Design method and system of pressure relief vortex reduction device, electronic equipment and storage medium

Abstract

The invention discloses a design method and system of a pressure relief and vortex reduction device, electronic equipment and a storage medium, the axial arrangement position of the pressure relief and vortex reduction device is designed according to the air entraining requirement, and it is guaranteed that the static pressure of the air entraining position meets the sealing air entraining pressure requirement. The overall dimension design of the pressure-relief vortex-reduction device is carried out under the conditions of structural dimension constraint and exhaust outlet static pressure constraint, miniaturization design is achieved on the premise that outlet static pressure meets index requirements, and the pressure-relief vortex-reduction device is compact in structure, convenient to install, light in weight, small in influence on dynamic characteristics of a rotor and high in reliability. And the risk of vibration during high-speed rotation of the rotor is reduced. According to the pneumatic design of the pressure relief vortex reducer adopting the through type contraction channel, the outlet static pressure is reduced by increasing the gas speed, so that the purpose of pressure relief is achieved, the reverse pressure gradient of the contraction channel is small, generation and development of flow separation can be effectively inhibited, the total pressure loss of flow is greatly reduced, the air entraining flow is small, and the service life is long. And the influence on the power of the engine is small.

Description

Technical Field

[0001] The present invention relates to the technical field of vortex reducer design, and in particular to a design method and system of a pressure relief vortex reducer, an electronic device, and a computer-readable storage medium. Background Art

[0002] Small and medium-sized aviation gas turbine engines have the design characteristics of small size, high speed and high thermal cycle parameters. The high-temperature components, high-speed rotating components and rotor-stator components inside the engine are designed with complex flow paths to bleed air from the main flow of the cold end compressor for sealing or cooling as needed, such as dynamic sealing of lubricating oil in the bearing cavity, air film cooling on the surface of the gas turbine blades, dynamic sealing of the grate teeth between the two cavities, etc. This requires the introduction of appropriate pressure with little impact on the main flow, and meets the sealing or cooling requirements of related components while overcoming the resistance along the way. At present, the conventional design is to use the main flow to directly open holes for bleed air, which puts forward high requirements on the selection of the bleed position. It is easy to cause the bleed pressure to be too large or too small when it is too close to the back or the front, resulting in an imbalance of the dynamic sealing pressure difference and failure of the seal. In addition, because the holes are opened on the hub flow channel surface, it is necessary to pass through the rotor spoke plate and then flow to both sides. Moreover, the bleed air speed after passing through the expansion disc cavity is small and the bleed air pressure is large. The airflow loss when bleeding in the required direction is large, and the amount of bleed air is large, resulting in a reduction in the gas compressed in the main flow of the compressor, resulting in a reduction in the output power of the engine. In addition, the prior art also uses tubular, fin-type or guide tube-type vortex reducers for air induction, but the existing vortex reducers have a large number of parts, complex assembly relationships, complex structural designs, inconvenient installation and disassembly, and increased flow losses. In addition, due to the large mass of the vortex reducer, the engine rotor dynamics problem is more complicated, and vibration problems are likely to occur during high-speed rotation, posing a safety hazard. Summary of the invention

[0003] The present invention provides a design method and system for a pressure relief vortex reducer, an electronic device, and a computer-readable storage medium, which can ensure that the static pressure at the bleed air position meets the sealing bleed air pressure requirement, and realize a miniaturized design under the premise of ensuring that the outlet static pressure meets the index requirements. The pressure relief vortex reducer has a compact structure, is easy to install, and is light in weight. It has little effect on the dynamic characteristics of the rotor, reduces the risk of vibration when the rotor rotates at high speed, and greatly reduces the total pressure loss of the flow. The bleed air flow rate is small, and the effect on the engine power is small.

[0004] According to one aspect of the present invention, a design method of a pressure relief vortex reducer is provided, comprising the following contents:

[0005] Design the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand;

[0006] Design the outline dimensions of the pressure relief vortex reducer under the constraints of structural dimensions and exhaust outlet static pressure.

[0007] The aerodynamic design of the pressure relief and vortex reducer is carried out using a through-type contraction channel, and the aerodynamic performance of the aerodynamic design scheme is evaluated;

[0008] The structural design of the pressure relief vortex reducer is carried out based on the outline dimension design scheme and the aerodynamic design scheme, and the strength evaluation of the structural design scheme is carried out.

[0009] Furthermore, the process of determining the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand includes the following contents:

[0010] Determine the static pressure requirement for sealing and the bleed air flow requirement for cooling according to the design status of the engine air system;

[0011] Perform numerical simulation on the engine compressor to obtain the static pressure distribution data along the hub flow path surface;

[0012] Based on the static pressure requirement and the static pressure distribution data along the hub flow path surface, the air bleed position is determined on the principle of meeting the static pressure requirement and retaining the static pressure margin. The air bleed position needs to select the meshing center of the end teeth of the adjacent rotor disk to obtain the static temperature of the hub flow path surface corresponding to the air bleed position.

[0013] Furthermore, the profile dimension design includes the axial profile width design, the radial inlet outer profile dimension design and the radial exhaust inner profile dimension design, wherein the radial exhaust inner profile dimension of the pressure relief vortex reducer is designed based on the following formula:

[0014]

[0015] And R 内 ≤min(R3,R4,...)

[0016] Among them, R 内 represents the inner diameter of the air flow channel of the pressure relief vortex reducer in the radial direction, k2 represents the total pressure recovery coefficient of the pressure relief vortex reducer, P Sin Indicates the static pressure at the intake position, P Sout Indicates the static pressure at the exhaust outlet, P Sout ≥P S0 , P S0 Indicates the static pressure required for sealing, T Sin represents the static temperature of the hub flow path surface corresponding to the bleed air position, R represents the gas constant, α represents the circumferential angular occupation of the air flow channel, m0 represents the bleed air flow demand required for cooling designed by the air system, R3 and R4 represent the inner diameters of the first-stage compressor rotor disk spoke and the second-stage compressor rotor disk spoke in the radial direction, respectively.

[0017] Furthermore, the contents of the aerodynamic design include the axial width of the airflow channel, the number of airflow channels and the shape of the airflow channel.

[0018] Furthermore, the design process of the number of airflow channels includes the following:

[0019] The wall thickness inner diameter arc length of the spacer rib is determined based on the strength requirement, and the wall thickness circumferential angle of the spacer rib is calculated based on the wall thickness inner diameter arc length and the radial exhaust inner contour size;

[0020] Assuming that the number of airflow channels is n, the circumferential angle of the airflow channels is calculated based on the circumferential angle of the wall thickness and the number of airflow channels;

[0021] The air intake circumferential length of the air flow channel is calculated based on the circumferential angle of the air flow channel and the radial air intake outer contour size;

[0022] It is determined whether the air intake circumferential length of the air flow channel can completely cover the circumferential length of at least one end tooth meshing gap and leave a circumferential margin. If this requirement is met, the number of air flow channels is determined to be n.

[0023] Furthermore, during the aerodynamic performance evaluation process, when the bleed air flow rate is too large, the axial width of the air flow channel is reduced and / or the number of air flow channels is reduced while ensuring that the strength requirements are met; when the bleed air flow rate is too small, the axial width of the air flow channel is increased and / or the number of air flow channels is increased while ensuring that the strength requirements are met, until the bleed air flow rate meets the requirements.

[0024] Furthermore, during the structural design process, a stopper is designed on the air inlet side of the spacer rib. The stopper needs to be partially inserted into the end tooth meshing gap and the insertion depth must not be less than a preset value.

[0025] In addition, the present invention also provides a design system for a pressure relief vortex reducer, which adopts the design method as described above and comprises:

[0026] Position design module, used to design the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand;

[0027] The dimension design module is used to design the outline dimension of the pressure relief vortex reducer under the conditions of structural dimension constraints and exhaust outlet static pressure constraints;

[0028] The aerodynamic design module is used to perform aerodynamic design of a pressure relief vortex reducer using a through-type contraction channel and to evaluate the aerodynamic performance of the aerodynamic design scheme;

[0029] The structural design module is used to carry out the structural design of the pressure relief vortex reducer based on the outline dimension design scheme and the aerodynamic design scheme, and to carry out strength evaluation of the structural design scheme.

[0030] In addition, the present invention also provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the above method by calling the computer program stored in the memory.

[0031] In addition, the present invention also provides a computer-readable storage medium for storing a computer program for designing a pressure relief vortex reducer, wherein the computer program executes the steps of the method described above when running on a computer.

[0032] The present invention has the following beneficial effects:

[0033] The design method of the pressure relief vortex reducer of the present invention designs the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand, and ensures that the static pressure at the bleed air position meets the sealing bleed air pressure demand. At the same time, the outline size design of the pressure relief vortex reducer is carried out under the conditions of structural size constraints and exhaust outlet static pressure constraints, and a miniaturized design is achieved under the premise of ensuring that the outlet static pressure meets the index requirements. The pressure relief vortex reducer has a compact structure, is easy to install, and is lightweight. It has little effect on the dynamic characteristics of the rotor, and reduces the risk of vibration when the rotor rotates at high speed. In addition, a through-type contraction channel is used for the aerodynamic design of the pressure relief vortex reducer, and the outlet static pressure is reduced by increasing the gas velocity, thereby achieving the purpose of pressure relief. The reverse pressure gradient of the contraction channel is small, which can effectively suppress the generation and development of flow separation, thereby greatly reducing the total pressure loss of the flow, and the bleed air flow rate is small, which has little effect on the engine power.

[0034] In addition, the design system of the pressure relief vortex reducer of the present invention also has the above advantages.

[0035] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0037] Figure 1 It is a flow chart of a design method of a pressure relief vortex reducer according to a preferred embodiment of the present invention.

[0038] Figure 2 yes Figure 1 Schematic diagram of the sub-process of step S1 in FIG.

[0039] Figure 3 It is a schematic cross-sectional diagram of the axial arrangement position and design dimensions of the pressure relief and vortex reducer of the preferred embodiment of the present invention.

[0040] Figure 4 It is a schematic diagram of the outline dimension design of a racetrack-shaped pressure relief and vortex reducer according to a preferred embodiment of the present invention.

[0041] Figure 5 It is a schematic diagram of the design of the airflow channel dimensions of the racetrack-shaped pressure relief and vortex reducer of the preferred embodiment of the present invention.

[0042] Figure 6 It is a schematic diagram of the projection shape and size of the airflow channel P of the racetrack-shaped pressure relief and vortex reducer of the preferred embodiment of the present invention.

[0043] Figure 7 It is a flowchart of the process of designing the number of airflow channels according to a preferred embodiment of the present invention.

[0044] Figure 8 It is a flow field schematic diagram obtained by numerically simulating the internal gas flow of a racetrack-shaped pressure relief vortex reducer in a preferred embodiment of the present invention.

[0045] Fig. 9 It is a schematic diagram of the three-dimensional model structure of the pressure relief and vortex reducer designed in the preferred embodiment of the present invention.

[0046] Fig.10 It is a schematic cross-sectional structure diagram of a pressure relief and vortex reducer designed in a preferred embodiment of the present invention.

[0047] Fig.11 It is a cross-sectional schematic diagram of a weight-reducing design of a spoke plate in a preferred embodiment of the present invention.

[0048] Fig.12 It is a cross-sectional schematic diagram of a hollow design of the ribs in a preferred embodiment of the present invention.

[0049] Fig.13 It is a schematic diagram of the module structure of a design system for a pressure relief and vortex reducer according to another embodiment of the present invention. DETAILED DESCRIPTION

[0050] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0051] Reference Figure 1 The preferred embodiment of the present application provides a design method for a pressure relief vortex reducer, comprising the following contents:

[0052] Step S1: designing the axial arrangement position of the pressure relief vortex reducer according to the bleed air requirement;

[0053] Step S2: designing the outline dimensions of the pressure relief vortex reducer under the conditions of structural dimension constraints and exhaust outlet static pressure constraints;

[0054] Step S3: using a through-type contraction channel to perform aerodynamic design of the pressure relief vortex reducer, and performing aerodynamic performance evaluation on the aerodynamic design scheme;

[0055] Step S4: Perform structural design of the pressure relief vortex reducer based on the outline dimension design scheme and the aerodynamic design scheme, and perform strength evaluation on the structural design scheme.

[0056] It can be understood that the design method of the pressure relief vortex reducer of this embodiment designs the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand, and ensures that the static pressure at the bleed air position meets the sealing bleed air pressure demand. At the same time, the contour size design of the pressure relief vortex reducer is carried out under the conditions of structural size constraints and exhaust outlet static pressure constraints, and a miniaturized design is achieved under the premise of ensuring that the outlet static pressure meets the index requirements. The pressure relief vortex reducer has a compact structure, is easy to install, and is light in weight. It has little effect on the dynamic characteristics of the rotor, and reduces the risk of vibration when the rotor rotates at high speed. In addition, a through-type contraction channel is used for the aerodynamic design of the pressure relief vortex reducer. The outlet static pressure is reduced by increasing the gas velocity, thereby achieving the purpose of pressure relief. The reverse pressure gradient of the contraction channel is small, which can effectively suppress the generation and development of flow separation, thereby greatly reducing the total pressure loss of the flow, and the bleed air flow rate is small, which has little effect on the engine power.

[0057] It is understandable that Figure 2 As shown, in step S1, the process of determining the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand includes the following contents:

[0058] Step S11: determining the static pressure requirement for sealing and the bleed air flow requirement for cooling according to the design status of the engine air system;

[0059] Step S12: performing numerical simulation on the engine compressor to obtain static pressure distribution data along the hub flow path surface;

[0060] Step S13: Based on the static pressure requirement and the static pressure distribution data along the hub flow path surface, the air bleed position is determined based on the principle of meeting the static pressure requirement and retaining the static pressure margin. The air bleed position needs to select the meshing center of the end teeth of the adjacent rotor disk to obtain the static temperature of the hub flow path surface corresponding to the air bleed position.

[0061] Specifically, first determine the static pressure P required for sealing based on the engine scheme that has been preliminarily designed and the design status of the engine air system. S0 and the bleed air flow m0 required for cooling. Then, the numerical simulation template (including grid and pre-processing settings) that has been verified by the same type of scheme test is used to perform numerical simulation on the engine compressor to extract the static pressure distribution data along the hub flow path surface. The axial position of the pressure relief vortex reducer is selected based on the principle of satisfying the static pressure and retaining a certain margin, specifically based on the following formula: PSin =k1×P S0 , where P Sin represents the static pressure at the air bleed position, k1 represents the static pressure margin coefficient, and its reference range can be selected from 1.1 to 1.2. Of course, in other embodiments of the present invention, it can also be selected according to actual needs. After determining the selection range of the air bleed position based on the above formula, the end tooth meshing center of the adjacent rotor disk is selected as the final air bleed position within the selection range, and the static temperature T of the hub flow path surface corresponding to the air bleed position is obtained. Sin .

[0062] It can be understood that the requirements for the position of the air intake in the present invention are not high. As long as sufficient static pressure margin is retained, the structure can be formed by the meshing gap formed by the end teeth and the disc cavity formed by the spokes of the rotor disc. The selection is subject to smaller constraints and the design is more flexible. In addition, the meshing gap of the end teeth is used to bleed air, and no additional holes are required. There is no impact on the early design of the flow path parts of the engine, which greatly reduces the workload of changing or adjusting the engine design scheme.

[0063] It can be understood that in step S2, the outline dimension design of the pressure relief vortex reducer includes the axial outline width design, the radial inlet outer outline dimension design and the radial exhaust inner outline dimension design. Specifically, Figure 3 As shown, since the pressure relief vortex reducer is arranged between two adjacent rotor disks and needs to draw air from the meshing gap of the rotor end teeth, in order to ensure assembly, the pressure relief vortex reducer and the blade wheel disc spoke are designed to have a clearance fit relationship in the axial direction. Its axial profile width W and the axial distance W1 between the rotor disks must satisfy the following relationship: W = W1 + δ, δ represents the axial clearance, and the specific value can be designed according to actual needs, in units of mm. In addition, in order to avoid the shaking of the pressure relief vortex reducer, its radial direction must maintain an interference fit relationship with the inner diameter of the rotor end teeth, so its radial air inlet outer profile dimension R 外 The following relationship must be satisfied: R 外 =R2+μ, where R2 represents the inner diameter of the rotor end teeth, and μ represents the radial interference, which can be selected according to the material properties and the minimum deformation at the working environment temperature, and the unit is mm. In addition, in order to reduce the gas flow loss caused by the obstruction of the left and right rotor spokes, the radial exhaust inner contour size R of the pressure relief reducer is 内 The minimum inner diameter of all spokes must not be exceeded. Figure 3 Two-stage axial compressor, R 内 ≤min(R3,R4), while for multi-stage compressors, R 内 ≤min(R3, R4, ...), where R3 and R4 represent the inner diameters of the first-stage compressor rotor disk spoke and the second-stage compressor rotor disk spoke in the radial direction, respectively.

[0064] Optionally, under the above structural dimension constraints, based on the same inlet pressure and airflow channel, the radial dimension of the vortex reducer will also affect the total pressure recovery coefficient of the flow, thereby affecting the static pressure of the exhaust outlet. 外 Optimize the design of radial exhaust inner profile size R when certain 内 , and is modified according to the subsequent aerodynamic performance evaluation simulation results. Specifically, the radial exhaust inner contour dimensions of the pressure relief vortex reducer are designed based on the following formula:

[0065]

[0066] And R 内 ≤min(R3,R4,...)

[0067] Among them, R 内 It represents the inner diameter of the air flow channel of the pressure relief vortex reducer in the radial direction, that is, the radial exhaust inner contour size, and k2 represents the total pressure recovery coefficient of the pressure relief vortex reducer. P Sin Indicates the static pressure at the intake position, P Sout Indicates the static pressure at the exhaust outlet, P Sout ≥P S0 , P S0 Indicates the static pressure required for sealing, T Sin represents the static temperature of the hub flow path surface corresponding to the bleed position, R represents the gas constant, for air, it is 287.06 J / (kg*K), α represents the circumferential angle of the airflow channel, m0 represents the bleed air flow required for cooling of the air system design, R3 and R4 represent the radial inner diameters of the first stage compressor rotor disc and the second stage compressor rotor disc, respectively. Among them, k2 can be taken as 0.995 to design the initial R 内 , and then iterate according to the subsequent aerodynamic performance evaluation simulation results. In addition, for the circumferential angle α of the airflow channel, the value of the number of airflow channels n can be assumed in the early stage. Generally, n ≥ 4 and is an even number, according to the formula The values ​​are taken preliminarily and then revised according to the simulation results of aerodynamic performance evaluation.

[0068] It can be understood that the outline size design of the pressure relief vortex reducer of the present invention not only takes into account the convenience of assembly, but also reduces the gas flow loss, and realizes a miniaturized design under the premise of ensuring that the outlet static pressure meets the index requirements. The pressure relief vortex reducer has a compact structure, is easy to install, and is light in weight. It has little effect on the dynamic characteristics of the rotor, and reduces the risk of vibration when the rotor rotates at high speed. In addition, the static pressure of the exhaust outlet can be adjusted according to demand, and the design is more flexible.

[0069] It can be understood that after completing the outline dimension design of the pressure relief vortex reducer, it is necessary to carry out the aerodynamic design of the pressure relief vortex reducer in combination with the current rotor disk structure. In step S3, the airflow channel of the pressure relief vortex reducer is designed as a through-type contraction channel, and the outlet static pressure is reduced by increasing the gas velocity, that is, the purpose of pressure relief is achieved. At the same time, the small adverse pressure gradient of the contraction channel is also conducive to controlling the generation and development of flow separation vortices during the airflow turning process, thereby reducing the total pressure loss of the flow. Among them, the content of the aerodynamic design includes the axial width of the airflow channel, the number of airflow channels and the shape of the airflow channel.

[0070] Specifically, combined Figures 3 to 6 As shown in the figure, since the inlet of the pressure relief vortex reducer directly utilizes the end tooth meshing gap of the adjacent rotor disk, the axial width of the end tooth meshing gap is the maximum axial distance m1 formed by the root of the end tooth on one side and the root of the matching end tooth, the design value of the axial width m of the airflow channel of the pressure relief vortex reducer must be larger than m1, and the gaps reserved on both sides should be determined according to the high-temperature deformation data of the maximum working state to ensure the conditions for the gas to flow along the steps in all states. Usually, at least (0.5-1.0) mm of gap is reserved on both sides to achieve the gas flow area of ​​the outlet of the end tooth meshing gap of the pressure relief vortex reducer to be aligned with and wrap the gas flow area of ​​the outlet of the end tooth meshing gap, avoiding the additional flow loss caused by the inverted step. In addition, a certain wall thickness t1 and t2 need to be reserved on both sides of the airflow channel. The specific values ​​of the wall thickness t1 and t2 are determined according to the strength evaluation results. The two can be the same or different.

[0071] In addition, if Figure 7 As shown, the design process of the number of airflow channels includes the following:

[0072] Step S31: determining the wall thickness inner diameter arc length of the spacing rib based on the strength requirement, and calculating the wall thickness circumferential angle of the spacing rib based on the wall thickness inner diameter arc length and the radial exhaust inner contour size;

[0073] Step S32: Assuming that the number of airflow channels is n, the circumferential angle occupied by the airflow channels is calculated based on the circumferential angle occupied by the wall thickness and the number of airflow channels;

[0074] Step S33: calculating the air intake circumferential length of the air flow channel based on the circumferential angle of the air flow channel and the radial air intake outer contour size;

[0075] Step S34: determine whether the air intake circumferential length of the airflow channel can completely cover the circumferential length of at least one end tooth meshing gap with a circumferential margin. If this requirement is met, determine the number of airflow channels to be n.

[0076] Specifically, the number of gas flow channels n is usually designed to be an even number in order to achieve circumferential symmetry of gas flow and better rotor dynamics performance. In addition, considering the structural strength, it is necessary to control the circumferential angle β of the wall thickness of the spacing ribs, the circumferential angle α of the gas flow channels, and the arc length L of the wall thickness inner diameter of the spacing ribs. arc Among them, wall thickness inner diameter arc length L arc The length is determined according to the strength requirements, usually not less than 3 mm. The present invention first takes 3 mm as the value, based on the formula: Then, assuming the number of airflow channels n is 6, based on the formula Then, based on the circumferential angle α of the airflow channel and the radial air intake outer contour size R 外 The air intake circumferential length L of the air flow channel is calculated arc外 , the calculation formula is: Since the air intake circumferential length L of the air flow channel arc外 It is necessary to completely cover the circumferential length L of at least one end tooth meshing gap, and generally leave a margin of (0.2-0.6) mm in the circumferential direction to achieve the gas flow range of the pressure relief vortex reducer inlet to align with and wrap the end tooth meshing gap outlet, that is, L arc外 =L+margin, the specific value of the margin can be set according to actual needs, and is not specifically limited here. If this requirement is met, the number of airflow channels n is determined to be an assumed value, that is, n=6. If this requirement is not met, the number of airflow channels n needs to be adjusted. For example, when L arc外 If it is too large, you need to increase the number of airflow channels. arc外 If the L is too small, the number of airflow channels needs to be reduced. In addition, if the full coverage requirement is not met, L arc The value of is corrected.

[0077] In addition, the airflow channel of the pressure relief and vortex reducer adopts a through-type channel with similar inlet and outlet cross-section shapes. The inlet and outlet cross-section shapes can be circular, rectangular, racetrack-shaped, and elliptical. Of course, the airflow channel can also adopt a special-shaped channel, wherein the special-shaped channel refers to the airflow channel whose inlet cross-section shape is not similar to the outlet cross-section shape, for example, the inlet cross-section shape is elliptical and the outlet cross-section shape is circular. Among them, the present invention preferably adopts a racetrack-shaped airflow channel. Compared with a rectangular airflow channel, the racetrack-shaped airflow channel can avoid stress concentration in the corner area while reducing flow separation losses in the corner area. The specific size design can be seen. Figure 6 As shown, the radius of the circumscribed circle of the short side of the runway is r = m / 2, and the projection length of the inlet section P view is: The outlet cross-sectional dimensions are automatically formed after penetrating at the same angle as the inlet cross-sectional dimensions.

[0078] It can be understood that after completing the aerodynamic design, the aerodynamic performance evaluation of the aerodynamic design needs to be carried out. Specifically, a three-dimensional numerical simulation template (including grid and pre-processing settings) that has been verified by experiments is used to perform a three-dimensional aerodynamic numerical simulation of the pressure relief vortex reducer under the given inlet total temperature, total pressure and outlet static pressure conditions required by the air system to evaluate its bleed air flow. If it meets the index requirements given by the engine air system, the aerodynamic design scheme is feasible. Otherwise, according to the difference, it returns to the aerodynamic design process of the pressure relief vortex reducer to redesign the number of airflow channels, the width of the airflow channels or the shape of the airflow channels. Among them, when the bleed air flow is too large, the axial width of the airflow channel and / or the number of airflow channels are reduced while ensuring that the strength requirements are met. When the bleed air flow is too small, the axial width of the airflow channel and / or the number of airflow channels are increased while ensuring that the strength requirements are met, until the bleed air flow meets the requirements. In addition, for special-shaped channels, if the bleed air flow rate is too large, it can be corrected by reducing the outlet exhaust channel area (including increasing the wall thickness to reduce the channel area); if the bleed air flow rate is too small, it can be corrected by increasing the outlet exhaust channel area (including reducing the wall thickness to increase the channel area when the strength standard is met). In addition, the bleed air flow index requirements are: m 引气 ≥m0,k3=m 引气 / m 压气机 , m 引气 represents the bleed air flow rate, m0 represents the bleed air flow rate required for cooling, m 压气机 represents the compressor flow rate, k3 represents the bleed air ratio, which must not exceed the preset value, for example, not more than 1%, otherwise it may cause an increase in engine power loss. If the bleed air ratio is too large, it can be adjusted by increasing the number of air flow channels, reducing the angle occupied by the gas channel, or reducing the cross-sectional area of ​​the channel, and vice versa.

[0079] The inventor of this application also conducted a numerical simulation of the gas flow in the runway-type channel contraction vortex reducer based on a compressor platform of a certain project. The flow field results show that the bleed air flow of the runway-type channel contraction vortex reducer accounts for 0.83% of the compressor intake flow, and the total pressure recovery coefficient is relatively high, reaching 0.998. The bleed air flow and outlet static pressure both meet the design requirements of the engine air system. The simulation results are as follows Figure 8 As shown, it can be seen that the gas flow inside the vortex reducer is good and there is no visible flow separation.

[0080] It can be understood that the present invention adopts a through-type contraction channel for the aerodynamic design of the pressure relief vortex reducer, and reduces the outlet static pressure by increasing the gas velocity, thereby achieving the purpose of pressure relief. The reverse pressure gradient of the contraction channel is small, which can effectively suppress the generation and development of flow separation, thereby greatly reducing the total pressure loss of the flow, and the bleed air flow is small, which has little impact on the engine power. In addition, the bleed air flow is adjustable, and the design is more flexible. In addition, based on the above-mentioned aerodynamic design, non-uniformly thickened fan-shaped spaced ribs are realized, which can further reduce the structure and weight of the pressure relief vortex reducer compared to the existing uniformly thick spaced ribs, which is beneficial to improving the rotor dynamics. At the same time, the air flow channel is simple and easy to process, and can be realized by simple penetrating milling or additive manufacturing technology.

[0081] It can be understood that in step S4, after completing the outline size design and gas design of the pressure relief and vortex reducer, the structural design of the pressure relief and vortex reducer of the final solution can be completed through the three-dimensional modeling software. Fig. 9 As shown in the figure, the internal structure cross-sectional diagram of the pressure relief vortex reducer can be seen Fig.10 As shown, it can be seen that the pressure relief vortex reducer is an integral disc structure. Among them, the specific three-dimensional modeling process belongs to the prior art and will not be repeated here. Optionally, in the process of structural design, a stopper is also designed on the air inlet side of the spacer rib. The stopper needs to be partially inserted into the end tooth meshing gap and the insertion depth must be not less than a preset value, for example, not less than 0.5 mm, to prevent relative rotation between the pressure relief vortex reducer and the rotor disc. It can be understood that the structural design of the pressure relief vortex reducer is simple, adopts an integral design, has a small number of parts, and has good assembly.

[0082] In addition, after completing the structural design of the pressure relief vortex reducer, it is necessary to conduct a strength assessment of the structural design. For example, a three-dimensional numerical simulation template (including mesh, material properties and pre-processing settings) that has been verified by experiments is used to conduct a strength assessment of the pressure relief vortex reducer under given speed, temperature and assembly constraints, and analyze its stress distribution and the yield strength σ under the maximum centrifugal radial stress and average circumferential stress. 0.1 and the ultimate strength σ b The strength reserve coefficient, where the yield strength standard is 0.80σ 0.1 , the ultimate strength standard is 0.65σ b . Among them, the specific strength assessment process belongs to the existing technology and will not be repeated here. If the assessed strength reserve coefficient is greater than 1, the vortex reducer design is feasible. Otherwise, return to the structural design process for redesign based on the difference. If necessary, return to the contour dimension design process and aerodynamic design process of the vortex reducer until the strength reserve coefficient under the given speed, temperature and assembly constraints is greater than 1. Only then can the design of the final pressure relief vortex reducer be completed.

[0083] Optionally, if the strength meets the requirements, further weight reduction optimization design can be performed, such as weight reduction design of the spoke plate, that is, reducing the wall thickness t1 and t2, such as Fig.11 As shown; or, reduce the axial angle β of the wall thickness of the spacer rib; or, use additive manufacturing technology to design the spacer rib to be hollow, such as Fig.12 shown.

[0084] In addition, if Fig.13 As shown, another embodiment of the present invention further provides a design system for a pressure relief vortex reducer, preferably using the design method as described above, including:

[0085] Position design module, used to design the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand;

[0086] The dimension design module is used to design the outline dimension of the pressure relief vortex reducer under the conditions of structural dimension constraints and exhaust outlet static pressure constraints;

[0087] The aerodynamic design module is used to perform aerodynamic design of a pressure relief vortex reducer using a through-type contraction channel and to evaluate the aerodynamic performance of the aerodynamic design scheme;

[0088] The structural design module is used to carry out the structural design of the pressure relief vortex reducer based on the outline dimension design scheme and the aerodynamic design scheme, and to carry out strength evaluation of the structural design scheme.

[0089] It can be understood that the design system of the pressure relief vortex reducer of this embodiment designs the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand, ensuring that the static pressure at the bleed air position meets the sealing bleed air pressure demand. At the same time, the contour size design of the pressure relief vortex reducer is carried out under the conditions of structural size constraints and exhaust outlet static pressure constraints, and a miniaturized design is achieved under the premise of ensuring that the outlet static pressure meets the index requirements. The pressure relief vortex reducer has a compact structure, is easy to install, and is lightweight. It has little effect on the dynamic characteristics of the rotor, reducing the risk of vibration when the rotor rotates at high speed. In addition, a through-type contraction channel is used for the aerodynamic design of the pressure relief vortex reducer, and the outlet static pressure is reduced by increasing the gas velocity, thereby achieving the purpose of pressure relief. The reverse pressure gradient of the contraction channel is small, which can effectively suppress the generation and development of flow separation, thereby greatly reducing the total pressure loss of the flow, and the bleed air flow rate is small, which has little effect on the engine power.

[0090] In addition, another embodiment of the present invention further provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the above method by calling the computer program stored in the memory.

[0091] In addition, another embodiment of the present invention further provides a computer-readable storage medium for storing a computer program for designing a pressure relief vortex reducer, wherein the computer program executes the steps of the method described above when running on a computer.

[0092] The general form of computer readable storage media includes: floppy disk, flexible disk, hard disk, magnetic tape, any other magnetic medium, CD-ROM, any other optical medium, punch cards, paper tape, any other physical medium with a pattern of holes, random access memory (RAM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), flash erasable programmable read-only memory (FLASH-EPROM), any other memory chip or cartridge, or any other medium that can be read by a computer. The instructions can further be transmitted or received by a transmission medium. The term transmission medium can include any tangible or intangible medium that can be used to store, encode or carry instructions for execution by a machine, and includes digital or analog communication signals or other intangible media that facilitate the communication of the above instructions. Transmission media include coaxial cables, copper wires and optical fibers, which include the wires of a bus used to transmit a computer data signal.

[0093] Those skilled in the art will appreciate that the embodiments of the present application can be provided as methods, systems, or computer program products. Therefore, the present application can adopt the form of complete hardware embodiments, complete software embodiments, or embodiments in combination with software and hardware. Moreover, the present application can adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that contain computer-usable program code. The scheme in the embodiments of the present application can be implemented in various computer languages, for example, object-oriented programming language Java and literal scripting language JavaScript, etc.

[0094] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1A device that provides the functions specified in a block or multiple blocks.

[0095] These computer program instructions may also be stored in a computer-readable memory capable of directing a computer or other programmable data processing device to operate in a specific manner, so that the instructions stored in the computer-readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0096] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process in the computer or other programmable device. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0097] Although the preferred embodiments of the present application have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0098] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

[0099] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A design method for a pressure relief vortex reducer, characterized in that: Includes the following: Design the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand; Design the outline dimensions of the pressure relief vortex reducer under the constraints of structural dimensions and exhaust outlet static pressure. The aerodynamic design of the pressure relief and vortex reducer is carried out using a through-type contraction channel, and the aerodynamic performance of the aerodynamic design scheme is evaluated; The structural design of the pressure relief vortex reducer is carried out based on the outline dimension design scheme and the aerodynamic design scheme, and the strength evaluation of the structural design scheme is carried out.

2. The design method of the pressure relief vortex reducer according to claim 1, characterized in that: The process of determining the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand includes the following contents: Determine the static pressure requirement for sealing and the bleed air flow requirement for cooling according to the design status of the engine air system; Perform numerical simulation on the engine compressor to obtain the static pressure distribution data along the hub flow path surface; Based on the static pressure requirement and the static pressure distribution data along the hub flow path surface, the air bleed position is determined on the principle of meeting the static pressure requirement and retaining the static pressure margin. The air bleed position needs to select the meshing center of the end teeth of the adjacent rotor disk to obtain the static temperature of the hub flow path surface corresponding to the air bleed position.

3. The design method of the pressure relief vortex reducer according to claim 2, characterized in that: The outline dimension design includes the axial outline width design, the radial inlet outer outline dimension design and the radial exhaust inner outline dimension design. The radial exhaust inner outline dimension of the pressure relief and vortex reducer is designed based on the following formula: And R 内 ≤min(R3,R4,...) Among them, R 内 represents the inner diameter of the air flow channel of the pressure relief vortex reducer in the radial direction, k2 represents the total pressure recovery coefficient of the pressure relief vortex reducer, P Sin Indicates the static pressure at the intake position, P Sout Indicates the static pressure at the exhaust outlet, P Sout ≥P S0 , P S0 Indicates the static pressure required for sealing, T Sin represents the static temperature of the hub flow path surface corresponding to the bleed air position, R represents the gas constant, α represents the circumferential angular occupation of the air flow channel, m0 represents the bleed air flow demand required for cooling designed by the air system, R3 and R4 represent the inner diameters of the first-stage compressor rotor disk spoke and the second-stage compressor rotor disk spoke in the radial direction, respectively.

4. The design method of the pressure relief vortex reducer according to claim 3, characterized in that: The contents of aerodynamic design include the axial width of the airflow channel, the number of airflow channels and the shape of the airflow channels.

5. The design method of the pressure relief vortex reducer according to claim 4, characterized in that: The design process for the number of airflow channels includes the following: The wall thickness inner diameter arc length of the spacer rib is determined based on the strength requirement, and the wall thickness circumferential angle of the spacer rib is calculated based on the wall thickness inner diameter arc length and the radial exhaust inner contour size; Assuming that the number of airflow channels is n, the circumferential angle of the airflow channels is calculated based on the circumferential angle of the wall thickness and the number of airflow channels; The air intake circumferential length of the air flow channel is calculated based on the circumferential angle of the air flow channel and the radial air intake outer contour size; It is determined whether the air intake circumferential length of the air flow channel can completely cover the circumferential length of at least one end tooth meshing gap and leave a circumferential margin. If this requirement is met, the number of air flow channels is determined to be n.

6. The design method of the pressure relief vortex reducer according to claim 4, characterized in that: During the aerodynamic performance evaluation process, when the bleed air flow rate is too large, the axial width of the air flow channel and / or the number of air flow channels are reduced while ensuring that the strength requirements are met. When the bleed air flow rate is too small, the axial width of the air flow channel and / or the number of air flow channels are increased while ensuring that the strength requirements are met, until the bleed air flow rate meets the requirements.

7. The design method of the pressure relief vortex reducer according to claim 1, characterized in that: During the structural design process, a stopper is also designed on the air inlet side of the spacer rib. The stopper needs to be partially inserted into the end tooth meshing gap and the insertion depth must not be less than a preset value.

8. A design system for a pressure relief vortex reducer, using the design method according to any one of claims 1 to 7, characterized in that: include: Position design module, used to design the axial arrangement position of the pressure relief vortex reducer according to the bleed air demand; The dimension design module is used to design the outline dimension of the pressure relief vortex reducer under the conditions of structural dimension constraints and exhaust outlet static pressure constraints; The aerodynamic design module is used to perform aerodynamic design of a pressure relief vortex reducer using a through-type contraction channel and to evaluate the aerodynamic performance of the aerodynamic design scheme; The structural design module is used to carry out the structural design of the pressure relief vortex reducer based on the outline dimension design scheme and the aerodynamic design scheme, and to carry out strength evaluation of the structural design scheme.

9. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the method according to any one of claims 1 to 7 by calling the computer program stored in the memory.

10. A computer-readable storage medium for storing a computer program for designing a pressure relief vortex reducer, characterized in that: When the computer program is run on a computer, the steps of the method according to any one of claims 1 to 7 are executed.

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