip and a single working condition is 10-20 seconds, which is suitable for scheme screening.
[0081] 2) The embodiment conforms to the real flow heat exchange mechanism of the turbine blade tip, and the flow heat exchange effect of the blade tip can be equivalently restored through the setting of different pipe element geometric parameters and aerodynamic parameters, and the calculation accuracy meets the requirements. As shown in FIGS. Figure 8 、 Figure 9 , Figure 8 、 Figure 9 respectively show the gas migration temperature and the heat exchange coefficient of each calculation region of the turbine blade tip calculated by the heat exchange calculation method of the embodiment. Through comparison with the three-dimensional CFD results, it is shown that the heat exchange calculation method of the embodiment has high calculation accuracy, and the feasibility and engineering practical value of the heat exchange calculation method of the embodiment are verified.
[0082] 3) In the iteration and optimization stage of the turbine blade tip, if the adjustment of the blade tip structure parameters is needed, the embodiment only needs to adjust the geometric parameters of the pipe elements in the pipe network program, which is very convenient and fast. Therefore, the embodiment has great potential in the design and optimization of turbine blade cooling structure.
[0083] Figure 10 A structural schematic diagram of an electronic device is provided for the embodiment. The electronic device includes a memory, a processor, and a computer program stored in the memory and executable on the processor, and the processor implements the turbine blade tip heat exchange calculation method as described above when executing the program, Figure 10 The electronic device 90 shown is merely an example and should not impose any limitation on the functions and use range of the embodiment of the present application.
[0084] The electronic device 90 can be in the form of a general computing device, for example, it can be a server device. The components of the electronic device 90 can include but are not limited to the above-mentioned at least one processor 91, the above-mentioned at least one memory 92, and a bus 93 connecting different system components including the memory 92 and the processor 91.
[0085] The bus 93 includes a data bus, an address bus, and a control bus.
[0086] The memory 92 can include volatile memory, such as a random access memory (RAM) 921 and / or a cache memory 922, and can further include a read-only memory (ROM) 923.
[0087] The memory 92 can further include programs / utilities 925 having a set of (at least one) program modules 924, such as an operating system, one or more application programs, other program modules, and program data, each of which or a combination of which can include the implementation of a network environment.
[0088] The processor 91 performs various function applications and data processing by running the computer program stored in the memory 92, such as the turbine blade tip heat exchange calculation method of the embodiment 1 of the present application.
[0089] The electronic device 90 can also communicate with one or more external devices 94 such as a keyboard or a pointing device, among others. This communication can occur via Input / Output (I / O) interface 95. Still yet, the model generation device 90 can communicate with one or more networks (such as a local area network (LAN), a wide area network (WAN), and / or the public network, such as the Internet) via network adapter 96. As depicted, network adapter 96 communicates with the other components of the model generation device 90 via bus 93. It should be appreciated that although not shown, other hardware and / or software modules could be used in conjunction with the model generation device 90. Such as, but not limited to, microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data archival storage systems, etc.
[0090] It should be noted that although several units / modules or sub-units / modules of an electronic device are mentioned in the foregoing detailed description, such a division is merely exemplary and not mandatory. Indeed, according to an embodiment of the application, the features and functionalities of two or more units / modules described above can be embodied in one unit / module. Conversely, the features and functionalities of one unit / module described above can be further divided into units / modules embodied by several units / modules.
[0091] The embodiment also provides a computer readable storage medium, having stored thereon a computer program, which when executed by a processor, causes the processor to perform the steps of the turbine blade tip heat exchange calculation method as described above.
[0092] More specifically, the readable storage medium can include, but is not limited to, a portable disc, a hard disk, a random access memory, a read-only memory, an erasable programmable read-only memory, an optical storage device, a magnetic storage device, or any suitable combination of the above.
[0093] In a possible implementation, the application can also be implemented in the form of a program product, which includes program codes for causing a terminal device to perform the steps of the turbine blade tip heat exchange calculation method as described above when the program product is run on the terminal device.
[0094] More specifically, the program codes for executing the application can be written in any combination of one or more programming languages, and can be executed entirely on the user device, partly on the user device and partly on a remote device, or entirely on a remote device, as a stand-alone software package, or partly on the user device and partly on a remote device.
[0095] Although the specific embodiments of the present application have been described above, it is understood by those skilled in the art that the present application is only illustrated by way of example, and the scope of protection of the present application is defined by the appended claims. Those skilled in the art can make various changes or modifications to the embodiments without departing from the principles and essence of the present application, and such changes and modifications fall within the scope of protection of the present application.
Claims
1. A method for calculating heat transfer at the tip of a turbine blade, characterized in that, include: The tip region of the turbine blades is divided into several heat exchange zones; Based on the defined heat exchange regions, a tip flow network diagram is constructed at the tip of the turbine blade. Based on the blade tip flow network diagram, generate the blade tip flow heat transfer calculation input file; as well as, Based on the input file for tip flow heat transfer calculation, run a one-dimensional pipe network flow heat transfer calculation program to extract the tip flow heat transfer calculation results; The step of dividing the turbine blade tip region into several heat exchange regions includes: The blade tip and blade base edge of the turbine blade are divided into several segments of equal arc length according to the arc length. Several virtual lines are formed by connecting the endpoints of each arc length on the leaf tip, leaf base, and leaf back edge. The turbine blade tip region is divided into several heat exchange regions based on the aforementioned virtual connections; In the step of constructing the tip flow network diagram of the turbine blade tip, Each heat exchange region of the blade tip flow network diagram includes at least one axial flow heat exchange tube element, at least two circumferential flow heat exchange tube elements, at least one circumferential flow inlet, and at least one circumferential flow outlet. The blade tip flow network diagram also includes at least one axial flow inlet and at least one axial flow outlet. The blade tip axial flow enters from the at least one axial flow inlet, flows through all the axial flow heat exchange tube elements, and exits from the at least one axial flow outlet. The blade tip circumferential flow enters from the corresponding circumferential flow inlet, flows through the corresponding at least two circumferential flow heat exchange tube elements, and intersects with the blade tip axial flow between the at least two circumferential flow heat exchange tube elements, and then exits from the corresponding circumferential flow outlet.
2. The method as described in claim 1, characterized in that, The blade tip flow network diagram also includes loss elements for simulating flow pressure loss; The blade tip axial flow enters from the at least one axial flow inlet, flows through the loss element, then flows through all the axial flow heat exchange tube elements respectively, and exits from the at least one axial flow outlet.
3. The method as described in claim 1, characterized in that, In the step of generating the input file for tip flow heat transfer calculation, The boundary conditions section of the input file for the blade tip flow heat transfer calculation includes geometric boundary conditions and aerodynamic boundary conditions. The geometric boundary conditions are used to define the axial flow geometry and circumferential flow geometry at the blade tip. The geometric boundary conditions are also used to define the geometric parameters of the heat exchange tube elements. The aerodynamic boundary conditions are used to define the aerodynamic parameters at the inlet and outlet.
4. The method as described in claim 1, characterized in that, The step of generating the input file for tip flow heat transfer calculation includes: The logical architecture part for generating the blade tip flow heat transfer calculation input file is written according to the input format required by the one-dimensional pipe network flow heat transfer calculation program.
5. The method as described in claim 1, characterized in that, Also includes: The extracted heat transfer calculation results for the blade tip flow include the temperature and heat transfer coefficient of the heat exchange tube element, and the temperature and heat transfer coefficient of the heat exchange tube element are used as the third type of boundary of the heat transfer region.
6. The method according to any one of claims 1 to 5, characterized in that, The turbine blade tip includes at least one of a flat tip, a grooved tip, and a small winglet tip.
7. An electronic 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 computer program, it implements the turbine blade tip heat transfer calculation method as described in any one of claims 1-6.
8. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the turbine blade tip heat transfer calculation method as described in any one of claims 1-6.