Ring Segment Thickness Design Method and System for Aeroengine Elastic Rings

Abstract

The present invention belongs to the field of aero-engines and relates to the design technology of the thickness of elastic ring segments. A method and a system for designing the thickness of elastic ring segments of an aero-engine are provided. The method includes: dividing the elastic ring into multiple segments, and obtaining the flexibility coefficient of the elastic ring segments according to the given initial value of the segment thickness and the elastic modulus; obtaining the initial value of the stiffness of the elastic ring based on the segment flexibility according to the flexibility coefficient of the elastic ring segments, the number of segments, and the included angle between adjacent inner and outer bosses; obtaining the maximum segment thickness of the elastic ring according to the maximum stiffness limit value of the elastic ring and the initial value of the stiffness of the elastic ring; obtaining the minimum segment thickness according to the maximum radial load of the elastic ring and the yield limit; through the finite element method, obtaining the final segment thickness from the interval formed by the minimum segment thickness and the maximum segment thickness according to the maximum stiffness limit value of the elastic ring. The elastic ring designed by the method of the present invention has good vibration reduction effect in the overall machine vibration, and the fatigue life meets the design requirements.

Description

Technical Field

[0001] The present invention belongs to the field of aero-engines, relates to the technology of the thickness design of an elastic ring segment, and particularly relates to a method and a system for designing the thickness of an elastic ring of an aero-engine. Background Art

[0002] As one of the important elastic supports commonly used on an aero-engine, the elastic ring can change the support stiffness of the rotor system by adjusting its rigidity to optimize the rotor dynamic characteristics; at the same time, the elastic ring can also absorb the vibration energy of the rotor-support system through its own deformation to play a certain role in vibration reduction. The structure of a typical elastic ring is shown in Figure 1 as shown, which includes a ring body 1 and inner bosses 2 and outer bosses 3 on both sides thereof.

[0003] At present, the research on elastic rings mainly focuses on the research of dynamic characteristics, focuses on designing the boss structure parameters of elastic rings, and generally uses empirical design for the wall thickness of elastic rings. However, in fact, the wall thickness of the elastic ring is a key parameter affecting the stiffness and deformation of the elastic ring. If the design is unreasonable, it will have a serious impact on the working safety and reliability of the engine rotor. For example, if the wall thickness of the elastic ring is designed too small, the elastic ring will generate excessive stress and cause fatigue damage under a large radial load; if the wall thickness of the elastic ring is designed too large, the deformation ability of the elastic ring will be small, and then when the engine rotor passes through the critical speed, the vibration energy absorbed by the deformation energy of the elastic ring itself will be weakened, reducing the vibration reduction effect. Summary of the Invention

[0004] In order to solve the technical problem that when designing the existing elastic ring, the thickness of the elastic ring is given by empirical design, which will cause excessive stress to cause fatigue damage or reduce the vibration reduction effect, the present invention discloses a method for designing the thickness of an elastic ring segment of an aero-engine, and the method includes the following steps:

[0005] S1. Divide the elastic ring into a plurality of ring segments according to the total number of inner and outer bosses of the elastic ring, and obtain the flexibility coefficient of the elastic ring segment according to the given initial value of the ring segment thickness and the elastic modulus;

[0006] S2. Obtain the initial value of the elastic ring stiffness based on the flexibility of the ring segment according to the flexibility coefficient of the elastic ring segment, the number of ring segments, and the included angle between adjacent inner and outer bosses;

[0007] S3. Conduct a whole-machine test on the engine to obtain the maximum limit value of the elastic ring stiffness, and correct the initial value of the ring segment thickness according to the maximum limit value of the elastic ring stiffness and the initial value of the elastic ring stiffness, and obtain the ring segment thickness when the initial value of the elastic ring stiffness is equal to the maximum limit value of the elastic ring stiffness as the maximum ring segment thickness;

[0008] S5. Obtain the minimum ring segment thickness based on the maximum radial load and yield limit of the elastic ring;

[0009] S6. Through the finite element method, obtain the final ring segment thickness from the interval formed by the minimum ring segment thickness and the maximum ring segment thickness according to the maximum limit value of the elastic ring stiffness.

[0010] Further, in step S1, divide the elastic ring into multiple ring segments according to the total number of inner and outer convex platforms of the elastic ring, and obtain the flexibility coefficient of the elastic ring segment according to the given initial value of the ring segment thickness and the elastic modulus, including:

[0011] S11. Conduct a structural analysis and a material analysis on the elastic ring to obtain the structural parameters and the elastic modulus. The structural parameters include the total number of the inner and outer convex platforms and the design dimensions of the elastic ring. The design dimensions of the elastic ring include the ring segment thickness, the ring segment length, and the axial length of the elastic ring;

[0012] S12. Divide the elastic ring into multiple ring segments according to the total number of the inner and outer convex platforms, assume each ring segment as a straight beam with equal cross-section and fixed ends at both ends, and obtain the ring segment length of the ring segment;

[0013] S13. Given an initial value of the ring segment thickness, calculate the flexibility coefficient at the central section of the straight beam with equal cross-section and fixed ends at both ends according to the initial value of the ring segment thickness and the elastic modulus, and use the flexibility coefficient at the central section as the flexibility coefficient of the elastic ring segment.

[0014] Even further, in step S13, given an initial value of the ring segment thickness, according to the initial value of the ring segment thickness and the elastic modulus, use the formula to calculate the flexibility coefficient at the central section of the straight beam with equal cross-section and fixed ends at both ends, where is the flexibility coefficient at the central section, is the ring segment length, is the axial length of the elastic ring, is the initial value of the ring segment thickness, E is the elastic modulus.

[0015] Further, in step S2, obtain the initial value of the elastic ring stiffness based on the flexibility of the ring segment according to the flexibility coefficient of the elastic ring segment, the number of ring segments, and the included angle between adjacent inner and outer convex platforms, including:

[0016] S21. Conduct a structural analysis on the elastic ring to obtain the included angle between adjacent inner and outer convex platforms;

[0017] S22. Through the flexibility coefficient of the elastic ring segment, the number of ring segments, and the included angle between adjacent inner and outer convex platforms, use the formula to calculate the initial value of the elastic ring stiffness, where is the initial value of the elastic ring stiffness, , m is the number of ring segments, α is the angle between adjacent inner and outer bosses, is the flexibility coefficient at the central section.

[0018] In an improved embodiment of the above ring segment thickness design method for an aero-engine elastic ring, the method further includes:

[0019] S4. Obtain the maximum radial load of the elastic ring through the resultant force of the maximum loads in the horizontal and vertical directions of the engine.

[0020] Further, in step S5, according to the maximum radial load of the elastic ring and the yield limit, obtain the minimum ring segment thickness, including:

[0021] S51. According to the maximum radial load of the elastic ring, use the formula to calculate the maximum stress at the end of the ring segment, where is the maximum radial load of the elastic ring, is the length of the ring segment, is the axial length of the elastic ring, is the initial value of the ring segment thickness, is the maximum stress at the end of the ring segment;

[0022] S52. Correct the initial value of the ring segment thickness according to the maximum stress at the end of the ring segment and the yield limit, and obtain the ring segment thickness when the maximum stress at the end of the ring segment is equal to the yield limit as the minimum ring segment thickness.

[0023] Further, in step S6, through the finite element method, obtain the final ring segment thickness from the interval formed by the minimum ring segment thickness and the maximum ring segment thickness according to the maximum stiffness limit value of the elastic ring, including:

[0024] S61. Take the minimum ring segment thickness and the maximum ring segment thickness as the design interval, and construct multiple elastic ring models;

[0025] S62. Obtain the simulated stiffness value of each elastic ring model through finite element analysis, and select the ring segment thickness value corresponding to the elastic ring model with the simulated stiffness value less than the maximum stiffness limit value of the elastic ring and the farthest distance from the maximum stiffness limit value of the elastic ring as the final ring segment thickness.

[0026] The embodiment of the present invention also provides a ring segment thickness design system for an aero-engine elastic ring, including a flexibility coefficient acquisition module, an initial elastic ring stiffness calculation module, a maximum ring segment thickness calculation module, a minimum ring segment thickness acquisition module, and a screening module.

[0027] Among them, the flexibility coefficient acquisition module is used to divide the elastic ring into multiple ring segments according to the total number of inner and outer bosses of the elastic ring, and obtain the flexibility coefficient of the elastic ring ring segment according to the given initial value of the ring segment thickness and the elastic modulus;

[0028] The initial elastic ring stiffness calculation module is used to obtain the initial elastic ring stiffness based on the ring segment flexibility coefficient, the number of ring segments, and the angle between adjacent inner and outer bosses according to the flexibility of the ring segments;

[0029] The maximum ring segment thickness calculation module is used to obtain the maximum limit value of the elastic ring stiffness through the overall engine test, and correct the initial ring segment thickness according to the maximum limit value of the elastic ring stiffness and the initial elastic ring stiffness, and obtain the ring segment thickness when the initial elastic ring stiffness is equal to the maximum limit value of the elastic ring stiffness as the maximum ring segment thickness;

[0030] The minimum ring segment thickness acquisition module is used to obtain the minimum ring segment thickness according to the maximum radial load and yield limit of the elastic ring;

[0031] The screening module is used to obtain the final ring segment thickness from the interval formed by the minimum ring segment thickness and the maximum ring segment thickness according to the maximum limit value of the elastic ring stiffness by the finite element method.

[0032] An embodiment of the present invention also provides a computer device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the above-mentioned ring segment thickness design method of the aero-engine elastic ring is implemented to solve the technical problem that when designing the existing elastic ring, the thickness of the elastic ring is given by empirical design, which will generate excessive stress, causing fatigue damage or reducing the vibration damping effect.

[0033] An embodiment of the present invention also provides a computer-readable storage medium, which stores a computer program for executing the above-mentioned ring segment thickness design method of the aero-engine elastic ring, to solve the technical problem that when designing the existing elastic ring, the thickness of the elastic ring is given by empirical design, which will generate excessive stress, causing fatigue damage or reducing the vibration damping effect.

[0034] Adopting the technical solution of the present invention can bring the following beneficial effects:

[0035] 1. By determining the maximum ring segment thickness of the elastic ring, the maximum stiffness of the elastic ring is within the allowable range, and when the engine rotor passes through the critical speed, the elastic ring generates a good vibration damping effect through its own deformation;

[0036] 2. By determining the minimum ring segment thickness of the elastic ring, the maximum stress of the elastic ring under the maximum radial load condition is less than the material yield limit, ensuring that no fatigue cracks occur during the service life of the engine;

[0037] The present invention has been successfully applied to the design of the thickness of the elastic ring segment of an engine. The elastic ring has passed the component tests and the endurance test of the whole machine. The vibration reduction effect of the whole machine of the elastic ring is good, and the fatigue life meets the design requirements. Description of the Drawings

[0038] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0039] Figure 1 Schematic diagram of the typical structure of the elastic ring;

[0040] Figure 2 Flowchart of the method for designing the thickness of the ring segment of the elastic ring of an aeroengine disclosed in the embodiment of the present invention;

[0041] Figure 3 Principle block diagram of the method for designing the thickness of the ring segment of the elastic ring of an aeroengine disclosed in the embodiment of the present invention;

[0042] Figure 4 Schematic diagram of the force model of the ring segment disclosed in the embodiment of the present invention;

[0043] Figure 5 Architecture diagram of the system for designing the thickness of the ring segment of the elastic ring of an aeroengine disclosed in the embodiment of the present invention;

[0044] Among them, 1, ring body 1; 2, inner convex platform; 3, outer convex platform; 501, flexibility coefficient acquisition module; 502, initial elastic ring stiffness calculation module; 503, maximum ring segment thickness calculation module; 504, minimum ring segment thickness acquisition module; 505, screening module. Detailed Embodiments

[0045] The embodiments of the present application will be described in detail below with reference to the drawings.

[0046] The following describes the implementation manners of the present application through specific examples. Those skilled in the art can easily understand the other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features of the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts belong to the scope protected by the present application.

[0047] An embodiment of the present invention discloses a method for designing the ring section thickness of an elastic ring of an aero-engine. Refer to Figure 2 and Figure 3 as shown. The method includes the following steps:

[0048] S1. Divide the elastic ring into multiple ring sections according to the total number of inner and outer bosses of the elastic ring, and obtain the flexibility coefficient of the elastic ring ring section according to the given initial value of the ring section thickness and the elastic modulus.

[0049] S2. Obtain the initial stiffness value of the elastic ring based on the flexibility of the ring section according to the flexibility coefficient of the elastic ring ring section, the number of ring sections, and the included angle between adjacent inner and outer bosses.

[0050] S3. Conduct a whole-engine test on the engine to obtain the maximum limit value of the elastic ring stiffness. Modify the initial value of the ring section thickness according to the maximum limit value of the elastic ring stiffness and the initial stiffness value of the elastic ring, and take the ring section thickness when the initial stiffness value of the elastic ring is equal to the maximum limit value of the elastic ring stiffness as the maximum ring section thickness.

[0051] S5. Obtain the minimum ring section thickness according to the maximum radial load and yield limit of the elastic ring.

[0052] S6. Through the finite element method, obtain the final ring section thickness from the interval formed by the minimum ring section thickness and the maximum ring section thickness according to the maximum limit value of the elastic ring stiffness.

[0053] Further, in step S1, dividing the elastic ring into multiple ring sections according to the total number of inner and outer bosses of the elastic ring, and obtaining the flexibility coefficient of the elastic ring ring section according to the given initial value of the ring section thickness and the elastic modulus includes:

[0054] S11. Conduct a structural analysis and a material analysis on the elastic ring to obtain the structural parameters and the elastic modulus. The structural parameters include the total number of inner and outer bosses and the design dimensions of the elastic ring. The design dimensions of the elastic ring include the ring section thickness, the ring section length, and the axial length of the elastic ring.

[0055] S12. Divide the elastic ring into multiple ring segments according to the total number of the internal and external convex platforms, assume each ring segment as a straight beam with equal cross-section and fixed ends at both ends, and obtain the length of the ring segment.

[0056] S13. Given an initial value of the ring segment thickness, calculate the flexibility coefficient at the central section of the straight beam with equal cross-section and fixed ends at both ends according to the initial value of the ring segment thickness and the elastic modulus, and take the flexibility coefficient at the central section as the flexibility coefficient of the elastic ring segment.

[0057] Furthermore, in step S13, given an initial value of the ring segment thickness, according to the initial value of the ring segment thickness and the elastic modulus, use the formula to calculate the flexibility coefficient at the central section of the straight beam with equal cross-section and fixed ends at both ends, where is the flexibility coefficient at the central section, is the length of the ring segment, is the axial length of the elastic ring, is the initial value of the ring segment thickness, E is the elastic modulus.

[0058] When the above steps S11 to S13 are specifically implemented, since the elastic ring of the aero-engine has a large number of internal and external convex platforms, the number of elastic ring segments is large and the span of the ring segment is small. The elastic ring can be divided into m ring segments according to the number of internal and external convex platforms of the elastic ring. Each ring segment can be assumed as a straight beam with fixed ends at both ends. If the total bearing force is set as F and the component force of each ring segment is Fi, its force model is as Figure 4 shown.

[0059] The flexibility coefficient at the central section of the straight beam with equal cross-section and fixed ends at both ends , mm / N, that is, the flexibility coefficient of the elastic ring segment can be obtained from Equation (1)

[0060] ………………………………Equation (1);

[0061] where is the length of the ring segment, calculated at the average radius, , mm; a is the width of the convex platform, b is the axial length of the elastic ring, m is the total number of internal and external convex platforms, D m is the average value of the outer diameter and the inner diameter of the elastic ring, I is the moment of inertia of the ring segment cross-section, mm 4 ; E is the elastic modulus, GPa.

[0062] For the rectangular ring segment cross-section, the moment of inertia I of its ring segment cross-section can be obtained from Equation (2)

[0063] , that is, ………………………………Formula (2);

[0064] where I is the moment of inertia of the ring segment cross-section, is the axial length of the elastic ring, in mm; is the initial thickness of the ring segment, in mm.

[0065] Furthermore, in step S2, based on the flexibility coefficient of the elastic ring segments, the number of segments, and the angle between adjacent inner and outer bosses, an initial value of the elastic ring stiffness based on the segment flexibility is obtained, including:

[0066] S21. Perform a structural analysis on the elastic ring to obtain the angle between adjacent inner and outer bosses;

[0067] S22. Using the flexibility coefficient of the elastic ring segments, the number of segments, and the angle between adjacent inner and outer bosses, adopt the formula to calculate the initial value of the elastic ring stiffness, where is the initial value of the elastic ring stiffness, , m is the number of segments, α is the angle between adjacent inner and outer bosses, is the flexibility coefficient at the central cross-section.

[0068] In the specific implementation of steps S21 and S22, for an elastic ring with m segments, only segments are subjected to force, and the forces on each segment can be defined as F0, F1,......F i , then the total bearing force F can be expressed by the following formula (3):

[0069] ……………………………Formula (3);

[0070] where is the angle between the component forces acting on the segments, that is, the angle between adjacent inner and outer bosses, in rad, and the angle of each segment is the same.

[0071] And the displacement of each segment can be expressed by the following formula (4):

[0072] ………………………………Formula (4);

[0073] Generally, the stiffness of the elastic ring in the direction of force F is , and the displacement under the action of force F is , so the initial value of the elastic ring stiffness ring segment thickness of the elastic ring can be expressed by the following formula (5):

[0074] ………………………………………Formula (5);

[0075] where is the total bearing force, in N; is the stiffness of the elastic ring in the direction of force F, in N / m; is the displacement of the elastic ring under the action of force F, in m. Substituting Eqs. (3) and (4) into Eq. (5), the following Eq. (6) can be obtained:

[0076] ……………………… Eq. (6);

[0077] In the specific implementation of the above step S3, the stiffness of the elastic ring is made equal to the maximum limit value of the stiffness of the elastic ring, and the maximum thickness of the elastic ring segment is calculated , and the maximum ring segment thickness should ensure that the elastic ring has a relatively small stiffness, so that when the engine passes through the critical speed of the rotor, the elastic ring can generate a large deformation to absorb vibration energy and play a vibration damping role, that is, the maximum thickness of the elastic ring segment can be inversely deduced through the following Eqs. (7) and (8):

[0078] ……………………… Eq. (7);

[0079] ……………………… Eq. (8);

[0080] where is the maximum limit value of the stiffness of the elastic ring, and it is generally recommended not to exceed , in N / m, which can be obtained through the whole engine vibration test of the engine and calculated according to the experimental data.

[0081] In an improved embodiment of the above method for designing the ring segment thickness of the elastic ring of the aeroengine, the method further includes:

[0082] S4. Obtain the maximum radial load of the elastic ring through the resultant force of the maximum loads in the horizontal and vertical directions of the engine. Specifically, the maximum radial load state of the elastic ring is the maximum value of the resultant force of the loads in the horizontal and vertical directions of the engine, and the full envelope of the maneuvering overload of the aircraft needs to be considered. Specifically, it can be calculated through the following Eq. (9):

[0083] …………………………… Eq. (9);

[0084] is the maximum horizontal force at the rotor support point where the elastic ring is located, in N;

[0085] is the maximum vertical force at the rotor support point where the elastic ring is located, in N, and both of these values can be extracted from the engine load design report.

[0086] Further, in step S5, the minimum ring segment thickness is obtained according to the maximum radial load and yield limit of the elastic ring, including:

[0087] S51, according to the maximum radial load of the elastic ring, use the formula Calculate the maximum stress at the end of the ring segment, where is the maximum radial load of the elastic ring, is the length of the ring segment, is the axial length of the elastic ring, is the initial value of the ring segment thickness, is the maximum stress at the end of the ring segment;

[0088] S52, correcting the initial value of the ring segment thickness according to the maximum stress at the end of the ring segment and the yield limit, and obtaining the ring segment thickness when the maximum stress at the end of the ring segment is equal to the yield limit as the minimum ring segment thickness.

[0089] In the specific implementation of steps S51 and S52, the minimum ring segment thickness should be able to ensure that the maximum stress of the elastic ring is Do not exceed the yield limit to avoid fatigue damage to the elastic ring during operation. When the force load is directly on the central section of the ring segment, the force on the ring segment is the largest and the stress at its end is also the largest. Therefore, the maximum stress of the end section of the ring segment is obtained by material mechanics through the following formula (10):

[0090] ………………………………Formula (10);

[0091] The length of the loop segment By formula Calculated. W is the section coefficient of the ring section, mm 3 , the section coefficient can be calculated by the following formula (11):

[0092] ………………………………Formula (11);

[0093] At this time, the maximum stress at the end of the ring segment can be expressed by the following formula (12):

[0094] ………………………………Formula (12);

[0095] In order to avoid fatigue damage of the elastic ring during operation, the maximum stress of the elastic ring is required to be Not exceeding the yield limit , the relationship between the two can be expressed by the following formula (13):

[0096] ………………………………Formula (13);

[0097] ——The yield limit corresponding to the elastic ring material, MPa.

[0098] When the maximum stress is the same as the yield limit , the minimum ring segment thickness can be calculated by the following formula (14) :

[0099] ………………………………Formula (14);

[0100] Furthermore, in step S6, by the finite element method, the final ring segment thickness is obtained from the interval formed by the minimum ring segment thickness and the maximum ring segment thickness according to the maximum stiffness limit value of the elastic ring, including:

[0101] S61. Taking the minimum ring segment thickness and the maximum ring segment thickness as the design interval, constructing a plurality of elastic ring models;

[0102] S62. Obtaining the simulated stiffness value of each elastic ring model through finite element analysis, and selecting the ring segment thickness value corresponding to the elastic ring model with the simulated stiffness value less than the maximum stiffness limit value of the elastic ring and the farthest distance from the maximum stiffness limit value of the elastic ring as the final ring segment thickness.

[0103] Adopting the technical solution of the present invention can bring the following beneficial effects:

[0104] 1. By determining the maximum ring segment thickness of the elastic ring, the maximum stiffness of the elastic ring is within the allowable value range, and when the engine rotor passes through the critical speed, the elastic ring produces a good vibration damping effect through its own deformation;

[0105] 2. By determining the minimum ring segment thickness of the elastic ring, the maximum stress of the elastic ring under the maximum radial load condition is less than the material yield limit, ensuring that no fatigue cracks occur during the service life of the engine;

[0106] The present invention has been successfully applied to the design of the ring segment thickness of an elastic ring of an engine. The elastic ring has passed the component test and the whole machine endurance test. The elastic ring has a good vibration damping effect in terms of the whole machine vibration and meets the design requirements in terms of fatigue life.

[0107] Based on the same inventive concept, an embodiment of the present invention also provides a system for designing the thickness of ring segments of an aero-engine elastic ring, as described in the following embodiments. Since the principle of the system for designing the thickness of ring segments of an aero-engine elastic ring to solve problems is similar to that of the method for designing the thickness of ring segments of an aero-engine elastic ring, the implementation of the system for designing the thickness of ring segments of an aero-engine elastic ring can refer to the implementation of the method for designing the thickness of ring segments of an aero-engine elastic ring, and the repeated parts will not be elaborated here. As used hereinafter, the term "unit" or "module" can be a combination of software and / or hardware that can achieve a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, implementation in hardware, or a combination of software and hardware is also possible and contemplated.

[0108] Figure 5 is a structural block diagram of a system for designing the thickness of ring segments of an aero-engine elastic ring disclosed in an embodiment of the present invention, as Figure 5 shown. The system includes a flexibility coefficient acquisition module 501, an initial elastic ring stiffness calculation module 502, a maximum ring segment thickness calculation module 503, a minimum ring segment thickness acquisition module 504, and a screening module 505. The following describes this structure.

[0109] Among them, the flexibility coefficient acquisition module 501 is used to divide the elastic ring into multiple ring segments according to the total number of inner and outer bosses of the elastic ring, and obtain the flexibility coefficient of the elastic ring segments according to the given initial ring segment thickness and elastic modulus;

[0110] The initial elastic ring stiffness calculation module 502 is used to obtain the initial elastic ring stiffness based on the flexibility of the ring segments according to the flexibility coefficient of the elastic ring segments, the number of ring segments, and the angle between adjacent inner and outer bosses;

[0111] The maximum ring segment thickness calculation module 503 is used to conduct a full-engine test on the engine to obtain the maximum limit value of the elastic ring stiffness, and correct the initial ring segment thickness according to the maximum limit value of the elastic ring stiffness and the initial elastic ring stiffness, and obtain the ring segment thickness when the initial elastic ring stiffness is equal to the maximum limit value of the elastic ring stiffness as the maximum ring segment thickness;

[0112] The minimum ring segment thickness acquisition module 504 is used to obtain the minimum ring segment thickness according to the maximum radial load and yield limit of the elastic ring;

[0113] The screening module 505 is used to obtain the final ring segment thickness from the interval formed by the minimum ring segment thickness and the maximum ring segment thickness according to the maximum limit value of the elastic ring stiffness by means of the finite element method.

[0114] In this embodiment, a computer device is provided, which includes a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the above-mentioned arbitrary method for designing the ring segment thickness of the aero-engine elastic ring is implemented.

[0115] Specifically, the computer device can be a computer terminal, a server, or a similar computing device.

[0116] In this embodiment, a computer-readable storage medium is provided, and the computer-readable storage medium stores a computer program for executing the above-mentioned arbitrary method for designing the ring segment thickness of the aero-engine elastic ring.

[0117] Specifically, the computer-readable storage medium includes permanent and non-permanent, removable and non-removable media, and information storage can be implemented by any method or technology. The information can be computer-readable instructions, data structures, program modules, or other data. Examples of computer-readable storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, compact disc read-only memory (CD-ROM), digital versatile disc (DVD) or other optical storage, magnetic cassette tapes, magnetic disk storage or other magnetic storage devices, or any other non-transmission medium that can be used to store information accessible by a computing device. As defined herein, computer-readable storage media do not include transitory computer-readable media, such as modulated data signals and carrier waves.

[0118] Obviously, those skilled in the art should understand that the above-mentioned modules or steps of the embodiments of the present invention can be implemented by a general-purpose computing device. They can be concentrated on a single computing device or distributed on a network composed of multiple computing devices. Optionally, they can be implemented by program codes executable by the computing device. Thus, they can be stored in a storage device and executed by the computing device. And in some cases, the steps shown or described can be executed in a different order than here, or they can be separately fabricated into individual integrated circuit modules, or multiple modules or steps among them can be fabricated into a single integrated circuit module to be implemented. In this way, the embodiments of the present invention are not limited to any specific combination of hardware and software.

[0119] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, various modifications and variations can be made to the embodiments of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A method for designing the ring segment thickness of an elastic ring of an aeroengine, characterized in that Including: Dividing the elastic ring into multiple ring segments according to the total number of inner and outer convex platforms of the elastic ring, and obtaining the flexibility coefficient of the elastic ring segment according to the given initial value of the ring segment thickness and the elastic modulus; Obtain the initial value of the elastic ring stiffness based on the flexibility coefficient of the elastic ring segment, the number of segments, and the included angle between adjacent inner and outer bosses, including: performing a structural analysis on the elastic ring to obtain the included angle between adjacent inner and outer bosses; using the flexibility coefficient of the elastic ring segment, the number of segments, and the included angle between adjacent inner and outer bosses, and adopting the formula to calculate the initial value of the elastic ring stiffness, where is the initial value of the elastic ring stiffness,[[]] , m is the number of segments, α is the included angle between adjacent inner and outer bosses,[[]] is the flexibility coefficient at the central section; Conducting a whole-machine test on the engine to obtain the maximum limit value of the elastic ring stiffness, and correcting the initial value of the ring segment thickness according to the maximum limit value of the elastic ring stiffness and the initial value of the elastic ring stiffness, so as to obtain the ring segment thickness when the initial value of the elastic ring stiffness is equal to the maximum limit value of the elastic ring stiffness as the maximum ring segment thickness; Obtain the minimum ring segment thickness according to the maximum radial load and yield limit of the elastic ring, including: according to the maximum radial load of the elastic ring, use the formula to calculate the maximum stress at the end of the ring segment, where is the maximum radial load of the elastic ring, is the length of the ring segment, is the axial length of the elastic ring, is the initial value of the ring segment thickness, is the maximum stress at the end of the ring segment; correct the initial value of the ring segment thickness according to the maximum stress at the end of the ring segment and the yield limit, and obtain the ring segment thickness when the maximum stress at the end of the ring segment is equal to the yield limit as the minimum ring segment thickness; Through the finite element method, obtaining the final ring segment thickness from the interval formed by the minimum ring segment thickness and the maximum ring segment thickness according to the maximum limit value of the elastic ring stiffness.

2. The method for designing the ring segment thickness of the elastic ring of an aeroengine according to claim 1, characterized in that, Dividing the elastic ring into multiple ring segments according to the total number of inner and outer convex platforms of the elastic ring, and obtaining the flexibility coefficient of the elastic ring segment according to the given initial value of the ring segment thickness and the elastic modulus, including: Conducting a structural analysis and a material analysis on the elastic ring to obtain structural parameters and the elastic modulus, where the structural parameters include the total number of the inner and outer convex platforms and the design dimensions of the elastic ring, and the design dimensions of the elastic ring include the ring segment thickness, the ring segment length, and the axial length of the elastic ring; Dividing the elastic ring into multiple ring segments according to the total number of the inner and outer convex platforms, assuming each ring segment as an equal-section straight beam with both ends fixed, and obtaining the ring segment length of the ring segment; Giving an initial value of the ring segment thickness, and calculating the flexibility coefficient at the central section of the equal-section straight beam with both ends fixed according to the initial value of the ring segment thickness and the elastic modulus, and taking the flexibility coefficient at the central section as the flexibility coefficient of the elastic ring segment.

3. The method for designing the ring section thickness of the elastic ring of an aero-engine according to claim 2, characterized in that, Given an initial value of the ring segment thickness, according to the initial value of the ring segment thickness and the elastic modulus, use the formula to calculate the flexibility coefficient at the central section of the straight beam with equal cross-section and fixed ends at both ends, where is the flexibility coefficient at the central section, is the length of the ring segment, is the axial length of the elastic ring, is the initial value of the ring segment thickness, E is the elastic modulus.

4. The method for designing the ring segment thickness of the elastic ring of an aeroengine according to claim 1, characterized in that Also including: Obtaining the maximum radial load of the elastic ring through the resultant force of the maximum loads in the horizontal and vertical directions of the engine.

5. The method for designing the ring segment thickness of the elastic ring of an aeroengine according to claim 1, characterized in that, Through the finite element method, obtaining the final ring segment thickness from the interval formed by the minimum ring segment thickness and the maximum ring segment thickness according to the maximum limit value of the elastic ring stiffness, including: Taking the minimum ring segment thickness and the maximum ring segment thickness as the design interval, and constructing multiple elastic ring models; Obtaining the simulated stiffness value of each elastic ring model through finite element analysis, and selecting the ring segment thickness value corresponding to the elastic ring model with the simulated stiffness value less than the maximum limit value of the elastic ring stiffness and the farthest distance from the maximum limit value of the elastic ring stiffness as the final ring segment thickness.

6. A ring segment thickness design system for an aeroengine elastic ring, characterized in that, Including: A flexibility coefficient obtaining module, which is used to divide the elastic ring into multiple ring segments according to the total number of inner and outer convex platforms of the elastic ring, and obtain the flexibility coefficient of the elastic ring segment according to the given initial value of the ring segment thickness and the elastic modulus; Elastic ring stiffness initial value calculation module, which is used to obtain the initial value of the elastic ring stiffness based on the flexibility coefficient of the elastic ring segment, the number of segments and the angle between adjacent inner and outer bosses, including: performing a structural analysis on the elastic ring to obtain the angle between adjacent inner and outer bosses; using the flexibility coefficient of the elastic ring segment, the number of segments and the angle between adjacent inner and outer bosses, and adopting the formula to calculate the initial value of the elastic ring stiffness, where is the initial value of the elastic ring stiffness, , m is the number of segments, α is the angle between adjacent inner and outer bosses, is the flexibility coefficient at the central section; A maximum ring segment thickness calculating module, which is used to conduct a whole-machine test on the engine to obtain the maximum limit value of the elastic ring stiffness, and correct the initial value of the ring segment thickness according to the maximum limit value of the elastic ring stiffness and the initial value of the elastic ring stiffness, so as to obtain the ring segment thickness when the initial value of the elastic ring stiffness is equal to the maximum limit value of the elastic ring stiffness as the maximum ring segment thickness; Minimum ring segment thickness acquisition module, which is used to obtain the minimum ring segment thickness according to the maximum radial load and yield limit of the elastic ring, including: according to the maximum radial load of the elastic ring, using the formula Calculate the maximum stress at the end of the ring segment, where Is the maximum radial load of the elastic ring, Is the length of the ring segment, Is the axial length of the elastic ring, Is the initial value of the ring segment thickness, Is the maximum stress at the end of the ring segment; correct the initial value of the ring segment thickness according to the maximum stress at the end of the ring segment and the yield limit, and obtain the ring segment thickness when the maximum stress at the end of the ring segment is equal to the yield limit as the minimum ring segment thickness; A screening module, which is used to obtain the final ring segment thickness from the interval formed by the minimum ring segment thickness and the maximum ring segment thickness through the finite element method according to the maximum limit value of the elastic ring stiffness.

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