Pseudo-time-step-based turbo-shaft engine whole-machine three-dimensional simulation method and system

Abstract

The application discloses a kind of based on pseudo time step turboshaft engine whole machine three-dimensional simulation method and system, it is first known working condition and is carried out quasi-one-dimensional simulation calculation, obtains the section parameter and component characteristic parameter of each component, after grid division is carried out to turboshaft engine, again known working condition is as input, with the section parameter and component characteristic parameter obtained by quasi-one-dimensional simulation calculation as initial value, three-dimensional simulation calculation is carried out using whole machine three-dimensional grid, and the rotational speed iteration of high pressure rotor and low pressure rotor is carried out by introducing pseudo time step, until the acceleration rate of high pressure rotor and low pressure rotor all meet preset condition, that is, it is balanced with the power of high pressure gas turbine and high pressure compressor, the power of low pressure gas turbine and low pressure compressor is balanced, dynamic solution engine stable state is realized by introducing pseudo time step, the convergence of whole machine three-dimensional simulation calculation is greatly improved, and flow details under adjacent component coupling can be captured, and flow details in component can be captured simultaneously.

Description

Technical Field

[0001] This invention relates to the field of steady-state simulation technology for turboshaft engines, and in particular, to a three-dimensional simulation method and system for turboshaft engines based on pseudo-time steps, electronic equipment, and computer-readable storage medium. Background Technology

[0002] Currently, numerical simulation methods for the steady-state operation of an engine typically begin by obtaining component characteristics through three-dimensional component simulation (or experimentation), and then perform a steady-state simulation of the entire engine based on component characteristics such as inlet and outlet flow rates and the power balance of rotor components (traditionally known as quasi-one-dimensional simulation). For example, for engines like... Figure 1 The turboshaft engine shown (consisting of an intake system, low-pressure compressor, high-pressure compressor, combustion chamber, high-pressure gas turbine, low-pressure gas turbine, power turbine, and exhaust nozzle) is typically first analyzed using 3D simulation or experiments to obtain the characteristics of each component. Then, quasi-one-dimensional simulations are performed based on the flow balance between adjacent components and the power balance between the compressor and gas turbine on the same shaft. The parameters transferred between adjacent components are average parameters of the cross-sections (such as average total temperature and total pressure). However, in actual engine operation, the parameters at the outlet of each component cross-section are non-uniform. Using average parameters for transfer results in the loss of some information transfer between components, failing to capture the flow details under the coupling of adjacent components in actual operating conditions. Furthermore, since each component is described using its own characteristics, the internal flow details of each component cannot be captured. Summary of the Invention

[0003] This invention provides a method and system for three-dimensional simulation of a turboshaft engine based on pseudo-time step, as well as electronic equipment and computer-readable storage media, to solve the technical problem that existing quasi-one-dimensional simulation calculation methods cannot capture the flow details under the coupling of adjacent components and the flow details inside each component.

[0004] According to one aspect of the present invention, a method for three-dimensional simulation of a turboshaft engine based on pseudo-time step is provided, comprising the following:

[0005] Based on the known operating conditions of the turboshaft engine, a quasi-one-dimensional simulation calculation of the engine is performed to obtain the cross-sectional parameters and characteristic parameters of each component.

[0006] The turboshaft engine is meshed to obtain the overall three-dimensional mesh.

[0007] Using known working conditions as input conditions and cross-sectional parameters and component characteristic parameters obtained from quasi-one-dimensional simulation calculations as initial values, the whole machine three-dimensional simulation calculation is performed based on the whole machine three-dimensional mesh, and pseudo-time steps are introduced to iterate the speed of the high-pressure and low-pressure rotors until the acceleration rates of the high-pressure and low-pressure rotors meet the preset conditions.

[0008] Furthermore, after obtaining the three-dimensional mesh of the whole machine, the whole machine is divided into a first calculation unit consisting of an intake device, a low-pressure compressor, a high-pressure compressor, a combustion chamber, and a high-pressure gas turbine inlet guide, and a second calculation unit consisting of a high-pressure gas turbine moving blade, a low-pressure gas turbine inlet guide, a low-pressure gas turbine moving blade, a power turbine, and an exhaust nozzle.

[0009] Furthermore, the process of the whole machine three-dimensional simulation calculation is as follows:

[0010] Using known working conditions as input conditions, and taking the low-pressure compressor speed, high-pressure compressor speed, and high-pressure gas turbine inlet guide outlet pressure obtained from quasi-one-dimensional simulation calculations as initial values, three-dimensional simulation calculations are carried out based on the first calculation unit to obtain the low-pressure compressor power, high-pressure compressor power, high-pressure gas turbine inlet guide outlet total temperature / outlet total pressure / outlet flow rate, and the three-dimensional flow field of the first calculation unit.

[0011] Using the total temperature and pressure at the outlet of the high-pressure gas turbine inlet guide vane, the pressure at the outlet of the tail nozzle, and the speed of the power turbine as input conditions, and the speeds of the low-pressure gas turbine and the high-pressure gas turbine obtained from quasi-one-dimensional simulation calculations as initial values, three-dimensional simulation calculations are carried out based on the second calculation unit to obtain the inlet flow rate of the high-pressure turbine moving blade, the power of the high-pressure turbine, the power of the low-pressure turbine, the power of the power turbine, and the three-dimensional flow field of the second calculation unit.

[0012] Determine whether the outlet flow of the high-pressure gas turbine inlet guide vane is balanced with the inlet flow of the high-pressure turbine moving blade. If they are not balanced, adjust the outlet pressure of the high-pressure gas turbine inlet guide vane to balance them.

[0013] The dynamic equations of the high-pressure and low-pressure rotors are constructed to solve for their acceleration rates, and a pseudo-time step is introduced to iteratively update the rotational speeds of the high-pressure and low-pressure rotors.

[0014] Repeat the above steps until the acceleration rates of both the high-pressure and low-pressure rotors are less than the preset threshold, at which point the three-dimensional simulation calculation of the whole machine will end.

[0015] Furthermore, the outlet pressure of the high-pressure gas turbine inlet guide vane is adjusted based on the following formula:

[0016]

[0017] in, and Wa represents the outlet pressure of the high-pressure gas turbine inlet guide vane after the nth and (n+1)th updates, respectively. HT Wa represents the inlet flow rate of the high-pressure turbine blades. 41 ω represents the outlet flow rate of the high-pressure gas turbine inlet guide vane, and ω represents the relaxation factor.

[0018] Furthermore, the dynamic equations of the high-pressure and low-pressure rotors are as follows:

[0019]

[0020] Among them, J L and J H Let n represent the moments of inertia of the low-pressure rotor and the high-pressure rotor, respectively. L and n H These represent the rotational speeds of the low-pressure rotor and the high-pressure rotor, respectively. and L represents the acceleration rates of the low-pressure rotor and the high-pressure rotor, respectively. LT L represents the power of a low-pressure gas turbine. HT L represents the power of a high-pressure gas turbine. LC Indicates the power of the low-pressure compressor, L HC This indicates the power of the high-pressure compressor.

[0021] Furthermore, the rotational speeds of the high- and low-pressure rotors are updated based on the following formula:

[0022]

[0023] in, and Let these represent the low-pressure compressor speeds at time t and (t+Δt), respectively. and Let represent the high-pressure compressor speed at time t and (t+Δt), respectively, and Δt represent the pseudo-time step.

[0024] Furthermore, the known operating conditions include flight altitude, Mach number, combustion chamber fuel flow rate, power turbine physical speed, atmospheric temperature, and atmospheric pressure.

[0025] In addition, the present invention also provides a three-dimensional simulation system for a turboshaft engine based on pseudo-time step, which employs the method described above, including:

[0026] The one-dimensional simulation module is used to perform quasi-one-dimensional simulation calculations of the turboshaft engine based on the known operating conditions of the engine, and to obtain the cross-sectional parameters and characteristic parameters of each component.

[0027] The mesh generation module is used to generate a three-dimensional mesh for the turboshaft engine.

[0028] The 3D simulation module is used to perform 3D simulation calculations of the whole machine based on the 3D mesh of the whole machine, using known working conditions as input conditions and cross-sectional parameters and component feature parameters obtained from quasi-1D simulation calculations as initial values. It also introduces pseudo-time steps to iterate the rotational speeds of the high-pressure and low-pressure rotors until the acceleration rates of the high-pressure and low-pressure rotors both meet the preset conditions.

[0029] In addition, the present invention also provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the method described above by calling the computer program stored in the memory.

[0030] In addition, the present invention also provides a computer-readable storage medium for storing a computer program for performing a three-dimensional simulation of a turboshaft engine based on a pseudo-time step, wherein the computer program executes the steps of the method described above when running on a computer.

[0031] The present invention has the following effects:

[0032] The pseudo-time step-based three-dimensional simulation method for a turboshaft engine of this invention first performs quasi-one-dimensional simulation calculations under known operating conditions to obtain the cross-sectional parameters and component characteristic parameters of each component. After meshing the turboshaft engine, the known operating conditions are used as input, and the cross-sectional parameters and component characteristic parameters obtained from the quasi-one-dimensional simulation calculations are used as initial values. A three-dimensional simulation calculation is then performed using the entire engine's three-dimensional mesh, and a pseudo-time step is introduced to iterate the rotational speeds of the high-pressure and low-pressure rotors until the acceleration rates of both the high-pressure and low-pressure rotors meet preset conditions, representing power balance between the high-pressure gas turbine and high-pressure compressor, and between the low-pressure gas turbine and low-pressure compressor. By introducing a pseudo-time step, the engine's stable state is dynamically solved, significantly improving the convergence of the three-dimensional simulation calculation. Furthermore, because iterative calculations are performed using three-dimensional simulation, the three-dimensional flow field of each component can be obtained, thus capturing the flow details under the coupling of adjacent components, as well as the flow details within the components.

[0033] In addition, the pseudo-time step-based three-dimensional simulation system for the entire turboshaft engine of the present invention also has the above-mentioned advantages.

[0034] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0035] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0036] Figure 1 This is a schematic diagram of the structure of a turboshaft engine according to a preferred embodiment of the present invention.

[0037] Figure 2 This is a flowchart illustrating a preferred embodiment of the three-dimensional simulation method for a turboshaft engine based on pseudo-time steps according to the present invention.

[0038] Figure 3 This is a schematic diagram of the logic flow for performing a steady-state three-dimensional simulation of a turboshaft engine in a preferred embodiment of the present invention.

[0039] Figure 4 yes Figure 2 A schematic diagram of the sub-process of step S3.

[0040] Figure 5 This is a schematic diagram of the module structure of a three-dimensional simulation system for a turboshaft engine based on pseudo-time step, according to another embodiment of the present invention. Detailed Implementation

[0041] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0042] Understandable, such as Figure 2 and Figure 3 As shown, a preferred embodiment of the present invention provides a three-dimensional simulation method for a turboshaft engine based on pseudo-time steps, including the following:

[0043] Step S1: Perform quasi-one-dimensional simulation calculations of the engine based on the known operating conditions of the turboshaft engine to obtain the cross-sectional parameters and characteristic parameters of each component;

[0044] Step S2: Mesh the turboshaft engine to obtain the overall three-dimensional mesh;

[0045] Step S3: Using known working conditions as input conditions and cross-sectional parameters and component characteristic parameters obtained from quasi-one-dimensional simulation calculations as initial values, perform three-dimensional simulation calculations of the whole machine based on the whole machine's three-dimensional mesh, and introduce pseudo-time steps to iterate the rotational speeds of the high-pressure and low-pressure rotors until the acceleration rates of the high-pressure and low-pressure rotors both meet the preset conditions.

[0046] It is understandable that the pseudo-time step-based three-dimensional simulation method for the entire turboshaft engine in this embodiment first performs quasi-one-dimensional simulation calculations under known operating conditions to obtain the cross-sectional parameters and component characteristic parameters of each component. After meshing the turboshaft engine, the known operating conditions are used as input, and the cross-sectional parameters and component characteristic parameters obtained from the quasi-one-dimensional simulation calculations are used as initial values. Three-dimensional simulation calculations are then performed using the entire engine's three-dimensional mesh, and a pseudo-time step is introduced to iterate the rotational speeds of the high-pressure and low-pressure rotors until the acceleration rates of both the high-pressure and low-pressure rotors meet preset conditions, representing power balance between the high-pressure gas turbine and the high-pressure compressor, and between the low-pressure gas turbine and the low-pressure compressor. By introducing a pseudo-time step, the engine's stable state is dynamically solved, greatly improving the convergence of the entire engine's three-dimensional simulation calculations. Furthermore, since iterative calculations are performed using three-dimensional simulation, the three-dimensional flow field of each component can be obtained, thereby capturing the flow details under the coupling of adjacent components, as well as the flow details within the components.

[0047] It is understood that in step S1, existing quasi-one-dimensional simulation methods for turboshaft engines are used to perform calculations based on known operating conditions to obtain the cross-sectional parameters and characteristic parameters of each component of the turboshaft engine. The known operating conditions include flight altitude, Mach number, atmospheric temperature T0, atmospheric pressure P0, combustion chamber fuel flow rate Wfb, and the physical speed N of the power turbine. p In addition, the cross-sectional parameters of each component include total temperature, total pressure, and flow rate, while the component characteristic parameters include the low-pressure compressor speed n. L Low-pressure compressor pressure ratio, high-pressure compressor pressure ratio, high-pressure compressor speed n H High-pressure gas turbine inlet guide valve outlet pressure P 41 High-pressure turbine expansion ratio, low-pressure turbine expansion ratio, power turbine expansion ratio, etc.

[0048] It is understood that in step S2, the three-dimensional mesh of the entire turboshaft engine is generated in the commercial software ICEM, and the three-dimensional meshes of each component are also extracted, thus obtaining the three-dimensional mesh of the entire engine and the three-dimensional meshes of each component, providing a model basis for subsequent three-dimensional simulation calculations of the entire engine. Optionally, after obtaining the three-dimensional mesh of the entire engine, the engine is divided into a first calculation unit consisting of an intake device, a low-pressure compressor, a high-pressure compressor, a combustion chamber, and a high-pressure gas turbine inlet guide vane, and a second calculation unit consisting of a high-pressure gas turbine rotor blade, a low-pressure gas turbine inlet guide vane, a low-pressure gas turbine rotor blade, a power turbine, and an exhaust nozzle. Subsequent three-dimensional simulation calculations are performed based on the first and second calculation units.

[0049] Understandable, such as Figure 4 As shown, in step S3, the process of the whole machine three-dimensional simulation calculation is as follows:

[0050] Step S31: Using known working conditions as input conditions, and using the low-pressure compressor speed, high-pressure compressor speed, and high-pressure gas turbine inlet guide outlet pressure obtained from quasi-one-dimensional simulation calculations as initial values, perform three-dimensional simulation calculations based on the first calculation unit to obtain the low-pressure compressor power, high-pressure compressor power, high-pressure gas turbine inlet guide outlet total temperature / outlet total pressure / outlet flow rate, and the three-dimensional flow field of the first calculation unit.

[0051] Step S32: Using the total temperature and pressure at the outlet of the high-pressure gas turbine inlet guide vane, the pressure at the outlet of the tail nozzle, and the speed of the power turbine as input conditions, and using the speed of the low-pressure gas turbine and the speed of the high-pressure gas turbine obtained from the quasi-one-dimensional simulation calculation as initial values, a three-dimensional simulation calculation is carried out based on the second calculation unit to obtain the inlet flow rate of the high-pressure turbine moving blade, the power of the high-pressure turbine, the power of the low-pressure turbine, the power of the power turbine, and the three-dimensional flow field of the second calculation unit.

[0052] Step S33: Determine whether the outlet flow of the high-pressure gas turbine inlet guide vane is balanced with the inlet flow of the high-pressure turbine moving blade. If they are not balanced, adjust the outlet pressure of the high-pressure gas turbine inlet guide vane to make them balanced.

[0053] Step S34: Construct the dynamic equations of the high-pressure and low-pressure rotors to solve for the acceleration rates of the high-pressure and low-pressure rotors, and introduce a pseudo-time step to iteratively update the rotational speeds of the high-pressure and low-pressure rotors;

[0054] Step S35: Repeat steps S31 to S34 until the acceleration rates of both the high-pressure and low-pressure rotors are less than the preset threshold, at which point the three-dimensional simulation calculation of the whole machine ends.

[0055] Specifically, the known operating conditions are first used as input conditions, and the low-pressure compressor speed n is obtained from quasi-one-dimensional simulation calculation. L High-pressure compressor speed n H High-pressure gas turbine inlet guide valve outlet pressure P 41 Using the initial value as a reference, a three-dimensional simulation calculation is performed based on the first computing unit to obtain the low-pressure compressor power L. LC High-pressure compressor power (L) HC High-pressure gas turbine inlet guide vane outlet total temperature T t41 / Total pressure P t41 / Export Flow Wa 41 And the three-dimensional flow field of the first calculation unit. The specific three-dimensional simulation calculation process is existing technology. For example, by loading calculation conditions (atmospheric temperature T0, atmospheric pressure P0, physical speed of high / low pressure compressors, combustion chamber fuel flow, etc.) in commercial software CFX to conduct three-dimensional simulation calculations, temperature and pressure data at any point in the first calculation unit can be obtained. For the high-pressure gas turbine inlet guide vane outlet, the total outlet temperature T is obtained by averaging the temperature, pressure, and velocity at various points on the outlet cross-section. t41 / Total pressure P t41 / Export Flow Wa 41 Power can be calculated from the total temperature and flow rate at the inlet and outlet of the component.

[0056] Then, the total outlet temperature T of the high-pressure gas turbine inlet guide vane is obtained. t41 / Total pressure P t41 Tail nozzle outlet pressure and power turbine speed N p As input conditions for the calculation, the exhaust nozzle outlet pressure is equal to the atmospheric pressure P0, and the low-pressure gas turbine speed and high-pressure gas turbine speed obtained from quasi-one-dimensional simulation calculation are used as initial values, where the low-pressure gas turbine speed is equal to the low-pressure compressor speed n. L The high-pressure gas turbine speed is equal to the high-pressure compressor speed n. HBased on the second computing unit, a three-dimensional simulation calculation was performed to obtain the inlet flow rate Wa of the high-pressure turbine blade. HT High-pressure turbine power L HT Low-pressure turbine power L LT Power Turbine L PT The three-dimensional flow field of the second calculation unit. The specific three-dimensional simulation calculation process is the same as step S31 and is also existing technology, so it will not be described again here.

[0057] Based on the constraints of flow balance, the outlet flow rate Wa of the high-pressure gas turbine inlet guide vane must be satisfied. 41 With the inlet flow rate Wa of the high-pressure turbine blade HT Balance, and according to the working principle of a turboshaft engine, when the inlet flow rate Wa of the high-pressure turbine moving blades... HT The outlet flow rate Wa of the high-pressure gas turbine inlet guide vane is greater than that of the gas turbine inlet guide vane. 41 This indicates either insufficient engine turbine capacity or excessive compressor flow. Therefore, when the high-pressure gas turbine inlet guide vane outlet flow rate Wa... 41 When there is an imbalance between the inlet flow rate of the high-pressure turbine moving blades and the pressure of the outlet pressure P of the high-pressure gas turbine inlet guide vane, it can be adjusted. 41 Until the two are balanced. Optionally, the outlet pressure of the high-pressure gas turbine inlet guide vane is adjusted based on the following formula:

[0058]

[0059] in, and Wa represents the outlet pressure of the high-pressure gas turbine inlet guide vane after the nth and (n+1)th updates, respectively. HT Wa represents the inlet flow rate of the high-pressure turbine blades. 41 ω represents the outlet flow rate of the high-pressure gas turbine inlet guide vane, and ω represents the relaxation factor. This invention increases the outlet pressure P of the high-pressure gas turbine inlet guide vane. 41 This improves the flow capacity of the engine turbine while simultaneously reducing the compressor inlet flow, allowing for rapid and precise flow balance. Additionally, each adjustment of the high-pressure gas turbine inlet guide valve outlet pressure P... 41 Then, steps S31 and S32 need to be repeated.

[0060] Then, the dynamic equations for the high-pressure and low-pressure rotors are constructed:

[0061]

[0062] Among them, J L and J H These represent the moments of inertia of the low-pressure rotor and the high-pressure rotor, respectively, determined by the engine's geometric parameters, n. L and nH These represent the rotational speeds of the low-pressure rotor and the high-pressure rotor, respectively. and L represents the acceleration rates of the low-pressure rotor and the high-pressure rotor, respectively. LT L represents the power of a low-pressure gas turbine. HT L represents the power of a high-pressure gas turbine. LC Indicates the power of the low-pressure compressor, L HC This represents the power of the high-pressure compressor. A pseudo-time step Δt is introduced to achieve iterative speed updates, specifically based on the following formula for updating the speeds of the high- and low-pressure rotors:

[0063]

[0064] in, and Let these represent the low-pressure compressor speeds at time t and (t+Δt), respectively. and Let represent the high-pressure compressor speed at time t and (t+Δt), respectively, and Δt represent the pseudo-time step.

[0065] Repeat steps S31 to S34 continuously until... Where ε is a small positive integer, the specific value can be selected according to actual needs, which represents the no acceleration or deceleration of the high and low rotors, and also represents the power balance between the high-pressure gas turbine and the high-pressure compressor, and the power balance between the low-pressure gas turbine and the low-pressure compressor. Thus, by introducing a pseudo-time step for speed iteration, the dynamic solution of the engine's stable state is realized, and the three-dimensional simulation calculation can be converged quickly.

[0066] In addition, such as Figure 5 As shown, another embodiment of the present invention also provides a three-dimensional simulation system for a turboshaft engine based on pseudo-time steps, preferably employing the method described above, including:

[0067] The one-dimensional simulation module is used to perform quasi-one-dimensional simulation calculations of the turboshaft engine based on the known operating conditions of the engine, and to obtain the cross-sectional parameters and characteristic parameters of each component.

[0068] The mesh generation module is used to generate a three-dimensional mesh for the turboshaft engine.

[0069] The 3D simulation module is used to perform 3D simulation calculations of the whole machine based on the 3D mesh of the whole machine, using known working conditions as input conditions and cross-sectional parameters and component feature parameters obtained from quasi-1D simulation calculations as initial values. It also introduces pseudo-time steps to iterate the rotational speeds of the high-pressure and low-pressure rotors until the acceleration rates of the high-pressure and low-pressure rotors both meet the preset conditions.

[0070] It is understood that the pseudo-time-step-based three-dimensional simulation system for the entire turboshaft engine in this embodiment first performs quasi-one-dimensional simulation calculations under known operating conditions to obtain the cross-sectional parameters and component characteristic parameters of each component. After meshing the turboshaft engine, the known operating conditions are used as input, and the cross-sectional parameters and component characteristic parameters obtained from the quasi-one-dimensional simulation calculations are used as initial values. Three-dimensional simulation calculations are then performed using the entire engine's three-dimensional mesh, and a pseudo-time step is introduced to iterate the rotational speeds of the high-pressure and low-pressure rotors until the acceleration rates of both the high-pressure and low-pressure rotors meet preset conditions. This indicates that the power balance between the high-pressure gas turbine and the high-pressure compressor, and the power balance between the low-pressure gas turbine and the low-pressure compressor, are achieved. By introducing a pseudo-time step, the engine's stable state is dynamically solved, greatly improving the convergence of the entire engine's three-dimensional simulation calculations. Furthermore, because iterative calculations are performed using three-dimensional simulation, the three-dimensional flow field of each component can be obtained, thereby capturing the flow details under the coupling of adjacent components, as well as the flow details within the components.

[0071] In addition, another embodiment of the present invention provides an electronic device including a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the method described above by calling the computer program stored in the memory.

[0072] In addition, another embodiment of the present invention provides a computer-readable storage medium for storing a computer program for performing a three-dimensional simulation of a turboshaft engine based on a pseudo-time step, wherein the computer program executes the steps of the method described above when running on a computer.

[0073] Common computer-readable storage media include: floppy disks, flexible disks, hard disks, magnetic tapes, any other magnetic media, CD-ROMs, any other optical media, punch cards, paper tape, any other physical media with perforated patterns, random access memory (RAM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), flash erasable programmable read-only memory (FLASH-EPROM), any other memory chips or cartridges, or any other media readable by a computer. Instructions may further be transmitted or received by a transmission medium. The term transmission medium can include any tangible or intangible medium used to store, encode, or carry instructions for machine execution, and includes digital or analog communication signals or intangible media that facilitate communication of such instructions. Transmission media include coaxial cables, copper wires, and optical fibers, which contain conductors for transmitting a bus of computer data signals.

[0074] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

[0075] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of this application can be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0076] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0077] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0078] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0079] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0080] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A three-dimensional simulation method for a turboshaft engine based on pseudo-time step, characterized in that, Includes the following: Based on the known operating conditions of the turboshaft engine, a quasi-one-dimensional simulation calculation of the engine is performed to obtain the cross-sectional parameters and characteristic parameters of each component. The turboshaft engine is meshed to obtain the overall three-dimensional mesh. Using known working conditions as input conditions and cross-sectional parameters and component characteristic parameters obtained from quasi-one-dimensional simulation calculations as initial values, the whole machine three-dimensional simulation calculation is performed based on the whole machine three-dimensional mesh, and pseudo-time steps are introduced to iterate the speed of the high and low pressure rotors until the acceleration rates of the high and low pressure rotors meet the preset conditions. After obtaining the three-dimensional mesh of the whole machine, the whole machine is divided into the first calculation unit consisting of the intake device, low-pressure compressor, high-pressure compressor, combustion chamber, and high-pressure gas turbine inlet guide, and the second calculation unit consisting of high-pressure gas turbine blades, low-pressure gas turbine inlet guide, low-pressure gas turbine blades, power turbine and tail nozzle. The process of the whole machine three-dimensional simulation calculation is as follows: Using known working conditions as input conditions, and taking the low-pressure compressor speed, high-pressure compressor speed, and high-pressure gas turbine inlet guide outlet pressure obtained from quasi-one-dimensional simulation calculations as initial values, three-dimensional simulation calculations are carried out based on the first calculation unit to obtain the low-pressure compressor power, high-pressure compressor power, high-pressure gas turbine inlet guide outlet total temperature / outlet total pressure / outlet flow rate, and the three-dimensional flow field of the first calculation unit. Using the total temperature and pressure at the outlet of the high-pressure gas turbine inlet guide vane, the pressure at the outlet of the tail nozzle, and the speed of the power turbine as input conditions, and the speeds of the low-pressure gas turbine and the high-pressure gas turbine obtained from quasi-one-dimensional simulation calculations as initial values, three-dimensional simulation calculations are carried out based on the second calculation unit to obtain the inlet flow rate of the high-pressure turbine moving blade, the power of the high-pressure turbine, the power of the low-pressure turbine, the power of the power turbine, and the three-dimensional flow field of the second calculation unit. Determine whether the outlet flow of the high-pressure gas turbine inlet guide vane is balanced with the inlet flow of the high-pressure turbine moving blade. If they are not balanced, adjust the outlet pressure of the high-pressure gas turbine inlet guide vane to balance them. The dynamic equations of the high-pressure and low-pressure rotors are constructed to solve for their acceleration rates, and a pseudo-time step is introduced to iteratively update the rotational speeds of the high-pressure and low-pressure rotors. Repeat the above steps until the acceleration rates of both the high-pressure and low-pressure rotors are less than the preset threshold, at which point the three-dimensional simulation calculation of the whole machine will end.

2. The three-dimensional simulation method for a turboshaft engine based on pseudo-time step as described in claim 1, characterized in that, Adjust the outlet pressure of the high-pressure gas turbine inlet guide vane based on the following formula: ； in, and These represent the outlet pressures of the high-pressure gas turbine inlet guide vanes after the nth and (n+1)th updates, respectively. This indicates the inlet flow rate of the high-pressure turbine blades. This indicates the outlet flow rate of the high-pressure gas turbine inlet guide vane. This represents the relaxation factor.

3. The three-dimensional simulation method for a turboshaft engine based on pseudo-time step as described in claim 1, characterized in that, The dynamic equations for the high-pressure and low-pressure rotors are as follows: ； in, and These represent the moments of inertia of the low-pressure rotor and the high-pressure rotor, respectively. and These represent the rotational speeds of the low-pressure rotor and the high-pressure rotor, respectively. and These represent the acceleration rates of the low-pressure rotor and the high-pressure rotor, respectively. Indicates the power of the low-pressure gas turbine. Indicates the power of the high-pressure gas turbine. This indicates the power of the low-pressure compressor. This indicates the power of the high-pressure compressor.

4. The three-dimensional simulation method for a turboshaft engine based on pseudo-time step as described in claim 3, characterized in that, The high- and low-pressure rotor speeds are updated based on the following formula: ； in, and Let these represent the low-pressure compressor speeds at time t and (t+Δt), respectively. and Let these represent the high-pressure compressor speeds at time t and (t+Δt), respectively. This indicates a pseudo-time step.

5. The three-dimensional simulation method for a turboshaft engine based on pseudo-time step as described in any one of claims 1 to 4, characterized in that, The known operating conditions include flight altitude, Mach number, combustion chamber fuel flow rate, power turbine physical speed, atmospheric temperature, and atmospheric pressure.

6. A three-dimensional simulation system for a turboshaft engine based on pseudo-time step, employing the method described in any one of claims 1 to 5, characterized in that, include: The one-dimensional simulation module is used to perform quasi-one-dimensional simulation calculations of the turboshaft engine based on the known operating conditions of the engine, and to obtain the cross-sectional parameters and characteristic parameters of each component. The mesh generation module is used to generate a three-dimensional mesh for the turboshaft engine. The 3D simulation module is used to perform 3D simulation calculations of the whole machine based on the 3D mesh of the whole machine, using known working conditions as input conditions and cross-sectional parameters and component feature parameters obtained from quasi-1D simulation calculations as initial values. It also introduces pseudo-time steps to iterate the rotational speeds of the high-pressure and low-pressure rotors until the acceleration rates of the high-pressure and low-pressure rotors both meet the preset conditions.

7. An electronic device, characterized in that, The method includes a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the method as described in any one of claims 1 to 5 by calling the computer program stored in the memory.

8. A computer-readable storage medium for storing a computer program for performing a three-dimensional simulation of a turboshaft engine based on pseudo-time steps, characterized in that, The computer program, when run on a computer, performs the steps of the method as described in any one of claims 1 to 5.

Images