Variable-cycle wide-area engine turbine design method and system

Abstract

The invention relates to the technical field of engine turbines, and discloses a variable-cycle wide-range engine turbine design method and system.The method comprises the steps that according to preset engine overall performance design requirements, conversion flow, conversion rotating speed and conversion power of multiple different working states are calculated and analyzed; judging whether the conversion flows and the conversion rotating speeds in the different working states meet the equal condition or not; if yes, designing based on a preset conventional turbine design method; if different weight coefficients are not given to the working states, generating design state parameters of the turbine based on the linear weighted sum; according to the design state parameters and the conversion power, at least one of one-dimensional parameter design, two-dimensional parameter design and three-dimensional parameter design of the engine turbine is carried out, so that the engine turbine meets the preset overall performance design requirement of the engine, the efficiency is high in different working states, the flow and power requirements of all working conditions are met, and the working efficiency is improved. And the reliability of the variable cycle engine turbine design method is verified.

Description

Technical Field

[0001] The present invention relates to the technical field of engine turbine design, and in particular to a variable cycle wide range engine turbine design method and system. Background Art

[0002] Variable cycle engines combine the advantages of high and low bypass ratio engines, enabling them to simultaneously meet the demands of high supersonic thrust and low fuel consumption at subsonic speeds. By modifying the geometry, size, or position of certain engine components, variable cycle engines adjust thermodynamic cycle parameters such as compression ratio, turbine inlet temperature, flow rate, speed, and bypass ratio. This redistributes internal engine flow and energy, resulting in an optimized thermodynamic cycle under varying operating conditions and consistent performance across a wide range of flight conditions and operating states.

[0003] Conventional turbine design methods rely on well-defined design states to achieve maximum efficiency, but variable-cycle engine turbines do not have fixed design states. Existing technologies lack methods that can flexibly adapt to the design requirements of variable-cycle engine turbines and cannot adjust design strategies based on varying operating conditions. When faced with the complex operating conditions of variable-cycle engines, the inability to accurately determine the design state results in turbine designs that fail to meet the engine's performance requirements under varying flight conditions and operating states, impacting overall engine performance. Summary of the Invention

[0004] In view of this, the present invention provides a variable cycle wide range engine turbine design method and system, which solves the problem of how to design an engine turbine to meet the performance requirements of the engine under different flight conditions and working states.

[0005] In a first aspect, the present invention provides a method for designing a turbine for a variable cycle wide range engine, comprising:

[0006] Calculate and analyze the converted flow, converted speed and converted power under multiple different working conditions according to the preset overall engine performance design requirements;

[0007] Determine whether the converted flow rates and converted speeds of multiple different working states meet the equality condition;

[0008] If the equal conditions are met, the design is performed based on the preset conventional turbine design method;

[0009] If the equality condition is not met, different weight coefficients are assigned to each working state, and the design state parameters of the turbine are generated based on the linear weighted sum, where the size of each weight coefficient represents the importance of different working states in the multi-objective optimization problem;

[0010] According to the design state parameters and the converted power, at least one of the one-dimensional parameter design, the two-dimensional parameter design and the three-dimensional parameter design of the engine turbine is performed to meet the preset overall performance design requirements of the engine.

[0011] The embodiment of the present invention calculates and analyzes the converted flow, converted speed, and converted power of multiple different operating states, and selects a design method based on the conditions of these parameters, which can better adapt to the complex and changeable working conditions of the variable cycle engine. When the converted flow and converted speed of different operating states meet the equality condition, a preset conventional turbine design method is adopted, and mature design experience is used to improve design efficiency. When the equality condition is not met, the design state parameters are generated by assigning weight coefficients, providing an effective solution to the problem of the unstable design state of the variable cycle engine turbine, so that the designed turbine can have good performance in various operating states, improve the success rate and reliability of the turbine design, and thus improve the overall performance and reliability of the variable cycle engine.

[0012] In an optional embodiment, the preset overall engine performance design requirements include: design parameters corresponding to inlet total pressure, inlet total temperature, flow rate, speed, expansion ratio and efficiency, as well as preset geometric design indicators and corresponding design parameters.

[0013] The embodiments of the present invention provide turbine designers with a clear design direction through specific design parameters, acting like clear navigation coordinates. During the design process, parameters such as inlet total pressure and inlet total temperature can be used to determine the heat and pressure loads the turbine must withstand under different operating conditions. This allows for targeted material selection and design structure selection, facilitating the coordinated optimization of multiple turbine performance indicators, avoiding the omission of important factors during the design process, and ensuring the optimal overall performance of the designed turbine.

[0014] In an optional embodiment, the design state parameters of the variable cycle wide range engine turbine include: flow design state parameters, expansion ratio design state parameters, speed design state parameters, and power design state parameters;

[0015] The weight coefficient is calculated according to the following formula:

[0016]

[0017] Among them, t i is the working time of a certain state, T is the total working time, w i is the fuel flow rate at a certain state, W design is the fuel flow rate at design status.

[0018] The embodiment of the present invention incorporates flow rate, expansion ratio, speed, and power into the design state parameters, comprehensively covering the key factors affecting turbine performance. The flow design state parameter is directly related to the engine's air intake volume, affecting combustion efficiency and work capacity; the expansion ratio design state parameter determines the efficiency of converting thermal energy into mechanical energy; the speed design state parameter affects the turbine's power output and stability; the power design state parameter reflects the turbine's work capacity under different operating conditions. These parameters work together to accurately outline the performance requirements of the turbine under different operating conditions, providing an accurate basis for subsequent design and ensuring that the designed turbine can operate stably and efficiently under various operating conditions; by introducing the working time and fuel flow calculation weight coefficient, it can scientifically reflect the importance of different working states in multi-objective optimization.

[0019] In an optional embodiment, the one-dimensional parameter design includes:

[0020] Meridian flow channel design is carried out with the goal of maximizing efficiency. Expressed as:

[0021]

[0022] Among them, G represents the flow rate, represents the total inlet temperature, Indicates the total inlet pressure, n indicates the speed, Indicates the converted flow rate, represents the converted speed, and Δλ represents the change in the guide vane installation angle.

[0023] The efficiency formula provided by the embodiments of this invention provides clear design direction and quantitative indicators for meridian flow channel design. Based on the parameter relationships in the formula, design variables such as flow channel shape and guide vane installation angle can be adjusted in a targeted manner to achieve maximum efficiency. Furthermore, through the quantitative calculation of efficiency, the advantages and disadvantages of different design solutions can be intuitively evaluated, facilitating comparison and screening during the design process.

[0024] In an optional embodiment, the two-dimensional parameter design includes:

[0025] Using the viscous controllable vortex design method, the inverse problem design of the S2 flow surface is performed based on the design state parameters, and the gradient of the entropy distribution along the radial direction is used to correct the viscosity and secondary flow effects;

[0026] If the design results of the S2 flow surface inverse problem meet the preset engine overall performance design requirements, the variable cycle wide range engine turbine blade shape is designed, and the S1 flow surface calculation analysis is performed to make it meet the preset engine overall performance design requirements.

[0027] The embodiment of the present invention adopts a viscous controllable vortex design method and corrects the viscosity and secondary flow effects based on the gradient of entropy distribution along the radial direction, which can more accurately simulate and process the complex flow conditions inside the turbine. Viscosity and secondary flow will cause energy loss, affecting the efficiency and performance of the turbine. By making targeted corrections to these factors, the flow loss can be effectively reduced and the energy conversion efficiency of the turbine can be improved; after the S2 flow surface inverse problem design meets the requirements, the turbine blade shape design is carried out, and combined with the S1 flow surface calculation and analysis, the turbine blades can be optimized from multiple angles. The S2 flow surface inverse problem design provides a basic framework for blade shape, and the S1 flow surface calculation and analysis evaluates and optimizes the performance of the blade from another dimension. The combination of the two makes the blade shape design more scientific and reasonable, which can better meet the requirements of the engine for airflow, pressure distribution and other aspects under different working conditions, and further improve the performance and reliability of the turbine.

[0028] In an optional embodiment, the performing of three-dimensional parameter design of the engine turbine includes:

[0029] If the turbine blade design meets the preset overall engine performance design requirements, a full three-dimensional design and optimization of the blades will be performed, and aerodynamic performance and flow field structure will be verified using three-dimensional viscosity calculations;

[0030] If the calculation verification result meets the preset engine overall performance design requirements, the design is completed; if it does not meet the requirements, iterative optimization design is performed until the preset engine overall performance design requirements are met.

[0031] The embodiments of this invention utilize three-dimensional viscosity calculations to verify aerodynamic performance and flow field structure, providing a solid guarantee for design reliability. Three-dimensional viscosity calculations can simulate the viscous properties of airflow in actual operation, more realistically reflecting the flow field conditions within the turbine. This calculation can identify potential design issues in advance. Preemptive verification through three-dimensional viscosity calculations allows for timely design adjustments, avoiding failures during actual manufacturing and operation, and improving engine reliability and stability.

[0032] In a second aspect, the present invention provides a variable cycle wide range engine turbine design system, comprising:

[0033] The multi-operating condition parameter conversion module is used to calculate and analyze the converted flow, converted speed and converted power of multiple different operating conditions according to the preset overall engine performance design requirements;

[0034] A condition judgment module is used to judge whether the converted flow rates and converted speeds of multiple different working states meet the equality condition;

[0035] A conventional design module, configured to perform design based on a preset conventional turbine design method if equal conditions are met;

[0036] A design state parameter generation module is used to assign different weight coefficients to each working state if the equality condition is not met, and generate the design state parameters of the turbine based on the linear weighted sum, where the size of each weight coefficient represents the importance of different working states in the multi-objective optimization problem;

[0037] The geometric design module is used to perform at least one of one-dimensional parameter design, two-dimensional parameter design and three-dimensional parameter design of the engine turbine according to the design state parameters and the converted power, so that it meets the preset overall performance design requirements of the engine.

[0038] In a third aspect, the present invention provides a computer device comprising: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, and the processor executing the variable cycle wide range engine turbine design method of the first aspect or any corresponding embodiment thereof by executing the computer instructions.

[0039] In a fourth aspect, the present invention provides a computer-readable storage medium having computer instructions stored thereon, the computer instructions being used to enable a computer to execute the variable cycle wide range engine turbine design method of the above-mentioned first aspect or any corresponding embodiment thereof.

[0040] In a fifth aspect, the present invention provides a computer program product comprising computer instructions for causing a computer to execute the variable cycle wide range engine turbine design method of the first aspect or any corresponding embodiment thereof. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0042] Figure 1 1 is a flow chart of a variable cycle wide range engine turbine design method according to an embodiment of the present invention;

[0043] Figure 2 1 is a flow chart of a specific example of a variable cycle wide range engine turbine design method according to an embodiment of the present invention;

[0044] Figure 3 is a structural block diagram of a variable cycle wide range engine turbine design system according to an embodiment of the present invention;

[0045] Figure 4Schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0046] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0047] For variable cycle engine turbines, due to the changes in the turbine's wide range of working conditions, the matching change rules of the elementary-level blades and blade row inlet and outlet velocity triangles that can be guaranteed by conventional turbines as the engine speed changes will inevitably be destroyed. The turbine blades designed in the existing technology according to a certain geometric state and turbine operating parameters are often unable to adapt to the airflow velocity triangles of other geometric states and working states, resulting in a series of problems such as deterioration of flow field matching between turbine blade rows, flow separation, and reduced work performance.

[0048] In order to overcome the shortcomings of the existing technology, this embodiment is based on a full three-dimensional aerodynamic design system of a conventional turbine. Aiming at the goal of "multi-objective state design" of a variable geometry turbine, a variable cycle wide-range engine turbine design method is provided. The turbine blade profile is designed using a three-dimensional modeling method based on a general rotating surface. This method fully considers the three-dimensional characteristics of the turbine flow field and better conforms to the actual flow state. Figure 1 FIG. 1 is a flow chart of a method for designing a turbine for a variable cycle wide range engine according to an embodiment of the present invention. Figure 1 As shown, the process includes the following steps:

[0049] S11, based on the preset overall engine performance design requirements, calculating and analyzing the converted flow rate, converted speed, and converted power of multiple different working states.

[0050] Specifically, the preset overall engine performance design requirements include design parameters for inlet total pressure, inlet total temperature, flow rate, speed, expansion ratio, and efficiency, as well as preset geometric design indicators and corresponding design parameters. Consider a design for a variable-cycle wide-range engine turbine for a new fighter jet. Under supersonic cruise conditions, the preset inlet total pressure is 2000 kPa, the inlet total temperature is 2000 K, the flow rate is 90 kg / s, the speed is 15,000 rpm, the expansion ratio is 3.0, and the efficiency target is set at 90%. Furthermore, the preset geometric design indicators include a turbine axial length of 0.4 m and a radial height of 0.5 m. Under subsonic flight conditions, these parameters differ: an inlet total pressure of 1000 kPa, an inlet total temperature of 1800 K, a flow rate of 50 kg / s, a speed of 10,000 rpm, an expansion ratio of 2.0, and an efficiency target of 88%. Geometric design indicators may also be adjusted based on airflow characteristics, such as a radial height of 0.45 m.

[0051] These specific design parameters encompass both thermodynamic parameters and geometric design indicators, ensuring a comprehensive design. Thermodynamic parameters determine the turbine's operating environment and energy conversion requirements, while geometric design indicators directly influence the flow characteristics of the airflow within the turbine. During the design process, designers select high-temperature alloy materials for the turbine blades and discs that can withstand the corresponding heat and pressure loads based on the total inlet pressure and temperature. The turbine's flow capacity and the shape and size of the blades are determined based on parameters such as flow rate and speed to ensure that intake and power generation requirements are met under different flight conditions.

[0052] In one embodiment, for a supersonic cruise aircraft, the main operating conditions are ground takeoff, accelerated climb, subsonic cruise, and supersonic cruise. As shown in Table 1, if a single operating condition is used as the design point, the efficiency at that point is relatively high, but the efficiency drops significantly in other operating conditions. Therefore, as a key component of an aircraft engine, the turbine design should comprehensively consider multiple operating conditions and conduct multi-condition optimization design. The goal of turbine optimization design is generally to maximize efficiency.

[0053] Table 1 Design parameters for different working states

[0054]

[0055] The efficiency of the design state can be expressed as:

[0056]

[0057] in, is the turbine efficiency, G is the turbine inlet flow rate, is the total pressure at the turbine inlet, is the total temperature of the turbine inlet, n is the turbine speed, To convert the flow rate, To convert the rotational speed, f1 represents a function.

[0058] Multi-objective state design requires optimal engine performance under all operating conditions. This is a multi-objective optimization problem, transforming multi-objective state design into multi-objective optimization design. The present invention uses the preset overall engine performance design requirements as the foundation for turbine design. By calculating and analyzing the converted flow rate, converted speed, and converted power under different operating conditions, it can accurately analyze the specific performance requirements of the engine under various operating conditions.

[0059] S12, determining whether the converted flow rates and converted rotation speeds of a plurality of different working states meet an equal condition.

[0060] Specifically, for example, based on the overall engine performance design requirements, the converted flow rate, converted speed, and converted power of m different operating states are calculated and analyzed. If the converted flow rate and converted speed of the m different states can be guaranteed to be equal, then equations (2) and (3) are satisfied:

[0061]

[0062] S131: If the equal conditions are met, design is performed based on a preset conventional turbine design method.

[0063] Specifically, when the converted flow rates and converted speeds for multiple different operating states meet the same conditions, the engine's operating state is relatively stable and close to conventional design conditions. Using a pre-set conventional turbine design approach fully leverages existing, proven design experience, processes, and data. This approach, proven through long-term practical experience, offers a relatively standardized design process, eliminating the need to re-explore complex design paths. This significantly reduces uncertainty and trial-and-error costs during the design process, saving design time and enabling rapid turbine design completion, thereby improving overall design efficiency.

[0064] S132: If the equality condition is not met, different weight coefficients are assigned to each working state, and the design state parameters of the turbine are generated based on the linear weighted sum, where the size of each weight coefficient represents the importance of different working states in the multi-objective optimization problem.

[0065] Specifically, variable-cycle wide-range engines must operate under a variety of complex operating conditions, and the performance requirements for turbines vary significantly across these conditions. Assigning weighting coefficients to different operating conditions allows for appropriate adjustment of design parameters based on the actual importance of each operating condition. During supersonic flight, high thrust requirements are even more critical. By increasing the weighting coefficient for this operating condition, turbine design prioritizes meeting high thrust requirements and optimizing turbine performance in this state. During subsonic cruise, low fuel consumption is paramount. By increasing the weighting coefficient for this operating condition, the design addresses engine performance requirements under various operating conditions, enhancing the engine's adaptability to various flight conditions. Turbine design involves multiple performance objectives, such as efficiency, thrust, and fuel consumption, which often interact with each other. Setting weighting coefficients provides an effective means of balancing these multiple objectives. By adjusting the weighting coefficients, appropriate trade-offs can be made between these objectives under different operating conditions.

[0066] In the embodiment of the present invention, when the converted flow rates and converted speeds of multiple different operating states do not meet the equality condition, different weights are assigned to each operating state. The magnitude of each weight represents the importance of the different operating states in the multi-objective optimization problem, and the linear weighted sum of the various operating states is used as the design state of the turbine. Therefore, the design state parameters of the variable cycle engine turbine can be expressed as follows:

[0067]

[0068]

[0069] Among them, ω i (i=1,2…,m) is the weight coefficient, and Indicates the flow design state parameters, Indicates the flow design state parameters, Indicates the speed design state parameter, Indicates power design state parameters;

[0070] The weight coefficient is calculated according to the following formula:

[0071]

[0072] Among them, t i is the working time of a certain state, T is the total working time, w i is the fuel flow rate at a certain state, W design is the fuel flow rate at design status.

[0073] S133, performing at least one of one-dimensional parameter design, two-dimensional parameter design, and three-dimensional parameter design of the engine turbine based on the design state parameters and the converted power, so that it meets the preset overall engine performance design requirements.

[0074] Specifically, the process of one-dimensional, two-dimensional, and three-dimensional parameter design is a step-by-step, progressive process. One-dimensional parameter design lays the foundation for subsequent design, determining the basic dimensions and key flow parameters of the turbine. Two-dimensional parameter design builds on the one-dimensional foundation by considering more complex flow phenomena and optimizing blade shape and flow paths. Three-dimensional parameter design comprehensively considers the spatial structure of the blades and the three-dimensional flow characteristics of the airflow to achieve comprehensive improvements in turbine performance. This progressive design approach continuously taps into the turbine's performance potential, gradually optimizing its aerodynamic performance and bringing the design closer to the ideal state, thereby improving the engine's overall performance and reliability.

[0075] The embodiments of the present invention allow for at least one of one-dimensional, two-dimensional, and three-dimensional parametric design, providing significant design flexibility. Depending on the design requirements and actual circumstances, different dimensional design approaches can be selected, allowing for the decision of whether to start with a one-dimensional foundational framework or perform intermediate improvements in two or three dimensions, determining the appropriate design dimensions. This flexibility allows the design to better adapt to a variety of complex design scenarios and varying design constraints, improving the adaptability and feasibility of the design solution.

[0076] In one embodiment, if Figure 2 As shown, the embodiment of the present invention is illustrated by an example of a process of progressively designing parameters of an engine turbine in one dimension, two dimensions, and three dimensions:

[0077] The present invention calculates new design parameters based on the overall performance requirements of the target turbine design. With maximum efficiency as the turbine design goal, a meridional flow path design based on one-dimensional optimization of turbine stage parameters is performed. In a variable cycle engine turbine, the change in the guide vane installation angle, Δλ, is crucial to turbine performance. Therefore, the efficiency of a variable cycle engine turbine can be expressed as:

[0078]

[0079] Among them, G represents the flow rate, represents the total inlet temperature, Indicates the total inlet pressure, n indicates the speed, Indicates the converted flow rate, represents the converted speed, and Δλ represents the change in the guide vane installation angle.

[0080] In one specific embodiment, based on calculations of design parameters and converted power, it is assumed that, under certain operating conditions, the appropriate meridian flow channel shape and dimensions are required to meet preset flow and expansion ratio requirements. Calculations revealed that when the meridian flow channel's inlet diameter is designed to be 1.2 meters, its outlet diameter is designed to be 0.8 meters, and its shape is tapered, it is possible to achieve an expansion ratio of 3, while maintaining a flow rate of 90 kg / s. Furthermore, optimization can achieve an efficiency approaching the preset 90% target. This process also considers the impact of rotational speed on airflow, adjusting the blade mounting angle to ensure smooth airflow within the meridian flow channel and reduce flow losses. Ultimately, a one-dimensional parameter design for this operating condition meets the preset overall engine performance design requirements.

[0081] Furthermore, if the one-dimensional design results meet the overall performance requirements, a viscous controlled vortex design method is then used to perform an inverse S2 flow surface design based on the streamline curvature method using the variable geometry turbine design state determined above. The influence of complex factors such as viscosity and the resulting secondary flow on turbine work can be calculated using the radial distribution of entropy. Compared to controlled vortex design, viscous controlled vortex design considers the variation in entropy gradients along the radial direction and its impact on turbine stage work capacity, channel area, airflow parameters, stage efficiency, and inter-stage coordination.

[0082] Furthermore, if the design results of the S2 inverse problem meet the overall performance requirements, the variable cycle engine turbine blades are shaped based on the blade profile design method of the general rotating surface, and the S1 flow surface calculation analysis is performed.

[0083] In one specific embodiment, based on design state parameters, information such as flow design state parameters and expansion ratio design state parameters is known under certain flight conditions. First, initial data such as the airflow velocity and pressure distribution on the S2 flow surface is calculated based on these parameters. Then, the initial design is adjusted by considering the gradient-corrected viscosity of the radial entropy distribution and the influence of secondary flow. For example, analysis revealed that the presence of secondary flow in the blade root region results in significant airflow losses. To address this issue, the blade profile in this region was optimized, increasing the blade curvature so that the airflow better adheres to the blade surface as it passes through it, reducing separation and losses. After multiple iterative calculations, once the inverse problem design results for the S2 flow surface meet the preset pressure distribution and efficiency requirements, turbine blade shape design is performed, and S1 flow surface computational analysis is conducted. During the S1 flow surface calculation, the circumferential spacing and blade thickness distribution of the blades are further optimized, ultimately ensuring that the design meets the preset overall engine performance design requirements under these operating conditions.

[0084] If the blade profile meets the expected requirements, full 3D blade design and optimization are performed, and aerodynamic performance and flow field analysis of the designed turbine are performed using 3D viscosity calculations. If the calculation results meet the overall performance requirements, the design is complete; if not, iterative optimization is required until the overall design requirements are met.

[0085] In one specific embodiment, assuming that the basic shape of the blade has been determined through preliminary design, the blade undergoes full three-dimensional design and optimization to further improve turbine performance. Using three-dimensional design software, the blade's spatial shape is finely adjusted, taking into account the impact of parameters such as the leading edge radius, trailing edge thickness, and tip clearance on aerodynamic performance. Subsequently, a three-dimensional viscosity calculation is used to verify the aerodynamic performance and flow field structure of the optimized blade. If the calculation verification results show that performance indicators such as efficiency and expansion ratio under various operating conditions, such as takeoff and cruise, meet the preset overall engine performance design requirements, the design is concluded. If these requirements are not met, such as if the efficiency under cruise conditions does not reach the preset value, iterative optimization design of relevant blade parameters, such as the leading edge shape and blade mounting angle, is performed again, and three-dimensional viscosity calculation verification is performed again until all preset requirements are met.

[0086] The multi-objective design method provided by the embodiments of the present invention takes all target states into account and can meet the requirements for optimal engine performance under all operating conditions of a variable cycle engine turbine. According to test results, compared with the original design method, the turbine efficiency in four typical operating conditions (ground takeoff, accelerated climb, subsonic cruise, and supersonic cruise) was improved by 0.5% to 1%. A variable cycle engine turbine designed using the method provided by the embodiments of the present invention met the design requirements of the variable cycle engine, with high efficiency under different operating conditions and meeting the flow rate and power requirements for each operating condition, thus verifying the reliability of the proposed variable cycle engine turbine design method.

[0087] This embodiment also provides a variable cycle wide-range engine turbine design system, which is used to implement the above-mentioned embodiments and preferred embodiments. Details already described will not be repeated here. As used below, the term "module" may refer to a combination of software and / or hardware that implements a predetermined function. Although the systems described in the following embodiments are preferably implemented in software, implementation using hardware, or a combination of software and hardware, is also possible and contemplated.

[0088] This embodiment provides a variable cycle wide range engine turbine design system, such as Figure 3 Shown, including:

[0089] The multi-operating condition parameter conversion module 31 is used to calculate and analyze the converted flow, converted speed and converted power of multiple different operating conditions according to the preset overall engine performance design requirements;

[0090] A condition judgment module 32 is used to judge whether the converted flow rates and converted speeds of multiple different working states meet the equality condition;

[0091] A conventional design module 33 is configured to perform design based on a preset conventional turbine design method if the equal conditions are met;

[0092] A design state parameter generation module 34 is configured to assign different weight coefficients to each operating state if the equality condition is not met, and generate the design state parameters of the turbine based on a linear weighted sum, wherein the magnitude of each weight coefficient represents the importance of the different operating states in the multi-objective optimization problem;

[0093] The geometric design module 35 is used to perform at least one of one-dimensional parameter design, two-dimensional parameter design and three-dimensional parameter design of the engine turbine according to the design state parameters and the converted power, so that it meets the preset overall engine performance design requirements.

[0094] In some optional embodiments, the preset overall engine performance design requirements in the multi-operating condition parameter conversion module 31 include: design parameters corresponding to inlet total pressure, inlet total temperature, flow rate, speed, expansion ratio and efficiency, as well as preset geometric design indicators and corresponding design parameters.

[0095] In some optional embodiments, the design state parameters of the variable cycle wide range engine turbine in the design state parameter generation module 34 include: flow design state parameters, expansion ratio design state parameters, speed design state parameters, and power design state parameters;

[0096] The weight coefficient is calculated according to the following formula:

[0097]

[0098] Among them, t i is the working time of a certain state, T is the total working time, w i is the fuel flow rate at a certain state, W design is the fuel flow rate at design status.

[0099] In some optional embodiments, the one-dimensional parameter design in the geometric design module 35 includes:

[0100] Meridian flow channel design is carried out with the goal of maximizing efficiency. Expressed as:

[0101]

[0102] Among them, G represents the flow rate, represents the total inlet temperature, Indicates the total inlet pressure, n indicates the speed, Indicates the flow design state parameters, represents the speed design state parameter, and Δλ represents the change in the guide vane installation angle.

[0103] In some optional embodiments, the two-dimensional parameter design in the geometric design module 35 includes:

[0104] Using the viscous controllable vortex design method, the inverse problem design of the S2 flow surface is performed based on the design state parameters, and the gradient of the entropy distribution along the radial direction is used to correct the viscosity and secondary flow effects;

[0105] If the design results of the S2 flow surface inverse problem meet the preset engine overall performance design requirements, the variable cycle wide range engine turbine blade shape is designed, and the S1 flow surface calculation analysis is performed to make it meet the preset engine overall performance design requirements.

[0106] In some optional embodiments, the three-dimensional parameter design of the engine turbine in the geometric design module 35 includes:

[0107] If the turbine blade design meets the preset overall engine performance design requirements, a full three-dimensional design and optimization of the blades will be performed, and aerodynamic performance and flow field structure will be verified using three-dimensional viscosity calculations;

[0108] If the calculation verification result meets the preset engine overall performance design requirements, the design is completed; if it does not meet the requirements, iterative optimization design is performed until the preset engine overall performance design requirements are met.

[0109] The further functional description of each of the above modules and units is the same as that of the above corresponding embodiments and will not be repeated here.

[0110] The variable cycle wide range engine turbine design system in this embodiment is presented in the form of a functional unit, where the unit refers to an ASIC (Application Specific Integrated Circuit) circuit, a processor and memory that executes one or more software or fixed programs, and / or other devices that can provide the above functions.

[0111] The embodiment of the present invention also provides a computer device having the above Figure 3 The variable cycle wide range engine turbine design system is shown.

[0112] See also Figure 4 , Figure 4 is a schematic diagram of the structure of a computer device provided by an optional embodiment of the present invention, such as Figure 4As shown, the computer device includes: one or more processors 10, memory 20, and interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. Various components utilize different buses to communicate with each other and can be installed on a common mainboard or installed in other ways as needed. The processor can process the instructions executed in the computer device, including instructions stored in the memory or on the memory to display the graphical information of the GUI on an external input / output device (such as, a display device coupled to the interface). In some optional embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories and multiple memories. Equally, multiple computer devices can be connected, and each device provides part of the necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Figure 4 A processor 10 is taken as an example.

[0113] The processor 10 may be a central processing unit, a network processor, or a combination thereof. The processor 10 may further include a hardware chip. The hardware chip may be an application-specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general purpose array logic, or any combination thereof.

[0114] The memory 20 stores instructions that can be executed by at least one processor 10, so as to enable at least one processor 10 to execute the method shown in the above embodiment.

[0115] The memory 20 may include a program storage area and a data storage area, wherein the program storage area may store an operating system and application programs required for at least one function; the data storage area may store data created based on the use of the computer device, etc. In addition, the memory 20 may include a high-speed random access memory, and may also include a non-transient memory, such as at least one disk storage device, a flash memory device, or other non-transient solid-state storage device. In some optional embodiments, the memory 20 may optionally include a memory remotely located relative to the processor 10, and these remote memories may be connected to the computer device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0116] The memory 20 may include a volatile memory, such as a random access memory; the memory may also include a non-volatile memory, such as a flash memory, a hard disk or a solid-state drive; the memory 20 may also include a combination of the above types of memory.

[0117] The computer device further includes a communication interface 30 for the computer device to communicate with other devices or a communication network.

[0118] The embodiment of the present invention also provides a computer-readable storage medium. The above-mentioned method according to the embodiment of the present invention can be implemented in hardware, firmware, or implemented as a computer code that can be recorded in a storage medium, or implemented as a computer code that is originally stored in a remote storage medium or a non-temporary machine-readable storage medium and downloaded through a network and will be stored in a local storage medium, so that the method described herein can be stored in such software processing on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only storage memory, a random access memory, a flash memory, a hard disk or a solid-state drive, etc.; further, the storage medium can also include a combination of the above-mentioned types of memory. It can be understood that a computer, a processor, a microprocessor central control system or programmable hardware includes a storage component that can store or receive software or computer code. When the software or computer code is accessed and executed by a computer, a processor or hardware, the method shown in the above embodiment is implemented.

[0119] A portion of the present invention may be applied as a computer program product, such as a computer program instruction, which, when executed by a computer, can call or provide the method and / or technical solution according to the present invention through the operation of the computer. Those skilled in the art should understand that the form in which the computer program instruction exists in a computer-readable medium includes, but is not limited to, a source file, an executable file, an installation package file, etc. Accordingly, the way in which the computer program instruction is executed by the computer includes, but is not limited to: the computer directly executes the instruction, or the computer compiles the instruction and then executes the corresponding compiled program, or the computer reads and executes the instruction, or the computer reads and installs the instruction and then executes the corresponding installed program. Here, the computer-readable medium may be any available computer-readable storage medium or communication medium that can be accessed by the computer.

[0120] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A variable cycle wide range engine turbine design method, characterized in that: include: Calculate and analyze the converted flow, converted speed and converted power under multiple different working conditions according to the preset overall engine performance design requirements; Determine whether the converted flow rates and converted speeds of multiple different working states meet the equality condition; If the equal conditions are met, the design is performed based on the preset conventional turbine design method; If the equality condition is not met, different weight coefficients are assigned to each working state, and the design state parameters of the turbine are generated based on the linear weighted sum, where the size of each weight coefficient represents the importance of different working states in the multi-objective optimization problem; According to the design state parameters and the converted power, at least one of the one-dimensional parameter design, the two-dimensional parameter design and the three-dimensional parameter design of the engine turbine is performed to meet the preset overall performance design requirements of the engine.

2. The method according to claim 1, characterized in that The preset overall engine performance design requirements include: design parameters corresponding to inlet total pressure, inlet total temperature, flow rate, speed, expansion ratio and efficiency, as well as preset geometric design indicators and corresponding design parameters.

3. The method according to claim 2, characterized in that The design state parameters of the variable cycle wide range engine turbine include: flow design state parameters, expansion ratio design state parameters, speed design state parameters, and power design state parameters; The weight coefficient is calculated according to the following formula: Among them, t i is the working time of a certain state, T is the total working time, w i is the fuel flow rate at a certain state, W design is the fuel flow rate at design status.

4. The method according to claim 3, characterized in that The one-dimensional parameter design includes: Meridian flow channel design is carried out with the goal of maximizing efficiency. Expressed as: Among them, G represents the flow rate, represents the total inlet temperature, Indicates the total inlet pressure, n indicates the speed, Indicates the converted flow rate, represents the converted speed, and Δλ represents the change in the guide vane installation angle.

5. The method according to claim 1 or 3, characterized in that The two-dimensional parameter design includes: Using the viscous controllable vortex design method, the inverse problem design of the S2 flow surface is performed based on the design state parameters, and the gradient of the entropy distribution along the radial direction is used to correct the viscosity and secondary flow effects; If the design results of the S2 flow surface inverse problem meet the preset engine overall performance design requirements, the variable cycle wide range engine turbine blade shape is designed, and the S1 flow surface calculation analysis is performed to make it meet the preset engine overall performance design requirements.

6. The method according to claim 5, characterized in that The three-dimensional parameter design of the engine turbine includes: If the turbine blade design meets the preset overall engine performance design requirements, a full three-dimensional design and optimization of the blades will be performed, and aerodynamic performance and flow field structure will be verified using three-dimensional viscosity calculations; If the calculation verification result meets the preset engine overall performance design requirements, the design is completed; if it does not meet the requirements, iterative optimization design is performed until the preset engine overall performance design requirements are met.

7. A variable cycle wide range engine turbine design system, characterized in that: include: The multi-operating condition parameter conversion module is used to calculate and analyze the converted flow, converted speed and converted power of multiple different operating conditions according to the preset overall engine performance design requirements; A condition judgment module is used to judge whether the converted flow rates and converted speeds of multiple different working states meet the equality condition; A conventional design module, configured to perform design based on a preset conventional turbine design method if equal conditions are met; A design state parameter generation module is used to assign different weight coefficients to each working state if the equality condition is not met, and generate the design state parameters of the turbine based on the linear weighted sum, where the size of each weight coefficient represents the importance of different working states in the multi-objective optimization problem; The geometric design module is used to perform at least one of one-dimensional parameter design, two-dimensional parameter design and three-dimensional parameter design of the engine turbine according to the design state parameters and the converted power, so that it meets the preset overall performance design requirements of the engine.

8. A computer device, characterized in that: include: A memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the variable cycle wide range engine turbine design method according to any one of claims 1 to 6 by executing the computer instructions.

9. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a computer to execute the variable cycle wide range engine turbine design method according to any one of claims 1 to 6.

10. A computer program product, characterized in that The method comprises computer instructions for causing a computer to execute the variable cycle wide range engine turbine design method according to any one of claims 1 to 6.

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