Non-uniformly-arranged efficient turbulent flow rib dust accumulation structure in rotor-stator disc cavity of aero-engine and design method of non-uniformly-arranged efficient turbulent flow rib dust accumulation structure

Abstract

The invention discloses a non-uniformly-arranged efficient turbulent flow rib dust accumulation structure in a rotor and stator disc cavity of an aero-engine and a design method, and relates to the field of design of turbulent flow rib dust accumulation structures in aero-engines. The problems that according to an existing turbulent flow structure, the optimal design is difficult to find out by changing the geometric structure for multiple times through a trial-and-error exhaustion design method, the design efficiency is low, and meanwhile the resistance loss is too large and cold air cannot flow out due to unreasonable design of parameters such as the turbulent flow rib spacing are solved. According to the method, turbulent flow ribs are arranged on an impact target surface in a rotor-stator disc cavity to change the distribution characteristic of a flow field, and the number of collision times of particles and a wall surface is increased by utilizing a lifting area of airflow in front of fins and a backflow area at the rear of the fins, so that part of particles are separated from incoming flow, and part of particles are deposited in front of the turbulent flow ribs; and finally, more particles are deposited in the rotating and static disc cavity. The design method is further suitable for the application field of the design method of the non-uniform turbulent flow rib dust accumulation structure capable of improving the particle deposition rate in the rotor-stator cavity.

Description

Technical Field

[0001] This invention relates to the field of dust accumulation structure design for turbulence ribs in aero engines, specifically to a high-efficiency dust accumulation structure and design method for non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero engine. Background Technology

[0002] Aero engines operating in environments with high levels of dust and sand are accompanied by high concentrations of particulate matter. Even after passing through the inlet particle separator, small-diameter dust particles still enter the engine and move within the engine along with the airflow. These particles not only impact the blade surfaces with the main airflow, causing abrasion and deposition, but also enter the turbine rotor cooling system through the air system, where they erode the pre-swirl nozzle assembly at high speed, accumulate in the turbine disk cavity, and deposit and block the turbine blade cooling channels. These effects have a significant negative impact on the engine's service life, performance, and safe operation.

[0003] Flow deflectors are widely used in the internal structural design of aero-engines. Different distributions of flow deflectors can induce various complex flow phenomena, such as vortices, secondary flows, and flow reattachment, altering the transport and deposition characteristics of particles within the engine and achieving separation of microparticles from the incoming flow. In a typical aero-engine turbine disk structure, sand-laden cooling air introduced from before the compressor enters the rotor disk through the inlet, then is depressurized and accelerated by pre-swirl nozzles before entering the rotor blades through the inlet to cool the turbine blades. Compared to disk structures, the rotor blade cavity is more complex and confined, making the problem of sand and dust particle deposition and blockage in the internal cooling channels and film cooling pores more prominent, and the reduction in turbine rotor blade life due to cooling failure more severe. Summary of the Invention

[0004] This invention addresses the problems of existing turbulence structures, which employ a trial-and-error exhaustive design method, resulting in low design efficiency due to repeated geometric modifications. Furthermore, unreasonable design parameters for turbulence rib spacing, distribution, quantity, and structure can lead to excessive drag loss and insufficient cooling airflow. Additionally, turbulence structures suffer from blockage, corrosion, and wear of internal cooling channels caused by particulate matter. The internal cooling channels of turbine blades are smaller than those of the stator disk, making them more susceptible to the adverse effects of particulate matter deposition. The blockage of internal cooling channels and film cooling holes by sand and dust particles is more pronounced, leading to a more severe reduction in turbine rotor blade lifespan due to cooling failure.

[0005] To solve the above-mentioned technical problems, the present invention is achieved through the following technical solution: Option 1: This invention proposes a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotating and stationary disk cavity of an aero-engine. The structure includes an air collection cavity, an air inlet, a rotating and stationary disk cavity, an annular turbulence rib, and a pre-swirl nozzle. After the particulate-containing airflow enters the gas collection chamber, it impacts the target surface through the air inlet. Annular turbulence ribs are arranged downstream of the stagnation point where the axis of the air inlet intersects with the impact surface of the rotating disk cavity, and on the outer wall of the rotating disk cavity. The annular turbulence ribs are arranged inside the rotating disk cavity to complete the switching of airflow between the rotating and stationary components within the system. The pre-swirl nozzle is used to deflect the airflow direction, changing it from axial motion to circumferential motion.

[0006] Option 2: A design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero-engine. The method is based on the structure described in Option 1 and includes the following steps: S1. Obtain the characteristic geometric parameters of the annular rib, including the rib height, rib width, rib spacing, and number of ribs; S2. Within the allowable range of characteristic geometric parameters, change the design values ​​of characteristic geometric parameters to construct the experimental point sample space; S3. By setting the height and width parameters of the annular ribs, the structural parameters describing the turbulence ribs are obtained through iterative solution. Geometric modeling and mesh generation are then performed to solve the three-dimensional compressible fluid continuity equation, momentum equation, and energy equation for the rotating-static disk cavity, thereby obtaining the basic flow field distribution characteristics of the rotating-static disk cavity at different sample points. S4. Solve for discrete phase considering drag force, Saffman lift force, pressure gradient force and thermophoretic force, and add a discrete random walk model to simulate the effect of turbulent fluctuations on the motion trajectory. S5. When particles collide with the surface of the component, the critical velocity model is used to determine whether the particles adhere to the wall or separate, and the shear stripping effect of the mainstream on the sediment is considered. S6. Establish a surrogate model for the particle deposition rate, flow loss and structural parameters in the rotating plate cavity; conduct numerical simulations by increasing the number of experimental sample points and verify the results predicted by the surrogate model. If the accuracy of the surrogate model is less than the set value, increase the number of sample points and re-establish the surrogate model until the accuracy of the surrogate model meets the design requirements.

[0007] Furthermore, in a preferred embodiment, S6 further includes a step of using a multi-objective optimization algorithm to find the design value of the geometric parameters of the turbulence rib that satisfies the optimization objectives, under the optimization objectives of ensuring that the flow resistance loss does not exceed the limit value and that the deposition rate in the cavity of the static system is the highest.

[0008] Furthermore, in a preferred embodiment, S2 further includes a step of changing the design value of the characteristic geometric parameters, which involves using the particle deposition rate η and the minimum pressure loss coefficient Cp in the rotating disk cavity as optimization objective functions to conduct multi-objective optimization research.

[0009] Furthermore, a preferred embodiment is provided, wherein the calculation method for the particle deposition rate η and the minimum pressure loss coefficient Cp within the rotating disk cavity is as follows: (1) (2) in, m d It refers to the sediment mass, in g; m inj It is the mass of the incident particle, g; P inlet It is the total inlet pressure, Pa; P outlet It is the total pressure at the outlet, in Pa.

[0010] Furthermore, a preferred embodiment is provided in which the solution of the three-dimensional compressible fluid continuity equation, momentum equation, and energy equation in the rotating-stationary system disk cavity in S3 is based on the Reynolds-averaged method and coupled. k-ω The SST turbulence model was obtained.

[0011] Furthermore, a preferred embodiment is provided in which the drag force, Saffman lift, pressure gradient force, and thermophoretic force in the discrete phase are calculated using the Lagrange method in S4.

[0012] Furthermore, in a preferred embodiment, the criterion for determining whether particles adhere to the wall or separate in S5 using a critical velocity model is as follows: When the normal velocity of a particle impacting the wall of an object is higher than the critical velocity, the particle bounces off the wall and re-enters the flow field with a certain rebound velocity to continue moving until the next impact or leaving the computational domain. Particles only deposit when their normal impact velocity is below the critical velocity. Simultaneously, considering the stripping effect of the mainstream on particles after deposition, when the shear stress exerted by the mainstream on the sediment is greater than the adhesive force on the particles, the sediment will be stripped from the object surface. The above deposition and separation models are implemented using the embedded UDF function of Fluent software.

[0013] Option 3: A computer-readable storage medium storing a computer program that, when executed by a processor, implements the steps of the method described in Option 2.

[0014] Option 4: A computer device, including a memory and a processor, wherein the memory stores a computer program, and when the processor runs the computer program stored in the memory, the processor executes the method described in Option 2.

[0015] The advantages of this invention are: This invention proposes a high-efficiency dust accumulation structure and design method for non-uniformly arranged baffles within the stator disk cavity of an aero-engine. By arranging baffles on the impact target surface within the stator disk cavity, the flow field distribution characteristics are altered. Utilizing the lifting region of the airflow in front of the baffles and the recirculation region behind the baffles, the number of collisions between particles and the wall is increased, causing some particles to separate from the incoming flow, while others deposit in front of the baffles, ultimately resulting in more particles being deposited inside the stator disk cavity. This reduces the particulate matter content entering the internal cooling channel of the turbine blade, mitigating problems such as blockage, corrosion, and wear caused by particulate matter. The internal cooling channel of the turbine blade is smaller than the stator disk cavity and is more sensitive to the adverse effects of particulate matter deposition. This invention reduces the impact of particulate matter deposition on the turbine blade to a certain extent, ensuring the unobstructed flow of the internal cooling channel for a longer period and improving the stable operating time of the turbine blade under high-temperature environments.

[0016] This invention discloses a high-efficiency dust accumulation structure and design method for non-uniformly arranged turbulence ribs within the rotor-stationary disk cavity of an aero-engine. The turbulence structure alters the distribution characteristics of the cooling airflow field, promoting the deposition of sand and dust particles within the rotor-stationary disk cavity. This reduces the amount of sand and dust entering the inlet of the turbine blade's internal flow channel, effectively lowering the amount of sand and dust deposited within the rotor blade cavity and reducing the risk of blockage. The sand and dust particles accumulated in the pre-spinning disk cavity can ultimately be discharged through the sand discharge holes.

[0017] This invention is also applicable to the field of a non-uniform turbulence rib dust accumulation structure design method that improves the particle deposition rate in the static cavity. Attached Figure Description

[0018] Figure 1 This is a flowchart of a design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotating and stationary disk cavity of an aero-engine, as described in Embodiment 2.

[0019] Figure 2 This is a schematic diagram of a high-efficiency turbulence rib dust accumulation structure with non-uniform arrangement in the rotor-stationary disk cavity of an aero-engine, as described in Embodiment 1.

[0020] Figure 3 This is a diagram showing the distribution of stagnation points within the rotating disk cavity as described in Implementation Method Eleven.

[0021] Wherein, (a) is a schematic diagram of the definition of the stagnation point; (b) is a schematic diagram of the distribution location of the stagnation point; gas collection chamber 1, air inlet 2, rotating stationary disc chamber 3, annular turbulence rib 4, pre-swirl nozzle 5.

[0022] Figure 4 This is a particle velocity distribution diagram inside the rotating disk cavity as described in Embodiment Eleven.

[0023] Among them, (a) is a schematic diagram of the distribution of particles with a velocity of 1 μm; (b) is a schematic diagram of the distribution of particles with a velocity of 5 μm; (c) is a schematic diagram of the distribution of particles with a velocity of 10 μm; and (d) is a schematic diagram of the distribution of particles with a velocity of 20 μm.

[0024] Figure 5 This is a schematic diagram comparing the particle deposition rate inside the disk cavity after different non-uniform turbulence ribs are arranged in the typical static disk cavity structure described in Implementation Method Eleven.

[0025] Figure 6 This is a flow line distribution diagram of the disk cavity in the high-efficiency dust accumulation structure design method for non-uniformly arranged turbulence ribs in the rotating and stationary disk cavity of an aero-engine, as described in Embodiment Eleven.

[0026] Among them, (a) is a streamline distribution diagram of a typical disk cavity; (b) is a streamline distribution diagram of a disk cavity with one annular baffle rib; and (c) is a streamline distribution diagram of a disk cavity with two annular baffle ribs. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them.

[0028] Implementation Method 1: This implementation method proposes a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotating and stationary disk cavity of an aero-engine. The structure includes an air collection cavity 1, an air inlet 2, a rotating and stationary disk cavity 3, an annular turbulence rib 4, and a pre-swirl nozzle 5. After the particulate-containing airflow enters the air collection chamber 1, it impacts the target surface through the air inlet 2. Annular turbulence ribs 4 are arranged downstream of the stagnation point where the axis of the air inlet 2 intersects with the impact target surface of the rotating and stationary disk cavity 3, and on the outer wall of the rotating and stationary disk cavity 3. The annular turbulence ribs 4 are arranged inside the rotating and stationary disk cavity 3 to complete the switching of airflow between the rotating and stationary components within the system. The pre-swirl nozzle 5 is used to deflect the airflow direction, changing it from axial motion to circumferential motion.

[0029] Implementation Method 2: This implementation method proposes a design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs within the rotor-stationary disk cavity of an aero-engine. The method is based on the structure described in Implementation Method 1 and includes the following steps: S1. Obtain the characteristic geometric parameters of the annular rib 4, including the rib height, rib width, rib spacing, and number of ribs; S2. Within the allowable range of characteristic geometric parameters, change the design values ​​of characteristic geometric parameters to construct the experimental point sample space; S3. By setting the height and width parameters of the annular ribs, the structural parameters describing the turbulence ribs are obtained through iterative solution. Geometric modeling and mesh generation are then performed to solve the three-dimensional compressible fluid continuity equation, momentum equation, and energy equation of the rotating-static disk cavity, thereby obtaining the basic flow field distribution characteristics of the rotating-static disk cavity at different sample points. S4. Solve for discrete phase considering drag force, Saffman lift force, pressure gradient force and thermophoretic force, and add a discrete random walk model to simulate the effect of turbulent fluctuations on the motion trajectory. S5. When particles collide with the surface of the component, the critical velocity model is used to determine whether the particles adhere to the wall or separate, and the shear stripping effect of the mainstream on the sediment is considered. S6. Establish a surrogate model for the particle deposition rate, flow loss and structural parameters in the rotating static disk cavity 3; conduct numerical simulation by increasing the number of experimental sample points and verify the results predicted by the surrogate model. If the accuracy of the surrogate model is less than the set value, increase the number of sample points and re-establish the surrogate model until the accuracy of the surrogate model meets the design requirements.

[0030] Implementation Method 3: This implementation method further defines the design method for the high-efficiency turbulence rib dust accumulation structure with non-uniform arrangement in the rotating and stationary disk cavity of the aero-engine described in Implementation Method 2. S6 also includes the step of using a multi-objective optimization algorithm to find the design value of the turbulence rib geometric parameters that meet the optimization objectives, under the optimization objectives of ensuring that the flow resistance loss does not exceed the limit value and that the deposition rate in the rotating and stationary disk cavity 3 is the highest.

[0031] Implementation Method 4: This implementation method further defines the design method of high-efficiency turbulence rib dust accumulation structure with non-uniform arrangement in the rotating and stationary disk cavity of the aero-engine described in Implementation Method 2. In S2, changing the design value of characteristic geometric parameters also includes the step of changing the particle deposition rate η and the minimum pressure loss coefficient Cp in the rotating and stationary disk cavity 3 as the optimization objective function to carry out multi-objective optimization research.

[0032] Implementation Method 5: This implementation method further defines the design method for the high-efficiency turbulence rib dust accumulation structure with non-uniform arrangement in the rotating and stationary disk cavity of an aero-engine described in Implementation Method 4. The calculation methods for the particle deposition rate η and the minimum pressure loss coefficient Cp in the rotating and stationary disk cavity 3 are as follows: (1) (2) in, m d It refers to the sediment mass, in g; m inj It is the mass of the incident particle, g; P inlet It is the total inlet pressure, Pa; P outlet It is the total pressure at the outlet, in Pa.

[0033] Implementation Method Six: This implementation method further defines the design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs within the rotor-stationary disk cavity of an aero-engine described in Implementation Method Four. In S3, the solution of the three-dimensional compressible fluid continuity equation, momentum equation, and energy equation of the rotor-stationary disk cavity 3 is based on the Reynolds-averaged method and coupled. k-ω The SST turbulence model was obtained.

[0034] Implementation Method Seven: This implementation method further defines the design method for the high-efficiency dust accumulation structure of non-uniformly arranged turbulence ribs in the rotating and stationary disk cavity of the aero-engine described in Implementation Method Two. In S4, the discrete phase is solved by considering the drag force, Saffman lift, pressure gradient force and thermophoretic force, which are calculated by the Lagrange method.

[0035] Implementation Method Eight: This implementation method further defines the design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero-engine described in Implementation Method Two. In S5, the criterion for determining whether particles adhere to the wall or separate is based on the critical velocity model: When the normal velocity of a particle impacting the wall of an object is higher than the critical velocity, the particle bounces off the wall and re-enters the flow field with a certain rebound velocity to continue moving until the next impact or leaving the computational domain. Particles only deposit when their normal impact velocity is below the critical velocity. Simultaneously, considering the stripping effect of the mainstream on particles after deposition, when the shear stress exerted by the mainstream on the deposit is greater than the adhesive force on the particles, the deposit will be stripped from the object surface. IX. This embodiment proposes a computer-readable storage medium storing a computer program that, when executed by a processor, implements the steps of the method described in any one of embodiments two to eight. Implementation Method 10: This implementation method provides a computer device, including a memory and a processor. The memory stores a computer program. When the processor runs the computer program stored in the memory, the processor executes the method described in any one of Implementation Methods 2 to 8.

[0036] Implementation Method Eleven: This implementation method provides an example, which is used to explain the above-described implementation methods one through eight. The specific example is as follows: See Figures 1 to 6 This embodiment describes a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs within the rotating-stationary disk cavity of an aero-engine. The main function of the pre-swirl nozzle is to deflect the airflow direction, shifting it from axial motion to predominantly circumferential motion. The main function of the pre-swirl cavity is to facilitate the switching of airflow between the rotating-stationary components within the system. The structural characteristics of the annular turbulence ribs are parameterized to obtain their characteristic geometric parameters (such as rib height, rib width, rib spacing, and number of ribs). Within the allowable range of geometric parameters, the design values ​​of the geometric parameters were changed to construct a sample space for test points. The parameters describing the turbulent rib structure were obtained by iteratively solving for the rib height and rib width parameters. Geometric modeling and mesh generation were then performed, and the continuity equation, momentum equation, and energy equation of the continuous phase of the rotating-stationary disk cavity structure were solved to obtain the basic flow field distribution characteristics of the rotating-stationary disk cavity at different sample points. The discrete phase solution considered the influence of drag force, Saffman lift, pressure gradient force, and thermophoretic force on particle motion.

[0037] To simulate the impact of turbulent fluctuations on the motion trajectory, a discrete random walk model was added. When particles collide with the component surface, a critical velocity model was used to determine whether particles adhered to the wall or separated, and the shear stripping effect of the mainstream on the deposits was considered. A surrogate model was established to manage particle deposition rate, flow loss, and structural parameters within the stabilization chamber. Numerical simulations were performed by increasing the number of experimental sample points, and the results predicted by the surrogate model were validated. If the accuracy of the surrogate model was less than the set value, the number of sample points was increased, and the surrogate model was re-established until the accuracy of the surrogate model met the design requirements.

[0038] Further optimization is conducted under the objectives of ensuring that the flow resistance loss is less than or equal to the limit and maximizing the deposition rate within the rotor blade cavity structure. A multi-objective optimization algorithm is then used to find the optimal geometric parameters of the turbulence ribs that satisfy the optimization goals. This method maximizes the use of the turbulence ribs to alter the cooling airflow field distribution characteristics, promoting the deposition of sand and dust particles within the rotor blade cavity. This achieves efficient particle deposition within the cavity, effectively reducing the amount of sand and dust deposited and the risk of blockage in the rotor blade cavity.

[0039] This example demonstrates a design method for a highly efficient turbulence-accumulating dust structure with non-uniform arrangement within the rotor-stationary disk cavity of an aero-engine. Specifically, it involves placing turbulence ribs on an impact target surface within the rotor-stationary disk cavity and optimizing the geometric and layout parameters of these ribs. The multi-objective optimization study was conducted using ISIGHT software, which organically integrates four mathematical algorithms: design of experiments, approximate modeling, exploratory optimization, and quality design, forming a unified solution. The turbulence rib structure was selected as the optimization object. The influence of the structural and layout parameters of the turbulence ribs on the particle deposition rate and flow resistance characteristics within the rotor-stationary disk cavity was analyzed to determine key influencing parameters, which were then used as design variables for optimization. Upper and lower intervals for these variables were given, with the particle deposition rate within the rotor-stationary disk cavity as the primary factor. η (Equation 1) Minimum pressure loss coefficient Cp Equation 2 is used as the objective function to conduct multi-objective optimization research.

[0040] (1) (2) in,m d It refers to the sediment mass, in g; m inj It is the mass of the incident particle, g; P inlet It is the total inlet pressure, Pa; P outlet It is the total pressure at the outlet, in Pa.

[0041] Numerical calculations were performed in the commercial CFD software ANSYS FLUENT. Unigraphics NX was used to model the rotating-stationary disk cavity structure. Fluent Meshing was used to generate a non-mechanical mesh for the fluid domain, with local refinement near the wall. The continuous phase was modeled using a Reynolds-averaged (RANS) method and coupled with... k-ω The SST turbulence model solves the three-dimensional continuity, momentum, and energy equations for compressible fluids, obtaining the flow field distribution characteristics of the internal structure of the rotating-stationary disk cavity.

[0042] Among them, the continuity equation is:

[0043] Energy equation:

[0044] Momentum equation:

[0045] The discrete phase is solved using the Lagrange method, and the particle trajectories are obtained by tracking the motion of dispersed particles in the continuous phase. The particle trajectories are solved by analyzing the balance of various forces acting on the particles, considering drag force, Saffman lift, pressure gradient force, and thermophoresis. When particles impact the surface of a component, a deposition model is used to determine whether the particles adhere to the surface or separate. This invention uses a critical velocity model for this determination. The criterion for particle deposition is: when the normal velocity of a particle impacting the object's wall is higher than the critical velocity, the particle rebounds from the wall and re-enters the flow field at a certain rebound velocity to continue moving until the next impact or leaving the computational domain; only when the normal impact velocity of the particle is lower than the critical velocity does deposition occur. Simultaneously, the stripping effect of the mainstream on the particles after deposition is considered; when the shear stress exerted by the mainstream on the deposit is greater than the adhesive force on the particles, the deposit will be stripped from the object's surface. The above deposition and separation models are implemented using the embedded UDF function of Fluent software.

[0046] To visually demonstrate the disc cavity structure, a 1 / 6 section of the entire ring is selected for analysis. It consists of an air collection chamber 1, an air inlet 2, a rotating and stationary disc cavity 3, an annular turbulence rib 4, and a pre-swirling nozzle 5. The annular turbulence rib is arranged within the rotating and stationary disc cavity.

[0047] In this embodiment, the particle-containing inflow enters the inlet chamber and impacts the target surface through the inlet hole 2, subsequently forming a wall jet in all directions and creating a crossflow along the flow direction. The crossflow is concentrated at the target surface, and its direction is consistent with the mainstream direction. The annular ribs 5 enhance the disturbance of the particle-containing airflow, suppress the further development of the crossflow, induce vortices, and lift the airflow. During the airflow lifting process, the number of collisions between particles and the annular ribs increases. Due to the obstruction effect of the annular ribs, the energy loss of the particles increases, and the particle velocity decreases. More particles have a normal velocity lower than the critical capture velocity of the wall when colliding with it, and thus deposit on the wall. Furthermore, during the flow development, particles continuously collide with the inner wall of the stator disk. When particles collide with the wall but do not deposit, their velocity and momentum continuously decrease. The velocity of the particles continuously decreases before reaching the pre-spinning section. Placing the annular ribs at a greater distance from the stagnation point can further reduce the particle velocity, thereby achieving a higher deposition rate.

[0048] Those skilled in the art will understand that the above description is merely a preferred embodiment of the present invention, and the features described in the various embodiments and / or claims of this disclosure can be combined or combined in various ways, even if such combinations or combinations are not explicitly described in this disclosure. This is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

[0049] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention. Clearly, those skilled in the art can make various alterations and modifications to the invention without departing from its spirit and scope. Thus, if these modifications and modifications of the invention fall within the scope of the claims and their equivalents, the invention is also intended to include these modifications and modifications.

Claims

1. A high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs within the rotor-stationary disk cavity of an aero-engine, characterized in that, The structure includes an air collection chamber (1), an air inlet (2), a rotating and stationary disc chamber (3), an annular turbulence rib (4), and a pre-swirl nozzle (5). After the particulate-containing airflow enters the gas collection chamber (1), it impacts the target surface through the air inlet (2). Annular turbulence ribs (4) are arranged downstream of the stagnation point where the axis of the air inlet (2) intersects with the impact target surface of the rotating plate cavity (3) and on the outer wall of the rotating plate cavity (3). The annular turbulence ribs (4) are arranged inside the rotating plate cavity (3) to complete the switching of the airflow between the rotating and stationary components in the system. The pre-rotating nozzle (5) is used to deflect the airflow direction, changing it from axial motion to circumferential motion.

2. A design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero-engine, characterized in that, The method is implemented based on the structure described in claim 1, and the method includes the following steps: S1. Obtain the characteristic geometric parameters of the annular rib (4), including the rib height, rib width, rib spacing, and number of ribs; S2. Within the allowable range of characteristic geometric parameters, change the design values ​​of characteristic geometric parameters to construct the experimental point sample space; S3. By setting the height and width parameters of the annular ribs, the parameters describing the turbulence rib structure are obtained through iterative solution. Geometric modeling and mesh generation are performed to solve the three-dimensional compressible fluid continuity equation, momentum equation and energy equation of the rotating-static disk cavity (3) and obtain the basic flow field distribution characteristics of the rotating-static disk cavity at different sample points. S4. Solve for discrete phase considering drag force, Saffman lift force, pressure gradient force and thermophoretic force, and add a discrete random walk model to simulate the effect of turbulent fluctuations on the motion trajectory. S5. When particles collide with the surface of the component, the critical velocity model is used to determine whether the particles adhere to the wall or separate, and the shear stripping effect of the mainstream on the sediment is considered. S6. Establish a proxy model for particle deposition rate, flow loss and structural parameters in the rotating static disk cavity (3); conduct numerical simulation by increasing the number of test sample points and verify the results predicted by the proxy model. If the accuracy of the proxy model is less than the set value, increase the number of sample points and re-establish the proxy model until the accuracy of the proxy model meets the design requirements.

3. The design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero-engine according to claim 2, characterized in that, S6 also includes the step of using a multi-objective optimization algorithm to find the design value of the geometric parameters of the turbulence rib that meets the optimization objectives, under the optimization objectives of ensuring that the flow resistance loss does not exceed the limit value and the deposition rate in the static system cavity (3) is the highest.

4. The design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero-engine according to claim 2, characterized in that, In S2, changing the design values ​​of characteristic geometric parameters also includes the steps of changing the particle deposition rate η and the minimum pressure loss coefficient Cp in the rotating static disk cavity (3) as the optimization objective function to carry out multi-objective optimization research.

5. The design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero-engine according to claim 4, characterized in that, The calculation methods for particle deposition rate η and minimum pressure loss coefficient Cp in the static disk cavity (3) are as follows: (1) (2) in, m d It refers to the sediment mass, in g; m inj It is the mass of the incident particle, g; P inlet It is the total inlet pressure, Pa; P outlet It is the total pressure at the outlet, in Pa.

6. The design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero-engine according to claim 2, characterized in that, Solving the three-dimensional compressible fluid continuity equation, momentum equation, and energy equation in the rotating stationary disk cavity (3) based on the Reynolds-averaged method and coupled k-ω The SST turbulence model was obtained.

7. The design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero-engine according to claim 2, characterized in that, In S4, the discrete phase is solved by considering the drag force, Saffman lift, pressure gradient force, and thermophoretic force, which are calculated using the Lagrange method.

8. The design method for a high-efficiency dust accumulation structure with non-uniformly arranged turbulence ribs in the rotor-stationary disk cavity of an aero-engine according to claim 2, characterized in that, In S5, the criteria for determining whether particles adhere to the wall or separate using the critical velocity model are as follows: When the normal velocity of a particle impacting the wall of an object is higher than the critical velocity, the particle bounces off the wall and re-enters the flow field with a certain rebound velocity to continue moving until the next impact or leaving the computational domain. Particles only deposit when their normal impact velocity is below the critical velocity. Simultaneously, considering the stripping effect of the mainstream on particles after deposition, when the shear stress exerted by the mainstream on the sediment is greater than the adhesive force on the particles, the sediment will be stripped from the object surface. The above deposition and separation models are implemented using the embedded UDF function of Fluent software.

9. A computer device, including a memory and a processor, characterized in that, The memory stores a computer program, and when the processor runs the computer program stored in the memory, the processor performs the method described in any one of claims 2-8.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the steps of the method according to any one of claims 2-8.

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