Method and device for realizing automatic modeling of high-pressure-ratio supersonic turbine

Abstract

The invention relates to an automatic modeling implementation method and device for a high-pressure-ratio supersonic turbine, computer equipment and a storage medium. The method comprises the steps that input parameters used for automatic modeling are obtained, the pitch diameter of the turbine is selected, and the speed ratio, the pressure ratio, the specific speed, the isentropic adiabatic work, the efficiency and the gas flow are calculated and determined according to the input parameters; a conical nozzle structure is selected for modeling design, aerodynamic parameters of a nozzle inlet, a throat and an outlet are calculated, and aerodynamic parameters of a cascade inlet and an outlet are calculated; determining the number of nozzles and blade grids and geometric parameters according to the distribution characteristics of the aerodynamic parameters obtained through calculation; whether the number of the nozzles and the blade grids and the geometric parameters meet preset requirements or not is judged; and if the preset requirements are met, three-dimensional modeling of the turbine is carried out according to the number of the nozzles and the blade grids and the geometric parameters. According to the method, automatic modeling of the high-pressure-ratio supersonic turbine can be achieved by inputting specific parameters.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine engines, and in particular to a method, device, computer equipment and storage medium for realizing automatic modeling of a high-pressure ratio supersonic turbine. Background Art

[0002] Liquid rocket engines refer to liquid propellant rocket engines, that is, chemical rocket propulsion systems that use liquid chemicals as energy and working fluids. Among them, open-cycle liquid rocket engines are widely used in the field of aerospace transportation. The total temperature of the gas turbine inlet of its core component is 1000-1200K, the pressure ratio is 20-50, and the speed is 10000-30000r / min. The high-temperature gas reaches supersonic speed after being accelerated by the nozzle. Its turbine design has obvious characteristics such as small aspect ratio, large turning angle, high pressure ratio, and high speed. Because the aspect ratio of the turbine blades is relatively small, secondary flows such as horseshoe vortex and channel vortex are significant, and the gas reaches supersonic speed at the outlet of the nozzle blades, and the flow inside the turbine is complex, which brings great difficulty and challenges to the design of such turbines.

[0003] Summary of the invention (same as claims)

[0004] Based on this, it is necessary to provide a method, device, computer equipment and storage medium for realizing automated modeling of a high-pressure ratio supersonic turbine in response to the above-mentioned technical problems.

[0005] A method for realizing automatic modeling of a high pressure ratio supersonic turbine, the method comprising:

[0006] Obtaining input parameters for automated modeling, the input parameters including turbine power, rotation speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant and fuel gas adiabatic index, selecting turbine mid-diameter, and calculating and determining speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency and fuel gas flow rate according to the input parameters;

[0007] Select the conical nozzle structure for modeling and design, calculate the aerodynamic parameters of the nozzle inlet, throat and outlet, and calculate the aerodynamic parameters of the cascade inlet and outlet;

[0008] Determine the number and geometric parameters of nozzles and cascades according to the distribution characteristics of the calculated aerodynamic parameters;

[0009] Determine whether the number and geometric parameters of nozzles and cascades meet the preset requirements;

[0010] If the preset requirements are met, three-dimensional modeling of the turbine is performed according to the number and geometric parameters of the nozzles and blade cascades.

[0011] In one embodiment, after the step of performing three-dimensional modeling of the turbine according to the number and geometric parameters of the nozzles and blade cascades if the preset requirements are met, the step further includes:

[0012] Conduct aerodynamic 3D simulation and performance analysis on the modeled turbine;

[0013] Determine whether the aerodynamic performance of the turbine meets the requirements and whether the strength and vibration characteristics meet the requirements.

[0014] In one embodiment, the step of calculating the aerodynamic parameters of the nozzle inlet, throat and outlet and calculating the aerodynamic parameters of the cascade inlet and outlet further includes:

[0015] The temperature, pressure, density, velocity and airflow angle of the nozzle inlet, nozzle throat and nozzle outlet are calculated respectively, and the temperature, pressure, density, velocity and airflow angle of the blade inlet and blade outlet are calculated respectively.

[0016] In one embodiment, the step of determining the number and geometric parameters of nozzles and blade cascades according to the calculated distribution characteristics of aerodynamic parameters further includes:

[0017] The geometric parameters of the nozzle include inlet diameter, contraction angle of contraction section, throat diameter, throat length, outlet diameter, expansion angle of expansion section and outlet angle;

[0018] The geometric parameters of the blade cascade include blade cascade height, blade cascade inlet installation angle and blade cascade outlet installation angle.

[0019] In one embodiment, the step of determining whether the number and geometric parameters of the nozzles and blade cascades meet the preset requirements further includes:

[0020] It is determined whether the blade cascade height is within a preset threshold range and whether the turbine part air intake is within a preset threshold range. If the requirements are not met, the number and geometric parameters of the nozzle and blade cascade are re-determined.

[0021] In one embodiment, the step of determining whether the aerodynamic performance of the turbine meets the requirements and determining whether the intensity vibration characteristics meet the requirements further includes:

[0022] The judgment condition of turbine aerodynamic performance is η T ≥η TS , and N T ≥N TS , and q mT ≤q mTS ;

[0023] If it is not satisfied, analyze the gas velocity vector distribution characteristics of the turbine cascade and redesign it;

[0024] Among them, ηT is the actual value of turbine efficiency, N T is the actual value of turbine power, q mT is the actual value of gas flow, η TS is the required value of turbine efficiency, N TS is the turbine power requirement, q mTS is the required gas flow rate.

[0025] In one embodiment, the step of determining whether the aerodynamic performance of the turbine meets the requirements and determining whether the intensity vibration characteristics meet the requirements further includes:

[0026] The judgment condition of the intensity vibration characteristic is ψ σ ≥ψ σMin , and (f n -nf basic ) / nf basic ≥γ Min ;

[0027] If not, redesign the three-dimensional model of the turbine housing and turbine disk;

[0028] Among them, ψ σ is the actual value of the strength safety factor of the turbine component, ψ σMin is the minimum allowable threshold of the turbine component strength safety factor, f n is the nth order natural frequency of the turbine disk, n is the natural order, f basic is the fundamental frequency of turbine rotation, γ Min It is the minimum allowable threshold of turbine disk vibration avoidance rate.

[0029] An automated modeling implementation device for a high-pressure ratio supersonic turbine, the device comprising:

[0030] A parameter acquisition module, wherein the parameter acquisition module is used to acquire input parameters for automatic modeling, wherein the input parameters include turbine power, rotation speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant and fuel gas adiabatic index, and the turbine mid-diameter is selected to calculate and determine the speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency and fuel gas flow rate according to the input parameters;

[0031] A calculation module, wherein the calculation module is used to select a conical nozzle structure for modeling and design, calculate aerodynamic parameters of the nozzle inlet, throat and outlet, and calculate aerodynamic parameters of the blade inlet and outlet; determine the number and geometric parameters of the nozzle and the blade according to the distribution characteristics of the calculated aerodynamic parameters;

[0032] A judgment module, the judgment module is used to judge whether the number and geometric parameters of the nozzles and the cascades meet the preset requirements;

[0033] A modeling module is used to perform three-dimensional modeling of the turbine according to the number and geometric parameters of the nozzles and blade grids if preset requirements are met.

[0034] A computer device comprises a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of any one of the above methods when executing the computer program.

[0035] A computer-readable storage medium stores a computer program, wherein the computer program implements the steps of any one of the above methods when executed by a processor.

[0036] The above-mentioned method, device, computer equipment and storage medium for realizing the automated modeling of the high-pressure ratio supersonic turbine, by obtaining input parameters for automated modeling, the input parameters include turbine power, speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant and fuel gas adiabatic index, selecting the turbine mid-diameter, calculating and determining the speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency and fuel gas flow rate according to the input parameters; selecting a conical nozzle structure for modeling design, calculating the aerodynamic parameters of the nozzle inlet, throat and outlet, and calculating the aerodynamic parameters of the blade inlet and outlet; determining the number and geometric parameters of the nozzle and blade according to the distribution characteristics of the calculated aerodynamic parameters; judging whether the number and geometric parameters of the nozzle and blade meet the preset requirements; if the preset requirements are met, three-dimensional modeling of the turbine is performed according to the number and geometric parameters of the nozzle and blade. The present invention can realize the automated modeling of the high-pressure ratio supersonic turbine by inputting specific parameters, and after completion, the performance evaluation of the model can be performed to ensure that the model meets the specific aerodynamic performance. The scheme is suitable for the design and evaluation process of the high-pressure ratio supersonic turbine of the liquid rocket engine, as well as the forward research and development design of the liquid rocket engine turbine, and has broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 A schematic flow chart of a method for implementing automated modeling of a high-pressure ratio supersonic turbine in one embodiment;

[0038] Figure 2 A schematic flow chart of a method for realizing automatic modeling of a high-pressure ratio supersonic turbine in another embodiment;

[0039] Figure 3 A schematic flow chart of a method for realizing automated modeling of a high-pressure ratio supersonic turbine in yet another embodiment;

[0040] Figure 4 A schematic diagram of a gas velocity vector distribution of a turbine cascade after modeling in one embodiment;

[0041] Figure 5A structural block diagram of an apparatus for realizing automated modeling of a high-pressure ratio supersonic turbine in one embodiment;

[0042] Figure 6 A structural block diagram of an apparatus for realizing automatic modeling of a high-pressure ratio supersonic turbine in another embodiment;

[0043] Figure 7 FIG. 4 is a diagram showing the internal structure of a computer device in one embodiment. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solution and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0045] In one embodiment, Figure 1 As shown, a method for realizing automatic modeling of a high pressure ratio supersonic turbine is provided, the method comprising:

[0046] Step 102, obtaining input parameters for automatic modeling, the input parameters including turbine power, speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant and fuel gas adiabatic index, selecting turbine mid-diameter, and calculating and determining speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency and fuel gas flow rate according to the input parameters;

[0047] Step 104, selecting a conical nozzle structure for modeling and design, calculating aerodynamic parameters of the nozzle inlet, throat and outlet, and calculating aerodynamic parameters of the cascade inlet and outlet;

[0048] Step 106, determining the number and geometric parameters of the nozzles and blade cascades according to the calculated distribution characteristics of the aerodynamic parameters;

[0049] Step 108, determining whether the number and geometric parameters of the nozzles and cascades meet preset requirements;

[0050] Step 110: If the preset requirements are met, three-dimensional modeling of the turbine is performed according to the number and geometric parameters of the nozzles and blade cascades.

[0051] In this embodiment, a method for realizing automatic modeling of a high-pressure ratio supersonic turbine is provided, taking a single-stage turbine of a liquid rocket engine as an example, and the specific description is as follows:

[0052] Firstly, using the input parameters such as turbine power, speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant, fuel gas adiabatic index, etc., the turbine mid-diameter is selected, and the speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency, and fuel gas flow rate are calculated and determined.

[0053] Next, a conical nozzle structure is selected to calculate the aerodynamic parameters such as temperature, pressure, density, velocity, airflow angle, etc. at the nozzle inlet, throat and outlet, and the aerodynamic parameters such as temperature, pressure, density, velocity, airflow angle, etc. at the moving blade inlet and outlet.

[0054] Then, according to the distribution characteristics of aerodynamic parameters, the number of nozzles and inlet diameter, contraction angle of the contraction section, throat diameter, throat length, outlet diameter, expansion angle of the expansion section, outlet angle and other geometric parameters are determined, as well as the number and blade height of the moving blades, inlet installation angle, outlet installation angle and other geometric parameters.

[0055] In one of the embodiments, the step of determining whether the number and geometric parameters of nozzles and blade cascades meet preset requirements further includes: determining whether the blade cascade height is within a preset threshold range and determining whether the air intake of the turbine part is within a preset threshold range. If the requirements are not met, the number and geometric parameters of nozzles and blade cascades are re-determined.

[0056] Specifically, the method for judging whether the nozzle and blade cascade meet the requirements is as follows: If the nozzle throat diameter and blade cascade height are too small, h can be used. r1 <h r1Min Judging from the measurement, it will lead to excessive turbine secondary flow loss and a significant decrease in turbine efficiency; if the nozzle throat diameter and blade cascade height are too large, the number of nozzles will be reduced and the turbine air intake will be less than the allowable threshold ε<ε Min , the turbine intake loss is too large, and the turbine efficiency drops significantly. If the nozzle and blade grid do not meet the requirements, they should be redesigned. r1 , ε are the actual values ​​of the blade cascade height and partial air intake, h r1Min , ε Min They are the minimum allowable thresholds for blade height and partial air intake respectively.

[0057] Finally, according to the number and geometric parameters of nozzles and blade cascades, the turbine inlet pipe, air collecting ring, nozzle, blade cascade and outlet pipe are three-dimensionally modeled.

[0058] In the above embodiment, by obtaining input parameters for automatic modeling, the input parameters include turbine power, speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant and fuel gas adiabatic index, selecting the turbine mid-diameter, calculating and determining the speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency and fuel gas flow rate according to the input parameters; selecting a conical nozzle structure for modeling, calculating the aerodynamic parameters of the nozzle inlet, throat and outlet, and calculating the aerodynamic parameters of the blade inlet and outlet; determining the number and geometric parameters of the nozzle and blade according to the distribution characteristics of the calculated aerodynamic parameters; judging whether the number and geometric parameters of the nozzle and blade meet the preset requirements; if the preset requirements are met, three-dimensional modeling of the turbine is performed according to the number and geometric parameters of the nozzle and blade. The present invention can realize the automatic modeling of a high-pressure ratio supersonic turbine by inputting specific parameters, and after completion, the performance evaluation of the model can be performed to ensure that the model meets specific aerodynamic performance. The scheme is suitable for the design and evaluation process of a high-pressure ratio supersonic turbine of a liquid rocket engine, as well as the forward research and development design of a liquid rocket engine turbine, and has broad application prospects.

[0059] In one embodiment, Figure 2 As shown, a method for realizing automatic modeling of a high-pressure ratio supersonic turbine is provided, wherein after the step of performing three-dimensional modeling of the turbine according to the number and geometric parameters of the nozzles and blade cascades if the preset requirements are met, the method further comprises:

[0060] Step 202, performing aerodynamic three-dimensional simulation and performance analysis on the modeled turbine;

[0061] Step 204, determining whether the aerodynamic performance of the turbine meets the requirements;

[0062] Step 206, determining whether the intensity vibration characteristic meets the requirements.

[0063] In one embodiment, the step of determining whether the aerodynamic performance of the turbine meets the requirements further comprises:

[0064] The judgment condition of turbine aerodynamic performance is η T ≥η TS , and N T ≥N TS , and q mT ≤q mTS ;

[0065] If it is not satisfied, analyze the gas velocity vector distribution characteristics of the turbine cascade and redesign it;

[0066] Among them, η T is the actual value of turbine efficiency, N T is the actual value of turbine power, q mT is the actual value of gas flow, η TSis the required value of turbine efficiency, N TS is the turbine power requirement, q mTS is the required gas flow rate.

[0067] In one embodiment, the step of determining whether the intensity vibration characteristic meets the requirements further includes:

[0068] The judgment condition of the intensity vibration characteristic is ψ σ ≥ψ σMin , and (f n -nf basic ) / nf basic ≥γ Min ;

[0069] If not, redesign the three-dimensional model of the turbine housing and turbine disk;

[0070] Among them, ψ σ is the actual value of the strength safety factor of the turbine component, ψ σMin is the minimum allowable threshold of the turbine component strength safety factor, f n is the nth order natural frequency of the turbine disk, n is the natural order, f basic is the fundamental frequency of turbine rotation, γ Min It is the minimum allowable threshold of turbine disk vibration avoidance rate.

[0071] Specifically, please refer to Figure 3 The flowchart of a method for realizing an automated modeling of a high-pressure ratio supersonic turbine is shown in FIG. Taking a single-stage turbine of a liquid rocket engine as an example, the steps are as follows:

[0072] S1, using the input parameters such as turbine power, speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant, fuel gas adiabatic index, etc., select the turbine mid-diameter, calculate and determine the speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency, and fuel gas flow rate.

[0073] S2, select a conical nozzle structure, calculate the aerodynamic parameters such as temperature, pressure, density, velocity, airflow angle, etc. at the nozzle inlet, throat and outlet, and calculate the aerodynamic parameters such as temperature, pressure, density, velocity, airflow angle, etc. at the moving blade inlet and outlet.

[0074] S3, according to the distribution characteristics of aerodynamic parameters, determine the number of nozzles and inlet diameter, contraction angle of the contraction section, throat diameter, throat length, outlet diameter, expansion angle of the expansion section, outlet angle and other geometric parameters; determine the number and blade height of the moving blade cascade, inlet installation angle, outlet installation angle and other geometric parameters.

[0075] S4, determine whether the nozzle and blade cascade meet the requirements. The nozzle throat diameter and blade cascade height are too small, h can be used r1 <h r1MinJudging from the measurement, it will lead to excessive turbine secondary flow loss and a significant decrease in turbine efficiency; if the nozzle throat diameter and blade cascade height are too large, the number of nozzles will be reduced and the turbine air intake will be less than the allowable threshold ε<ε Min , the turbine intake loss is too large, and the turbine efficiency drops significantly. If the nozzle and blade cascade do not meet the requirements, go to step S3 for redesign; if the nozzle and blade cascade meet the requirements, go to step S5. Where, h r1 , ε are the actual values ​​of the blade cascade height and partial air intake, h r1Min , ε Min They are the minimum allowable thresholds for blade height and partial air intake respectively.

[0076] S5, according to the number and geometric parameters of nozzles and blade cascades, three-dimensional modeling of turbine inlet pipe, air collecting ring, nozzle, blade cascade, outlet pipe is performed. Confirm the three-dimensional modeling of single-stage turbine flow, casing, and turbine disk.

[0077] S6, turbine aerodynamic 3D simulation and performance analysis. Based on the single-stage turbine flow 3D model, finite element volume segmentation is performed, and a three-dimensional aerodynamic simulation of the turbine full flow field is performed. Please refer to Figure 4 shown.

[0078] S7, determine whether the aerodynamic parameters such as turbine efficiency, power, and gas flow meet the requirements. The conditions for meeting the requirements are: η T ≥η TS , and N T ≥N TS , and q mT ≤q mTS If not, analyze the distribution characteristics of the turbine blade gas velocity vector and proceed to step S1 for redesign; if satisfied, proceed to step S8. Where, η T 、N T ,q mT are the actual values ​​of turbine efficiency, power and gas flow, respectively, TS 、N TS ,q mTS are the turbine efficiency, power and gas flow requirement values ​​respectively.

[0079] S8, determine whether the strength vibration characteristics meet the requirements. The conditions for determination are: strength safety factor ψ σ ≥ψ σMin , and (f n -nf basic ) / nf basic ≥γ Min If not, go to step S5 to redesign the single-stage turbine housing and turbine disk three-dimensional model; if satisfied, go to step S9. In the formula, ψ σ , σMin, are the actual value and the minimum permissible threshold of the strength safety factor of the turbine components, respectively. n is the nth order natural frequency of the turbine disk, n is the natural order, f basic is the fundamental frequency of turbine rotation, γ Min It is the minimum allowable threshold of turbine disk vibration avoidance rate.

[0080] S9, aerospace high-pressure ratio supersonic turbine design completed.

[0081] In this embodiment, not only can the automated modeling of a high pressure ratio supersonic turbine be achieved, but the performance of the model can also be evaluated to ensure that the model meets specific aerodynamic performance, thereby ensuring the reliability of the modeling.

[0082] It should be understood that although Figure 1-Figure 4 The steps in the flowchart are shown in sequence as indicated by the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified in this document, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. Moreover, Figure 1-Figure 4 At least part of the steps may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed in turn or alternately with other steps or at least part of the sub-steps or stages of other steps.

[0083] In one embodiment, Figure 5 As shown, a device 500 for realizing automatic modeling of a high pressure ratio supersonic turbine is provided, the device comprising:

[0084] A parameter acquisition module 501 is used to acquire input parameters for automatic modeling, wherein the input parameters include turbine power, rotation speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant and fuel gas adiabatic index, select the turbine mid-diameter, and calculate and determine the speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency and fuel gas flow rate according to the input parameters;

[0085] A calculation module 502, which is used to select a conical nozzle structure for modeling and design, calculate the aerodynamic parameters of the nozzle inlet, throat and outlet, and calculate the aerodynamic parameters of the blade inlet and outlet; determine the number and geometric parameters of the nozzle and the blade according to the distribution characteristics of the calculated aerodynamic parameters;

[0086] A judgment module 503, which is used to judge whether the number and geometric parameters of the nozzles and cascades meet preset requirements;

[0087] The modeling module 504 is used to perform three-dimensional modeling of the turbine according to the number and geometric parameters of the nozzles and blade cascades if the preset requirements are met.

[0088] In one embodiment, Figure 6 As shown, an automatic modeling implementation device 500 for a high pressure ratio supersonic turbine is provided, the device comprising a simulation analysis module 505, the simulation analysis module being used for:

[0089] Conduct aerodynamic 3D simulation and performance analysis on the modeled turbine;

[0090] Determine whether the aerodynamic performance of the turbine meets the requirements and whether the strength and vibration characteristics meet the requirements.

[0091] In one embodiment, the device is also used to:

[0092] The temperature, pressure, density, velocity and airflow angle of the nozzle inlet, nozzle throat and nozzle outlet are calculated respectively, and the temperature, pressure, density, velocity and airflow angle of the blade inlet and blade outlet are calculated respectively.

[0093] In one embodiment, the device is also used to:

[0094] The geometric parameters of the nozzle include inlet diameter, contraction angle of contraction section, throat diameter, throat length, outlet diameter, expansion angle of expansion section and outlet angle;

[0095] The geometric parameters of the blade cascade include blade cascade height, blade cascade inlet installation angle and blade cascade outlet installation angle.

[0096] In one embodiment, the device is also used to:

[0097] It is determined whether the blade cascade height is within a preset threshold range and whether the turbine part air intake is within a preset threshold range. If the requirements are not met, the number and geometric parameters of the nozzle and blade cascade are re-determined.

[0098] In one embodiment, the device is also used to:

[0099] The judgment condition of turbine aerodynamic performance is η T ≥η TS , and N T ≥N TS , and q mT ≤q mTS ;

[0100] If it is not satisfied, analyze the gas velocity vector distribution characteristics of the turbine cascade and redesign it;

[0101] Among them, η T is the actual value of turbine efficiency, N Tis the actual value of turbine power, q mT is the actual value of gas flow, η TS is the required value of turbine efficiency, N TS is the turbine power requirement, q mTS is the required gas flow rate.

[0102] In one embodiment, the device is also used to:

[0103] The judgment condition of the intensity vibration characteristic is ψ σ ≥ψ σMin , and (f n -nf basic ) / nf basic ≥γ Min ;

[0104] If not, redesign the three-dimensional model of the turbine housing and turbine disk;

[0105] Among them, ψ σ is the actual value of the strength safety factor of the turbine component, ψ σMin is the minimum allowable threshold of the turbine component strength safety factor, f n is the nth order natural frequency of the turbine disk, n is the natural order, f basic is the fundamental frequency of turbine rotation, γ Min It is the minimum allowable threshold of turbine disk vibration avoidance rate.

[0106] The specific limitations on the device for realizing the automated modeling of a high-pressure ratio supersonic turbine can be found in the above-mentioned limitations on the method for realizing the automated modeling of a high-pressure ratio supersonic turbine, which will not be repeated here.

[0107] In one embodiment, a computer device is provided, whose internal structure diagram can be as follows: Figure 7 As shown. The computer device includes a processor, a memory and a network interface connected through a device bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating device, a computer program and a database. The internal memory provides an environment for the operation of the operating device and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, an automated modeling implementation method for a high-pressure ratio supersonic turbine is implemented.

[0108] Those skilled in the art will understand that Figure 7The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.

[0109] In one embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, and the processor implements the steps in the above method embodiments when executing the computer program.

[0110] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0111] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in the present application can include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0112] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0113] The above-mentioned embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent of the present application shall be subject to the attached claims.

Claims

1. A method for realizing automatic modeling of a high pressure ratio supersonic turbine, the method comprising: Obtain input parameters for automated modeling, the input parameters including turbine power, rotation speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant and fuel gas adiabatic index, select turbine mid-diameter, and calculate and determine speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency and fuel gas flow rate according to the input parameters; Select the conical nozzle structure for modeling and design, calculate the aerodynamic parameters of the nozzle inlet, throat and outlet, and calculate the aerodynamic parameters of the cascade inlet and outlet; Determine the number and geometric parameters of nozzles and cascades according to the distribution characteristics of the calculated aerodynamic parameters; Determine whether the number and geometric parameters of nozzles and cascades meet the preset requirements; If the preset requirements are met, three-dimensional modeling of the turbine is performed according to the number and geometric parameters of the nozzles and blade cascades.

2. The method for realizing automatic modeling of a high-pressure ratio supersonic turbine according to claim 1, characterized in that: After the step of performing three-dimensional modeling of the turbine according to the number and geometric parameters of the nozzles and blade cascades if the preset requirements are met, the method further includes: Conduct aerodynamic 3D simulation and performance analysis on the modeled turbine; Determine whether the aerodynamic performance of the turbine meets the requirements and whether the strength and vibration characteristics meet the requirements.

3. The method for realizing automatic modeling of a high pressure ratio supersonic turbine according to claim 1, characterized in that: The step of calculating the aerodynamic parameters of the nozzle inlet, throat and outlet and the aerodynamic parameters of the cascade inlet and outlet also includes: The temperature, pressure, density, velocity and airflow angle of the nozzle inlet, nozzle throat and nozzle outlet are calculated respectively, and the temperature, pressure, density, velocity and airflow angle of the blade inlet and blade outlet are calculated respectively.

4. The method for realizing the automated modeling of a high-pressure ratio supersonic turbine according to claim 3, characterized in that: The step of determining the number and geometric parameters of the nozzles and blade cascades according to the distribution characteristics of the calculated aerodynamic parameters also includes: The geometric parameters of the nozzle include inlet diameter, contraction angle of contraction section, throat diameter, throat length, outlet diameter, expansion angle of expansion section and outlet angle; The geometric parameters of the blade cascade include blade cascade height, blade cascade inlet installation angle and blade cascade outlet installation angle.

5. The method for realizing automatic modeling of a high-pressure ratio supersonic turbine according to claim 4, characterized in that: The step of determining whether the number and geometric parameters of the nozzles and blade cascades meet the preset requirements also includes: It is determined whether the blade cascade height is within a preset threshold range and whether the turbine part air intake is within a preset threshold range. If the requirements are not met, the number and geometric parameters of the nozzle and blade cascade are re-determined.

6. The method for realizing automatic modeling of a high pressure ratio supersonic turbine according to claim 2, characterized in that: The step of judging whether the aerodynamic performance of the turbine meets the requirements and judging whether the strength vibration characteristics meet the requirements also includes: The judgment condition of turbine aerodynamic performance is η T ≥η TS , and N T ≥N TS , and q mT ≤q mTS ; If it is not satisfied, analyze the gas velocity vector distribution characteristics of the turbine cascade and redesign it; Among them, η T is the actual value of turbine efficiency, N T is the actual value of turbine power, q mT is the actual value of gas flow, η TS is the required value of turbine efficiency, N TS is the turbine power requirement, q mTS is the required gas flow rate.

7. The method for realizing automatic modeling of a high pressure ratio supersonic turbine according to claim 6, characterized in that: The step of judging whether the aerodynamic performance of the turbine meets the requirements and judging whether the strength vibration characteristics meet the requirements also includes: The judgment condition of the intensity vibration characteristic is ψ σ ≥ψ σMin , and (f n -nf basic ) / nf basic ≥γ Min ; If not, redesign the three-dimensional model of the turbine housing and turbine disk; Among them, ψ σ is the actual value of the strength safety factor of the turbine component, ψ σMin is the minimum allowable threshold of the turbine component strength safety factor, f n is the nth order natural frequency of the turbine disk, n is the natural order, f basic is the fundamental frequency of turbine rotation, γ Min It is the minimum allowable threshold of turbine disk vibration avoidance rate.

8. An automated modeling implementation device for a high-pressure ratio supersonic turbine, characterized in that: The device comprises: A parameter acquisition module, wherein the parameter acquisition module is used to acquire input parameters for automatic modeling, wherein the input parameters include turbine power, rotation speed, inlet temperature, inlet pressure, outlet pressure, fuel gas constant and fuel gas adiabatic index, and the turbine mid-diameter is selected to calculate and determine the speed ratio, pressure ratio, specific speed, isentropic adiabatic work, efficiency and fuel gas flow rate according to the input parameters; A calculation module, wherein the calculation module is used to select a conical nozzle structure for modeling and design, calculate aerodynamic parameters of the nozzle inlet, throat and outlet, and calculate aerodynamic parameters of the blade inlet and outlet; determine the number and geometric parameters of the nozzle and the blade according to the distribution characteristics of the calculated aerodynamic parameters; A judgment module, the judgment module is used to judge whether the number and geometric parameters of the nozzles and the cascades meet the preset requirements; A modeling module is used to perform three-dimensional modeling of the turbine according to the number and geometric parameters of the nozzles and blade grids if preset requirements are met.

9. A computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 7 are implemented.

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