Interstage mixing turbine pneumatic integrated design method, system, medium and equipment

Abstract

The invention discloses an interstage mixing turbine pneumatic integrated design method, system, medium and equipment, in the method, one-dimensional flow design is conducted on a blade tip and a blade root of a turbine, input variables and output variables of one-dimensional flow design of the interstage mixing turbine are determined, the input variables are pneumatic performance and geometric parameters, and the output variables are geometric parameters; blade profile design is conducted on the blade tip and the blade root of the turbine, input variables and output variables of blade profile design of the interstage mixing turbine are determined, the input variables are geometric parameters, the output variables are blade profile space parameters, and turbine blade two-dimensional design is conducted from the blade tip to the blade root; three-dimensional modeling of the interstage mixing turbine is completed by using Unigraphics NX, determination of a rotating fluid domain of an interstage mixing turbine model, division of computational grids and CFD simulation calculation are completed by using Workbench, and an aerodynamic performance result is obtained.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic simulation technology for variable cycle engines, and in particular to an integrated aerodynamic design method, system, medium, and equipment for interstage mixing turbines. Background Technology

[0002] In the modern aviation field, variable cycle engines have become a key direction for the development of aviation power due to their unique advantages. Traditional aero-turbine engines have fixed thermodynamic cycle characteristics and can only achieve optimal performance within a limited flight range. In contrast, variable cycle engines have variable thermodynamic cycle characteristics. By changing the geometry, size, or position of some components, thermodynamic cycle parameters such as pressure ratio, turbine inlet temperature, airflow, and bypass ratio can be flexibly adjusted to achieve switching of engine cycle operating modes, thereby maintaining good performance under various flight conditions.

[0003] The variable-cycle engine architecture with an interstage mixing turbine is a variable-cycle engine architecture adapted to the mission profile of air superiority fighters. The interstage mixing turbine is the core variable-cycle feature unique to this engine architecture. During subsonic cruise, this component increases the total fan flow rate and bypass ratio by increasing the fan speed and reducing the internal flow rate, thereby achieving low fuel consumption during subsonic cruise.

[0004] Currently, China has conducted extensive research on the aerodynamic design methods and loss characteristics of turbine cooling bleed air, but these are not applicable to the design and loss and efficiency analysis of interstage mixing turbines, making it difficult to meet the performance, economy, and other multi-purpose and multi-task requirements of this variable cycle engine architecture.

[0005] The information disclosed in the background section is only for enhancing the understanding of the background of this invention, and therefore may contain information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0006] This invention provides a method, system, medium, and equipment for the integrated aerodynamic design of interstage mixing turbines, which solves the problems of large interstage mixing losses and overall efficiency in the existing integrated aerodynamic design of interstage mixing turbines for variable cycle engines.

[0007] An interstage mixing turbine aerodynamic integration design method includes:

[0008] One-dimensional flow design was performed on the blade tip and blade root of the turbine to determine the input and output variables of the one-dimensional flow design of the interstage mixing turbine. The input variables are aerodynamic performance and geometric parameters, and the output variables are geometric parameters.

[0009] The blade profiles of the turbine are designed separately at the blade tip and blade root. The input and output variables of the interstage mixing turbine blade profile design are determined. The input variables are geometric parameters and the output variables are blade profile spatial parameters. The turbine blades are designed in two dimensions from the blade tip to the blade root.

[0010] The 3D model of the interstage mixing turbine was completed using Unigraphics NX. Workbench was used to determine the rotating fluid domain of the interstage mixing turbine model, generate the computational mesh, perform CFD simulation calculations, and obtain aerodynamic performance results.

[0011] In the aforementioned interstage mixing turbine aerodynamic integrated design method, the one-dimensional flow design includes,

[0012] Step S111, in the one-dimensional flow design process, based on the stator critical area A nb Calculate the absolute velocity c1 at the stator exit;

[0013] Step S112: Based on the velocity triangle and the physical rotational speed N of the turbine, calculate the conversion process from the stator outlet to the rotor inlet, and obtain the relative velocity w1 at the rotor inlet.

[0014] Step S113: Based on the critical area of ​​the rotor, calculate the relative velocity w2 at the rotor outlet. Based on the velocity triangle and the physical rotational speed N of the turbine, calculate the conversion process from the rotor outlet to the turbine outlet to obtain the absolute velocity c2 at the turbine outlet.

[0015] In the aforementioned interstage mixing turbine aerodynamic integrated design method, in step S111, the Mach number at the stator critical point is given as 1, and the critical area A is calculated based on the airflow state parameters and the Mach number. nb The calculation formula is as follows:

[0016]

[0017] Among them, A nb It is the stator critical area; Wa represents the gas flow rate; ρ represents the gas density; v represents the gas velocity; P4 and T4 represent the turbine inlet static pressure and static temperature, respectively; R is the gas constant; K represents the ratio of gas specific heat capacities; Ma nb It is the Mach number of the gas in the critical area.

[0018] In the aforementioned interstage mixing turbine aerodynamic integrated design method, the total temperature at the stator outlet remains constant, and the total pressure loss is represented by the total pressure recovery coefficient. After the stator outlet cross-sectional airflow parameters are calculated, the formula for calculating the absolute velocity c1 of the stator outlet airflow is as follows:

[0019]

[0020] Where c1 represents the absolute velocity of the airflow at the stator exit.

[0021] In the aforementioned interstage blending turbine aerodynamic integrated design method, in step S112, the relative velocity w1 at the rotor inlet is calculated using the following formula:

[0022]

[0023]

[0024] Where w1 represents the relative velocity at the rotor inlet; α1 represents the angle between the absolute velocity c1 and the airflow direction; β1 represents the angle between the relative velocity w1 and the airflow direction; u is the tangential velocity of the rotor at radius r; r represents the radius; and N is the physical rotational speed of the turbine.

[0025] In the aforementioned interstage blending turbine aerodynamic integrated design method, in step S113, the relative velocity w2 at the rotor outlet can be calculated based on the outlet air path performance parameters, and is expressed as:

[0026]

[0027] Where w2 represents the relative velocity at the rotor outlet; T5 represents the static temperature at the turbine outlet; and Ma5 represents the Mach number of the outlet airflow.

[0028] In the aforementioned interstage hybrid turbine aerodynamic integrated design method, the absolute velocity c2 at the turbine outlet and the rotor outlet angle are obtained based on the relative velocities w2 and N, using the following calculation formula:

[0029]

[0030] Where c2 represents the absolute velocity at the turbine outlet; α2 represents the angle between the absolute velocity c2 and the airflow direction; and β2 represents the angle between the relative velocity w2 and the airflow direction.

[0031] A system for implementing the method includes:

[0032] The one-dimensional flow module performs one-dimensional flow design for the blade tip and blade root of the turbine, and determines the input and output variables of the one-dimensional flow design of the interstage mixing turbine. The input variables are aerodynamic performance and geometric parameters, and the output variables are geometric parameters.

[0033] The blade profile design module performs blade profile design on the blade tip and blade root of the turbine, and determines the input and output variables of the interstage mixing turbine blade profile design. The input variables are geometric parameters, and the output variables are blade profile spatial parameters. The turbine blade is designed in two dimensions from the blade tip to the blade root.

[0034] The modeling module uses Unigraphics NX to complete the 3D modeling of the interstage mixing turbine, and Workbench to complete the determination of the rotating fluid domain, the generation of the computational mesh, and the CFD simulation calculation to obtain the aerodynamic performance results of the interstage mixing turbine model.

[0035] A computer storage medium including computer instructions that, when run on a computer, cause the computer to perform the method.

[0036] An electronic device, the electronic device comprising:

[0037] Memory, processor, and computer programs stored in memory and executable on the processor, wherein,

[0038] The processor implements the method when executing the program.

[0039] Compared with existing technologies, this invention has the following advantages: it establishes a design and calculation platform for interstage blending turbine blades, enabling the design and modeling of turbine blades; and it establishes a simulation platform for the aerodynamic performance of interstage blending turbines, enabling the simulation calculation of blade aerodynamic performance. This invention solves the problems of large interstage blending losses and overall efficiency in the integrated aerodynamic design of interstage blending turbines in existing technologies. Attached Figure Description

[0040] Various other advantages and benefits of the present invention will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. Furthermore, the same reference numerals denote the same parts throughout the drawings.

[0041] In the attached diagram:

[0042] Figure 1 This is a schematic flowchart of an embodiment of the present disclosure of an integrated aerodynamic design method for an interstage mixing turbine in a variable cycle engine;

[0043] Figure 2 This is a definition of the turbine stator and rotor cross-section and a velocity triangle diagram provided in one embodiment of the present disclosure;

[0044] Figure 3 This is a single-channel diagram of an interstage mixing turbine provided in one embodiment of this disclosure;

[0045] Figure 4This is a two-stage stator and rotor mesh diagram of an interstage mixing turbine provided in one embodiment of this disclosure.

[0046] The present invention will be further explained below with reference to the accompanying drawings and embodiments. Detailed Implementation

[0047] Specific embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While specific embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0048] It should be noted that certain terms are used in the specification and claims to refer to specific components. Those skilled in the art will understand that different terms may be used to refer to the same component. This specification and claims do not distinguish components based on differences in terminology, but rather on differences in function. The terms "comprising" or "including" used throughout the specification and claims are open-ended and should be interpreted as "comprising but not limited to." The following descriptions are preferred embodiments for carrying out the invention; however, these descriptions are for the purpose of understanding the general principles of the specification and are not intended to limit the scope of the invention. The scope of protection of this invention is determined by the appended claims.

[0049] To facilitate understanding of the embodiments of the present invention, further explanations and descriptions will be provided below with reference to the accompanying drawings and specific embodiments. The accompanying drawings do not constitute a limitation on the embodiments of the present invention.

[0050] like Figures 1 to 4 As shown, the integrated aerodynamic design method for interstage mixing turbines includes the following steps:

[0051] One-dimensional flow design was performed on the blade tip and blade root of the turbine to determine the input and output variables of the one-dimensional flow design of the interstage mixing turbine. The input variables are aerodynamic performance and geometric parameters, and the output variables are geometric parameters.

[0052] The blade profiles of the turbine are designed separately at the blade tip and blade root. The input and output variables of the interstage mixing turbine blade profile design are determined. The input variables are geometric parameters and the output variables are blade profile spatial parameters. The turbine blades are designed in two dimensions from the blade tip to the blade root.

[0053] The 3D model of the interstage mixing turbine was completed using Unigraphics NX. Workbench was used to determine the rotating fluid domain of the interstage mixing turbine model, generate the computational mesh, perform CFD simulation calculations, and obtain aerodynamic performance results.

[0054] In a preferred embodiment of the interstage mixing turbine aerodynamic integrated design method, the one-dimensional flow design includes,

[0055] Step S111, in the one-dimensional flow design process, based on the stator critical area A nb Calculate the absolute velocity c1 at the stator exit;

[0056] Step S112: Based on the velocity triangle and the physical rotational speed N of the turbine, calculate the conversion process from the stator outlet to the rotor inlet, and obtain the relative velocity w1 at the rotor inlet.

[0057] Step S113: Based on the critical area of ​​the rotor, calculate the relative velocity w2 at the rotor outlet. Based on the velocity triangle and the physical rotational speed N of the turbine, calculate the conversion process from the rotor outlet to the turbine outlet to obtain the absolute velocity c2 at the turbine outlet.

[0058] In a preferred embodiment of the interstage mixing turbine aerodynamic integrated design method, in step S111, the Mach number at the stator critical point is given as 1, and the critical area A is calculated based on the airflow state parameters and the Mach number. nb The calculation formula is as follows:

[0059]

[0060] Among them, A nb It is the stator critical area; Wa represents the gas flow rate; ρ represents the gas density; v represents the gas velocity; P4 and T4 represent the turbine inlet static pressure and static temperature, respectively; R is the gas constant; K represents the ratio of gas specific heat capacities; Ma nb It is the Mach number of the gas in the critical area.

[0061] In a preferred embodiment of the interstage mixing turbine aerodynamic integrated design method, the total temperature at the stator outlet remains constant, and the total pressure loss is represented by the total pressure recovery coefficient. After the stator outlet cross-sectional airflow parameters are calculated, the formula for calculating the absolute velocity c1 of the stator outlet airflow is as follows:

[0062]

[0063] Where c1 represents the absolute velocity of the airflow at the stator exit.

[0064] In a preferred embodiment of the interstage mixing turbine aerodynamic integrated design method, in step S112, the relative velocity w1 at the rotor inlet is calculated using the following formula:

[0065]

[0066]

[0067] Where w1 represents the relative velocity at the rotor inlet; α1 represents the angle between the absolute velocity c1 and the airflow direction; β1 represents the angle between the relative velocity w1 and the airflow direction; u is the tangential velocity of the rotor at radius r; r represents the radius; and N is the physical rotational speed of the turbine.

[0068] In a preferred embodiment of the interstage mixing turbine aerodynamic integrated design method, in step S113, the relative velocity w2 at the rotor outlet can be calculated based on the outlet air path performance parameters, and is expressed as:

[0069]

[0070] Where w2 represents the relative velocity at the rotor outlet; T5 represents the static temperature at the turbine outlet; and Ma5 represents the Mach number of the outlet airflow.

[0071] In a preferred embodiment of the interstage mixing turbine aerodynamic integrated design method, the absolute velocity c2 at the turbine outlet and the rotor outlet angle are obtained based on the relative velocities w2 and N, and the calculation formula is as follows:

[0072]

[0073] Where c2 represents the absolute velocity at the turbine outlet; α2 represents the angle between the absolute velocity c2 and the airflow direction; and β2 represents the angle between the relative velocity w2 and the airflow direction.

[0074] A system for implementing the method includes:

[0075] The one-dimensional flow module performs one-dimensional flow design for the blade tip and blade root of the turbine, and determines the input and output variables of the one-dimensional flow design of the interstage mixing turbine. The input variables are aerodynamic performance and geometric parameters, and the output variables are geometric parameters.

[0076] The blade profile design module performs blade profile design on the blade tip and blade root of the turbine, and determines the input and output variables of the interstage mixing turbine blade profile design. The input variables are geometric parameters, and the output variables are blade profile spatial parameters. The turbine blade is designed in two dimensions from the blade tip to the blade root.

[0077] The modeling module uses Unigraphics NX to complete the 3D modeling of the interstage mixing turbine, and Workbench to complete the determination of the rotating fluid domain, the generation of the computational mesh, and the CFD simulation calculation to obtain the aerodynamic performance results of the interstage mixing turbine model.

[0078] A computer storage medium including computer instructions that, when run on a computer, cause the computer to perform the method.

[0079] An electronic device, the electronic device comprising:

[0080] Memory, processor, and computer programs stored in memory and executable on the processor, wherein,

[0081] The processor implements the method when executing the program.

[0082] In one embodiment, such as Figure 1 As shown, this invention provides a method for integrated aerodynamic design of an interstage mixing turbine for a variable cycle engine, comprising the following steps:

[0083] Step S1: Build an interstage mixing turbine blade deflection design calculation platform to realize turbine blade design modeling;

[0084] The method for constructing a design and calculation platform for the aerodynamic performance of an interstage mixing turbine is as follows:

[0085] Step S11: Perform one-dimensional flow design on the blade tip and blade root of the turbine respectively, and determine the input and output variables of the one-dimensional flow design of the interstage mixing turbine. The input variables are aerodynamic performance and geometric parameters, and the output variables are geometric parameters.

[0086] Calculate the output variables based on the given input variables to complete the one-dimensional flow design of the interstage mixing turbine:

[0087] Step S111, in the one-dimensional flow design process, based on the stator critical area A nb Calculate the absolute velocity c1 at the stator exit. Given a Mach number of 1 at the stator critical point, calculate the critical area A based on the airflow state parameters and the Mach number. nb The calculation formula is as follows:

[0088]

[0089] Among them, A nb It is the stator critical area; Wa represents the gas flow rate; ρ represents the gas density; v represents the gas velocity; P4 and T4 represent the turbine inlet static pressure and static temperature, respectively; R is the gas constant; K represents the ratio of gas specific heat capacities; Ma nb It is the Mach number of the gas in the critical area.

[0090] The gas flows through the turbine stator without performing work on the surroundings, and heat transfer to the casing is negligible. However, flow losses exist, so the total temperature at the stator outlet can be considered constant, and the total pressure loss is represented by the total pressure recovery coefficient. After calculating the gas path parameters at the stator outlet section, the absolute velocity c1 of the gas flow at the stator outlet is calculated using the following formula:

[0091]

[0092] Where c1 represents the absolute velocity of the airflow at the stator exit.

[0093] Step S112, as follows Figure 2 As shown, based on the velocity triangle and the physical rotational speed N of the turbine, the conversion process from the stator outlet to the rotor inlet is calculated, and the relative velocity w1 at the rotor inlet is obtained. The calculation formula is as follows:

[0094]

[0095]

[0096] Where w1 represents the relative velocity at the rotor inlet; α1 represents the angle between the absolute velocity c1 and the airflow direction; β1 represents the angle between the relative velocity w1 and the airflow direction; u is the tangential velocity of the rotor at radius r; r represents the radius; and N is the physical rotational speed of the turbine.

[0097] Step S113: Based on the rotor critical area, calculate the relative velocity w2 at the rotor outlet. The calculation formula is as follows:

[0098]

[0099] Where w2 represents the relative velocity at the rotor outlet; T5 represents the static temperature at the turbine outlet; and Ma5 represents the Mach number of the outlet airflow.

[0100] Based on the velocity triangle and the physical rotational speed N of the turbine, the conversion process from the rotor outlet to the turbine outlet is calculated to obtain the absolute velocity c2 at the turbine outlet and the rotor outlet angle. The calculation formula is as follows:

[0101]

[0102] Where c2 represents the absolute velocity at the turbine outlet; α2 represents the angle between the absolute velocity c2 and the airflow direction; and β2 represents the angle between the relative velocity w2 and the airflow direction.

[0103] Step S12: Perform blade profile design for the blade tip and blade root of the turbine respectively, and determine the input and output variables for the interstage mixing turbine blade profile design. The input variables are geometric parameters, and the output variables are blade profile spatial parameters.

[0104] Step S13: Perform two-dimensional design of turbine blades from blade tip to blade root;

[0105] Step S2: Build an interstage mixing turbine aerodynamic performance simulation platform to realize the simulation calculation of blade aerodynamic performance;

[0106] The method for building a simulation platform for the aerodynamic performance of interstage mixing turbines is as follows:

[0107] Step S21: Use Unigraphics NX to complete the 3D modeling of the interstage mixing turbine, such as... Figure 3 As shown;

[0108] Step S22: Use Workbench to determine the rotating fluid domain and generate the computational mesh for the interstage mixing turbine model, such as... Figure 4 As shown, CFD simulation boundary conditions were set to obtain aerodynamic performance results.

[0109] In one embodiment, the mixing loss and overall efficiency of an interstage mixing turbine with an integrated aerodynamic design are simulated and verified. The total pressure loss of the mixer mainly consists of the following two aspects: (1) the loss caused by the mixing airflow affecting the flow field of the internal airflow; (2) the loss caused by the mixing of the two airflows. In the subsequent numerical simulation, firstly, the turbine components are simulated without mixing, and the actual power and overall efficiency of the two-stage turbine are calculated. In the unmixed simulation, it is necessary to re-establish the unperforated second-stage turbine guide model, because the internal airflow will inevitably flow into the mixing channel of the second-stage guide. Then, simulations with different mixing flow rates are performed at the same rotational speed, and the actual power and overall efficiency of the two-stage turbine after mixing are calculated, and the influence of different mixing flow rates on turbine power, overall efficiency and mixing loss is analyzed.

[0110] The simulation operation is based on a speed of 32000 r / min, and the simulation boundary conditions are shown in Table 1. Three sets of mixed inlet conditions are set, mainly different from the total pressure at the mixed inlet.

[0111] Table 1. Boundary conditions for blending inlet

[0112]

[0113] As shown in Table 2, compared to the unmixed turbine, the pressure ratio of the second-stage turbine under mixing condition 1 increased from 2.320 to 2.492, and the power of the second-stage turbine also increased accordingly from 6.065 × 10⁻⁶. 4 Increased to 7.164 × 10 4 W, meaning the mixed gas can improve the work capacity of the second turbine. However, the mixed gas also interferes with the flow field of the first turbine, causing the pressure drop ratio of the first-stage turbine to decrease from 1.981 to 1.750, and the power of the first-stage turbine to decrease from 5.789 × 10⁻⁶. 4 Reduced to 5.171×10 4 W. Meanwhile, the overall turbine power increased to 1.234 × 10⁻⁶. 5 W indicates that as the mixing flow rate increases, the overall turbine power also increases, compared to the unmixed turbine's overall power of 1.185 × 10⁻⁶. 5W indicates that interstage mixing can effectively improve the overall work capacity of the turbine. Furthermore, the interstage mixing turbine obtained through aerodynamic integration design improved the overall turbine efficiency from 0.8336 to 0.8814, demonstrating that this method effectively solves the problems of large interstage mixing losses and low overall efficiency in existing interstage mixing turbine aerodynamic integration designs. Similarly, mixing conditions 2 and 3 also reduced mixing losses and improved overall efficiency and turbine power.

[0114] Table 2 Performance parameters under different blending conditions

[0115]

[0116] The aerodynamic integrated design method for interstage mixing turbines in variable cycle engines proposed in this invention can realize the modeling and performance calculation of interstage mixing turbines under different mixing flow rates and pressures, analyze the impact of interstage mixing on turbine power, efficiency and flow losses, and effectively solve the problems of large interstage mixing losses and overall efficiency in the existing aerodynamic integrated design of interstage mixing turbines.

[0117] This invention establishes a design and calculation platform for interstage mixing turbine blades, performing one-dimensional flow design at the blade tip and root separately; calculating output variables (geometric parameters) based on input variables (aerodynamic performance and geometric parameters); designing the airfoil and outputting its spatial parameters; and designing the blade in two dimensions from tip to root. This achieves an integrated aerodynamic modeling process from one-dimensional to three-dimensional, improving design accuracy; separate design of the blade tip and root considers the differences in end-flow characteristics, improving blade aerodynamic performance; clearly defined input and output variables facilitate parametric modeling and automated design; provides a high-precision three-dimensional geometric model foundation for subsequent CFD simulations, enhancing simulation reliability; and supports refined design of complex flow structures in variable cycle engines, adapting to multi-condition operation requirements. The stator critical area and other flow parameters are calculated using the stator outlet Mach number and static temperature; the rotor inlet and outlet velocities are calculated using velocity triangles and physical rotational speed N; and flow modeling is performed using parameters such as airflow direction angle. The stator outlet Mach number and static temperature accurately reflect the flow state of the gas in the stator channel, providing a foundation for subsequent velocity calculations. Velocity triangle modeling precisely describes the airflow trajectory in the rotor, improving the accuracy of aerodynamic performance prediction. Modeling with angle parameters (α, β) enhances airflow direction control and optimizes blade angle design. It also provides boundary conditions and initial flow field settings for subsequent CFD simulations, enhancing simulation accuracy. Based on one-dimensional flow design results, airfoil parameter design is carried out. Two-dimensional blade modeling is performed from the blade tip to the blade root. The output airfoil spatial parameters are used as input for three-dimensional modeling. Airfoil design directly determines the flow characteristics of the airflow in the blade channel, affecting efficiency and losses. The two-dimensional modeling process considers the airflow distribution characteristics in the blade cascade, optimizing blade curvature and thickness distribution. The spatial parameter output supports three-dimensional modeling and structural strength analysis, ensuring coordinated aerodynamic and structural design. This improves the aerodynamic efficiency and stall resistance of the blades, adapting to the complex operating conditions of variable cycle engines. It also provides fundamental geometric support for flow control and loss optimization in interstage mixing turbines. A simulation platform for the aerodynamic performance of an interstage mixing turbine was constructed. Unigraphics NX was used for 3D modeling; Workbench was used for fluid domain partitioning and mesh generation; CFD boundary conditions were set, and simulation calculations were performed to obtain aerodynamic performance results (pressure, velocity, loss, efficiency, etc.). 3D modeling achieves a digital reconstruction of the realistic geometry, improving simulation accuracy; mesh generation ensures the stability and convergence of the flow field solution, suitable for complex flow structures; CFD simulation can intuitively reflect the flow state of the airflow in the interstage mixing turbine and identify loss sources; reasonable boundary condition settings simulate real operating conditions, improving the reliability of simulation results; aerodynamic performance results can be used to back-optimize blade design and flow control strategies, forming a design-simulation closed loop.The flow loss mechanism of interstage mixing turbines is modeled and its performance analyzed under different mixing flow rates and pressures. The impact of mixing on turbine power and efficiency is evaluated through one-dimensional flow and CFD simulation. The flow loss is reduced by optimizing blade angles, airfoils, and mixing structures. The influence mechanism of interstage mixing on flow loss is analyzed, and key loss regions are identified. Optimization of the mixing structure can improve airflow mixing uniformity and reduce energy dissipation. Adjustment of blade angles and airfoils can reduce boundary layer separation and secondary flow losses, improve the overall turbine efficiency, and meet the efficiency requirements of multi-mode operation of variable cycle engines. This supports the engine to maintain high-efficiency operation under different flight conditions and improves mission adaptability.

[0118] Although embodiments of the present invention have been described above in conjunction with the accompanying drawings, the present invention is not limited to the specific embodiments and application fields described above. The specific embodiments described above are merely illustrative and instructive, and not restrictive. Those skilled in the art can make many other forms based on the guidance of this specification and without departing from the scope of protection of the claims of the present invention, and all of these are within the scope of protection of the present invention.

Claims

1. A method for integrated aerodynamic design of interstage mixing turbines, characterized in that, Includes the following steps: One-dimensional flow design was performed on the blade tip and blade root of the turbine to determine the input and output variables of the one-dimensional flow design of the interstage mixing turbine. The input variables are aerodynamic performance and geometric parameters, and the output variables are geometric parameters. The blade profiles of the turbine are designed separately at the blade tip and blade root. The input and output variables of the interstage mixing turbine blade profile design are determined. The input variables are geometric parameters and the output variables are blade profile spatial parameters. The turbine blades are designed in two dimensions from the blade tip to the blade root. The 3D model of the interstage mixing turbine was completed using Unigraphics NX. Workbench was used to determine the rotating fluid domain of the interstage mixing turbine model, generate the computational mesh, perform CFD simulation calculations, and obtain aerodynamic performance results.

2. The interstage blending turbine aerodynamic integrated design method according to claim 1, characterized in that, Preferred one-dimensional flow designs include: Step S111, in the one-dimensional flow design process, based on the stator critical area A nb Calculate the absolute velocity c1 at the stator exit; Step S112: Based on the velocity triangle and the physical rotational speed N of the turbine, calculate the conversion process from the stator outlet to the rotor inlet, and obtain the relative velocity w1 at the rotor inlet. Step S113: Based on the critical area of ​​the rotor, calculate the relative velocity w2 at the rotor outlet. Based on the velocity triangle and the physical rotational speed N of the turbine, calculate the conversion process from the rotor outlet to the turbine outlet to obtain the absolute velocity c2 at the turbine outlet.

3. The interstage blending turbine aerodynamic integrated design method according to claim 2, characterized in that, In step S111, the Mach number at the stator critical point is given as 1, and the critical area A is calculated based on the airflow state parameters and the Mach number. nb The calculation formula is as follows: ； Among them, A nb It is the stator critical area; Wa represents the gas flow rate; ρ represents the gas density; v represents the gas velocity; P4 and T4 represent the turbine inlet static pressure and static temperature, respectively; R is the gas constant; K represents the ratio of gas specific heat capacities; Ma nb It is the Mach number of the gas in the critical area.

4. The interstage blending turbine aerodynamic integrated design method according to claim 3, characterized in that, With the total temperature at the stator outlet remaining constant, and the total pressure loss expressed by the total pressure recovery coefficient, the formula for calculating the absolute velocity c1 of the stator outlet gas flow after the stator outlet cross-sectional gas path parameters have been calculated is as follows: ； Where c1 represents the absolute velocity of the airflow at the stator exit.

5. The interstage blending turbine aerodynamic integrated design method according to claim 1, characterized in that, In step S112, the relative velocity w1 at the rotor inlet is calculated using the following formula: ； ； Where w1 represents the relative velocity at the rotor inlet; α1 represents the angle between the absolute velocity c1 and the airflow direction; β1 represents the angle between the relative velocity w1 and the airflow direction; u is the tangential velocity of the rotor at radius r; r represents the radius; and N is the physical rotational speed of the turbine.

6. The interstage mixing turbine aerodynamic integrated design method according to claim 1, characterized in that, In step S113, the relative velocity w2 at the rotor outlet can be calculated based on the outlet gas path performance parameters, and is expressed as: ； Where w2 represents the relative velocity at the rotor outlet; T5 represents the static temperature at the turbine outlet; and Ma5 represents the Mach number of the outlet airflow.

7. The interstage blending turbine aerodynamic integrated design method according to claim 6, characterized in that, Based on the relative velocities w2 and N, the absolute velocity c2 at the turbine outlet and the rotor outlet angle are obtained using the following formula: ； Where c2 represents the absolute velocity at the turbine outlet; α2 represents the angle between the absolute velocity c2 and the airflow direction; and β2 represents the angle between the relative velocity w2 and the airflow direction.

8. A system for implementing the method of any one of claims 1-7, characterized in that, It includes: The one-dimensional flow module performs one-dimensional flow design for the blade tip and blade root of the turbine, and determines the input and output variables of the one-dimensional flow design of the interstage mixing turbine. The input variables are aerodynamic performance and geometric parameters, and the output variables are geometric parameters. The blade profile design module performs blade profile design on the blade tip and blade root of the turbine, and determines the input and output variables of the interstage mixing turbine blade profile design. The input variables are geometric parameters, and the output variables are blade profile spatial parameters. The turbine blade is designed in two dimensions from the blade tip to the blade root. The modeling module uses Unigraphics NX to complete the 3D modeling of the interstage mixing turbine, and Workbench to complete the determination of the rotating fluid domain, the generation of the computational mesh, and the CFD simulation calculation to obtain the aerodynamic performance results of the interstage mixing turbine model.

9. A computer storage medium, characterized in that, The storage medium includes computer instructions that, when executed on a computer, cause the computer to perform the method as described in any one of claims 1-7.

10. An electronic device, characterized in that, The electronic device includes: Memory, processor, and computer programs stored in memory and executable on the processor, wherein, When the processor executes the program, it implements the method as described in any one of claims 1-7.

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