Frame support structure and aircraft engine

Abstract

The present invention discloses a frame support structure and an aircraft engine, comprising: an outer mounting edge; an inner mounting edge; an outer wall connected to the outer mounting edge; an inner wall connected to the inner mounting edge and forming an outer flow channel with the outer wall, wherein the inner surface of the inner wall forms an inner flow channel; a support plate structure respectively connecting the inner wall and the outer wall, wherein a plurality of support plate structures are arranged along the circumference of the frame support structure for transferring loads; an arc-shaped folding structure, wherein the arc-shaped folding structure comprises an arc-shaped portion and a first connecting portion and a second connecting portion arranged at intervals along the radial direction of the frame support structure, wherein the two ends of the arc-shaped portion are respectively connected to the arc-shaped portions of the first end of the first connecting portion and the first end of the second connecting portion, wherein the second end of the first connecting portion is used to connect to the outer mounting edge, and the second end of the second connecting portion is used to connect to the outer wall, or the second end of the first connecting portion is used to connect to the inner mounting edge, and the second end of the second connecting portion is used to connect to the inner wall.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engines, and in particular, to a frame support structure. In addition, the present invention also relates to an aircraft engine comprising the frame support structure. Background Art

[0002] Usually, the frame support on aviation gas turbine engines and ground combustion engines is a double-layer structure. The inner and outer layers form the gas channel, and there are multiple support plates in the middle that are evenly or unevenly distributed around the circumference to support and transfer the rotor load. Its structure is as follows: Figure 1 shown.

[0003] During the operation of aviation gas turbine engines and ground-based combustion engines, the frame support structure transfers the fulcrum load on the rotor support to the outer stator casing, while bearing the surface pressure load of the gas channel and the temperature load generated by the passage of high-temperature combustion gas.

[0004] When the frame support structure with support plates in the prior art is applied to the hot end of aviation gas turbine engines and ground combustion engines, the support plates are in direct contact with the high-temperature combustion gas. The metal temperature of the support plate is relatively high, while the temperature of the part connected with the rotor support and the stator casing is relatively low, resulting in a large thermal gradient in the frame support structure during operation, such as Figure 2 As shown, the two ends of the support plate limit the thermal expansion of the support plate, which causes large stresses in the connection parts between the support plate and the inner wall and the outer wall, thereby reducing the low cycle fatigue life of the frame support structure and failing to meet the long life requirements of advanced aviation gas turbine engines and ground combustion engines. Summary of the invention

[0005] The present invention provides a frame support structure and an aircraft engine to solve the technical problem in the prior art that a large thermal gradient exists in the support structure during operation, resulting in large stress between the support structure and a rotor support and between the support structure and a stator casing, which affects the low cycle fatigue life of the structure.

[0006] According to one aspect of the present invention, there is provided a frame support structure, which is applied to an aircraft engine and is arranged between a stator casing and a rotor support. The frame support structure comprises:

[0007] The outer mounting edge is used to connect with the stator casing for centering and load transfer;

[0008] Inner mounting edge, used to connect with the rotor support for centering and load transfer;

[0009] An outer wall connected to the outer mounting edge;

[0010] An inner wall connected to the inner mounting edge and forming an outer flow channel with the outer wall, and an inner surface of the inner wall forming an inner flow channel;

[0011] A support plate structure, respectively connecting the inner wall and the outer wall, wherein a plurality of the support plate structures are arranged along the circumference of the frame support structure for transmitting loads;

[0012] The arc-shaped folding structure is respectively arranged between the outer mounting edge and the outer wall and between the inner mounting edge and the inner wall, and is used to bear the load transmitted from the support plate structure area in a high temperature state to the stator casing and rotor support in a low temperature state, so as to alleviate the radial thermal deformation limitation of the supporting structure when subjected to high temperature.

[0013] As a further improvement of the above technical solution, the arc-shaped folding structure includes an arc-shaped portion and a first connecting portion and a second connecting portion arranged at radial intervals along the frame support structure, the two ends of the arc-shaped portion are respectively connected to the arc-shaped portions of the first end of the first connecting portion and the first end of the second connecting portion, the second end of the first connecting portion is used to connect to the outer mounting edge, and the second end of the second connecting portion is used to connect to the outer layer wall, or the second end of the first connecting portion is used to connect to the inner mounting edge, and the second end of the second connecting portion is used to connect to the inner layer wall.

[0014] As a further improvement of the above technical solution, the arc-shaped folding structure is provided with a plurality of stress release structures, and the circumferential distribution positions of the stress release structures match the circumferential distribution positions of the support plate structure.

[0015] As a further improvement of the above technical solution, the stress release structure is a hole-shaped structure, and the circumferential size of the stress release structure is 1.5-2 times the circumferential size of the support plate structure.

[0016] As a further improvement of the above technical solution, the support plate structure is a hollow structure, and two ends of the support plate structure are respectively connected to the outer surface of the outer wall and the inner surface of the inner wall.

[0017] As a further improvement of the above technical solution, the frame support structure includes an oil pipeline, which is connected to the lubricating oil pipeline of the engine and is used to pass through the support plate structure to the support point of the rotor support to introduce lubricating oil to the support point of the rotor support.

[0018] As a further improvement of the above technical solution, the design method of the arc folding structure includes: S1. Calculating the load transmitted to the rotor support and / or to the stator casing by the radial thermal expansion of the support plate structure, the calculation formula is:

[0019] (1)

[0020] Where k is the stiffness of the arc-shaped part, and x is the radial displacement of the high-temperature support plate;

[0021] S2. The structural stiffness of the arc portion, the structural stiffness of the first connection portion, and the structural stiffness of the second connection portion are calculated using equations (2) to (4). The design formula includes:

[0022] (2)

[0023] (3)

[0024] (4)

[0025] In the formula, is the stiffness of the first connection, is the stiffness of the second connection, is the elastic modulus, and are the outer diameters of the first connecting part and the second connecting part, respectively, and are the inner diameter of the first connecting part and the inner diameter of the second connecting part, respectively, and are the length of the first connecting portion and the length of the second connecting portion respectively.

[0026] As a further improvement of the above technical solution, the arc-shaped folding structure is provided with a plurality of hole-shaped stress release structures, and the design method further comprises step S3: designing the stiffness of the stress release structure region, and the design formula is:

[0027] (5)

[0028] In the formula, is the stiffness of the stress relief structure, and are the outer radius and inner radius of the arc part respectively, is the number of stress relief structures, The major axis width is constructed for stress relief, Construct the minor axis length for stress relief.

[0029] As a further improvement of the above technical solution, the design method also includes: setting spatial structure size constraints and process constraints, and using finite element analysis to iteratively optimize the length of the first connection part and / or the length of the second connection part and / or the length of the third connection part and / or the outer diameter of the first connection part and / or the outer diameter of the second connection part and / or the outer arc radius of the third connection part and / or the inner diameter of the first connection part and / or the inner diameter of the second connection part and / or the inner arc radius of the third connection part and / or the number of stress release structures and / or the major axis width of the stress release structure and / or the minor axis length of the stress release structure.

[0030] According to another aspect of the present invention, there is also provided an aircraft engine, which comprises the above-mentioned frame supporting structure.

[0031] The present invention has the following beneficial effects:

[0032] The frame support structure adopts a traditional double-wall structure design, which is used to be arranged between the stator casing and the rotor support. It is a rotating body structure as a whole like the stator casing and the rotor support. It has an outer wall and an inner wall, and a support plate structure is arranged between the two for connection and support and to transfer load based on the support plate structure. An outer flow channel is formed between the outer wall and the inner wall, and the inner flow channel is formed inside the inner wall. Based on the aerodynamic performance requirements, the aerodynamic performance requirements can be met by adjusting the shape of the support plate and / or adjusting the size of the flow channel; the outer mounting edge is arranged on the outer wall, and the inner mounting edge is arranged on the inner wall; the outer mounting edge located on the outermost ring is connected to the stator casing for centering and load transfer, and the inner mounting edge located on the innermost ring is connected to the rotor support for transfer of the rotor fulcrum load, respectively. An arc-shaped folding structure is arranged between the outer walls and between the inner mounting edge and the inner wall. At the outer mounting edge, two ends of the arc-shaped folding structure are respectively connected to the outer mounting edge and the outer wall. At the inner mounting edge, two ends of the arc-shaped folding structure are respectively connected to the inner mounting edge and the inner wall. Therefore, in the working state, the arc-shaped folding structure mainly bears the load transmitted from the support plate structure area in the high temperature state to the outer stator and the inner support in the low temperature state. The flexible folding structure design based on the arc portion alleviates the radial thermal deformation limitation of the supporting structure when it is subjected to high temperature, effectively reduces the large stress generated by the connection ends of the inner and outer peripheries of the frame supporting structure due to high temperature expansion, and reduces the high stress level caused by the large thermal gradient in the working state, thereby improving the low cycle fatigue life of components.

[0033] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] 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:

[0035] Figure 1 It is a structural schematic diagram of a frame support structure in the prior art;

[0036] Figure 2 It is a schematic diagram of stress distribution simulation of a frame support structure in the working state in the prior art;

[0037] Figure 3 is a cross-sectional view of the frame support structure of a preferred embodiment of the present invention Figure 1 ;

[0038] Figure 4 is a cross-sectional view of the frame support structure of a preferred embodiment of the present invention Figure 2 ;

[0039] Figure 5 is a schematic diagram of temperature distribution in a working state of a frame support structure of a preferred embodiment of the present invention;

[0040] Figure 6 It is a schematic diagram of stress distribution simulation of the frame support structure of the preferred embodiment of the present invention under working conditions.

[0041] Legend:

[0042] 100, outer mounting edge; 200, arc-shaped folding structure; 201, first connecting portion; 202, arc-shaped portion; 203, second connecting portion; 300, stress release structure; 400, outer wall; 401, outer flow channel; 500, support plate structure; 600, inner wall; 601, inner flow channel; 700, inner mounting edge. DETAILED DESCRIPTION

[0043] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0044] Figure 1 It is a structural schematic diagram of a frame support structure in the prior art; Figure 2 It is a schematic diagram of stress distribution simulation of a frame support structure in the working state in the prior art; Figure 3 is a cross-sectional view of the frame support structure of a preferred embodiment of the present invention Figure 1 ; Figure 4 is a cross-sectional view of the frame support structure of a preferred embodiment of the present invention Figure 2 ; Figure 5 is a schematic diagram of temperature distribution in a working state of a frame support structure of a preferred embodiment of the present invention; Figure 6 It is a schematic diagram of stress distribution simulation of the frame support structure of the preferred embodiment of the present invention under working conditions.

[0045] like Figures 3 to 5 As shown, the frame support structure of this embodiment is applied to an aircraft engine and is used to be arranged between a stator casing and a rotor support. The frame support structure includes:

[0046] The outer mounting edge 100 is used to connect with the stator casing for centering and load transmission;

[0047] The inner mounting edge 700 is used to connect with the rotor support for centering and load transmission;

[0048] The outer wall 400 is connected to the outer mounting edge 100;

[0049] The inner wall 600 is connected to the inner mounting edge 700 and forms an outer flow channel 401 with the outer wall 400. The inner surface of the inner wall 600 forms an inner flow channel 601.

[0050] The support plate structures 500 are respectively connected to the inner wall 600 and the outer wall 400. A plurality of support plate structures 500 are arranged along the circumference of the frame support structure to transfer loads.

[0051] The arc-shaped folding structure 200 is respectively arranged between the outer mounting edge 100 and the outer wall 400 and between the inner mounting edge 700 and the inner wall 600, and is used to bear the load transferred from the support plate structure area in a high temperature state to the stator casing and rotor support in a low temperature state, so as to alleviate the radial thermal deformation limitation of the supporting structure when subjected to high temperature.

[0052] The structural form of the connection between the outer mounting edge 100 and the stator casing and the structural form of the connection between the inner mounting edge 700 and the rotor support are realized by referring to the connection methods in the prior art, such as the use of circumferentially uniformly distributed bolts.

[0053] It can be understood that the frame support structure adopts a traditional double-wall structure design, which is used to be arranged between the stator casing and the rotor support. It is a rotating body structure as a whole like the stator casing and the rotor support. It has an outer wall 400 and an inner wall 600, and a support plate structure 500 is arranged between the two for connection and support and to transfer load based on the support plate structure 500. An outer flow channel 401 is formed between the outer wall 400 and the inner wall 600, and the inner wall 600 is the inner flow channel 601. Based on the aerodynamic performance requirements, the aerodynamic performance requirements can be met by adjusting the shape of the support plate and / or adjusting the size of the flow channel; the outer mounting edge 100 is arranged on the outer wall 400, and the inner mounting edge 700 is arranged on the inner wall 600. The outer mounting edge 100 located on the outermost ring is connected to the stator casing for centering and load transfer, and the inner mounting edge 700 located on the innermost ring is connected to the rotor support to transfer the rotor fulcrum load, respectively. An arc-shaped folding structure 200 is arranged between the outer wall 400 and the inner wall 600, and at the position of the outer wall 100, two ends of the arc-shaped folding structure 200 are respectively connected to the outer wall 400 and the outer wall 400, and at the position of the inner wall 700, two ends of the arc-shaped folding structure 200 are respectively connected to the inner wall 700 and the inner wall 600, so that in the working state, the arc-shaped folding structure 200 mainly bears the load transmitted from the support plate structure 500 area in the high temperature state to the outer stator and the inner support in the low temperature state. The flexible folding structure design based on the arc-shaped folding structure 200 relieves the radial thermal deformation limitation of the supporting structure when it is subjected to high temperature, effectively reduces the large stress generated by the connection ends of the inner and outer peripheries of the frame supporting structure due to high temperature expansion, and reduces the high stress level caused by the large thermal gradient in the working state, thereby improving the low cycle fatigue life of the components.

[0054] Specifically, the arc-shaped folding structure 200 includes an arc-shaped portion 202 and a first connecting portion 201 and a second connecting portion 203 arranged at intervals along the radial direction of the frame support structure. The two ends of the arc-shaped portion 202 are respectively connected to the first end of the first connecting portion 201 and the first end of the second connecting portion 203. The second end of the first connecting portion 201 is used to connect to the outer mounting edge 100, and the second end of the second connecting portion 203 is used to connect to the outer wall 400. Alternatively, the second end of the first connecting portion 201 is used to connect to the inner mounting edge 700, and the second connecting portion 203 is used to connect to the outer wall 400. The second end of 3 is used to connect with the inner wall 600, the arc-shaped folding structure 200 is connected with the outer mounting edge 100 through its first connecting portion 201, and is connected with the outer wall 400 through the second connecting portion 203. At the position of the inner mounting edge 700, the arc-shaped folding structure 200 is connected with the inner mounting edge 700 through its first connecting portion 201, and is connected with the inner wall 600 through the second connecting portion 203, and then in the working state, the arc-shaped portion 202 mainly bears the load transmitted from the support plate structure 500 area in the high temperature state to the outer stator and the inner peripheral support in the low temperature state;

[0055] It should be understood that the shape of the support plate structure 500 and the size design of the inner and outer flow channels 401 can be realized by referring to the existing design methods, and this embodiment will not elaborate on it. Specifically, the shape of the support plate structure 500 and the size of the inner and outer flow channels 401 can be iteratively optimized by finite element analysis so that the final result meets the aerodynamic performance requirements. It should be noted that the arc portion 202 is in a "⊂" shape or a "⊃" shape, that is, its design orientation can be designed according to the actual structural space matching, and it is more flexible; the first connecting portion 201 and the second connecting portion 203 are preferably designed in a straight cylinder shape, and the cross section of the arc portion 202 is semicircular, and the structure is tightly connected to maximize its stress release effect.

[0056] In some embodiments, the arc-shaped folding structure 200 is provided with a plurality of stress release structures 300, and the circumferential distribution position of the stress release structure 300 matches the circumferential distribution position of the support plate structure 500. By further providing the stress release structure 300 on the arc-shaped folding structure 200, the load transfer can be further reduced, the stress concentration problem can be improved, and the large stress caused by the high-temperature thermal expansion of the support plate can be reduced; based on this, the circumferential distribution position of the stress release structure 300 is set to match the circumferential distribution position of the support plate structure 500, even if the position of the stress release structure 300 matches the stress concentration area caused by the high-temperature thermal expansion of the support plate structure 500, the stress reduction effect is improved; preferably, the stress release structure 300 is a hole-shaped structure, and the stress release structure The circumferential dimension of 300 is designed to be 1.5-2 times the circumferential dimension of the support plate structure 500. If the circumferential dimension of the stress release structure 300 is less than 1.5 times the circumferential dimension of the support plate structure 500, the stress reduction effect is not obvious. If it is greater than 2 times the circumferential dimension of the support plate structure 500, the stress release structure 300 will be flattened, and greater stress will be generated at the side circle position due to stress concentration. It should be noted that the stress release structure 300 is preferably arranged on the arc-shaped folding structure 200 on the periphery to match the large stress area distribution and stress reduction requirements and reduce processing costs. In other embodiments, stress release structures 300 can also be provided on both the inner and outer arc-shaped folding structures 200 to improve stress release and reduction effects.

[0057] In some embodiments, the support plate structure 500 is a hollow structure, and the two ends of the support plate structure 500 are respectively connected to the outer surface of the outer wall 400 and the inner surface of the inner wall 600. It can be understood that the support plate structure 500 is a hollow structure, which is more conducive to lightweight design. On the other hand, it is more convenient to optimize the shape and flow channel size of the support plate structure 500, while maintaining a low mass change to optimize aerodynamic performance and reduce aerodynamic losses; further, the frame support structure includes an oil pipeline, which is connected to the lubricating oil pipeline of the engine and is used to pass through the support plate structure 500 to the fulcrum of the rotor support to guide The lubricating oil is introduced into the fulcrum of the rotor support, that is, the support plate structure 500 is designed to be a hollow structure, and the lubricating oil can be introduced into the rotor fulcrum at the periphery through the lubricating oil pipeline to provide lubrication; wherein, the support plate structure 500 is preferably evenly distributed along the circumference of the frame support structure to avoid unnecessary excitation sources, but when the oil supply and / or oil return position has special structural requirements, the support plate structure 500 can also be arranged with a non-uniform distribution. Regardless of whether the support plate structure 500 is a uniformly distributed or non-uniformly distributed structure, the number and circumferential distribution position of the stress release structure 300 are matched with the support plate structure 500 to ensure the stress reduction effect.

[0058] In some embodiments, the design method of the arc folding structure includes: S1. Calculating the load transmitted to the rotor support and / or to the stator casing by the radial thermal expansion of the support plate structure, the calculation formula is:

[0059] (1)

[0060] Where k is the stiffness of the arc-shaped part, and x is the radial displacement of the high-temperature support plate;

[0061] S2. The structural stiffness of the arc portion, the structural stiffness of the first connection portion, and the structural stiffness of the second connection portion are calculated using equations (2) to (4). The design formulas include:

[0062] (2)

[0063] (3)

[0064] (4)

[0065] In the formula, is the stiffness of the first connection, is the stiffness of the second connection, is the elastic modulus, and are the outer diameters of the first connecting part and the second connecting part, respectively, and are the inner diameter of the first connecting part and the inner diameter of the second connecting part, respectively, and are the length of the first connecting portion and the length of the second connecting portion respectively.

[0066] The above formula is used as the design basis and reference to realize the design of the frame supporting structure, and based on the above formula, it can be known that the stiffness of the arc-shaped folding structure can be adjusted by adjusting the length of the first connecting part and / or the length of the second connecting part and / or the outer diameter of the first connecting part and / or the outer diameter of the second connecting part and / or the inner diameter of the first connecting part and / or the inner diameter of the second connecting part, which has stronger applicability in the design process and highly matches the structural design requirements.

[0067] In some embodiments, the arc-shaped folding structure is provided with a plurality of hole-shaped stress release structures, and the design method further comprises step S3: designing the stiffness of the stress release structure region, and the design formula is:

[0068] (5)

[0069] In the formula, is the stiffness of the stress relief structure, and are the outer radius and inner radius of the arc part respectively, is the number of stress relief structures, The major axis width is constructed for stress relief, Construct the minor axis length for stress relief.

[0070] According to the above calculation formula and the relevant principles of material mechanics, the stiffness of the arc part And the stiffness of the stress relief hole area Less than the stiffness of a single-layer cylinder and Therefore, combined with formula (1), it can be seen that the use of folded structure and stress relief holes can reduce the load transmitted to the inner and outer mounting surfaces, thereby reducing stress and improving low-cycle fatigue life.

[0071] Further, the design method also includes: setting spatial structure size constraints and process constraints, and using finite element analysis to iteratively optimize the length of the first connection part and / or the length of the second connection part and / or the length of the third connection part and / or the outer diameter of the first connection part and / or the outer diameter of the second connection part and / or the outer arc radius of the third connection part and / or the inner diameter of the first connection part and / or the inner diameter of the second connection part and / or the inner arc radius of the third connection part and / or the number of stress release structures and / or the major axis width of the stress release structure and / or the minor axis length of the stress release structure; that is, adjusting the thickness, length and other dimensions of the arc folding structure can meet the high-temperature support plate expansion and deformation requirements, and optimizing the shape of the stress release hole to further reduce stress and improve low-cycle fatigue life. Through modeling, finite element analysis and iterative optimization, the corresponding design parameters can be quickly obtained based on computer software matching design requirements to improve efficiency. Further, the above design method is to iteratively optimize the length of the first and second connection parts of the arc folding structure, the thickness of the arc folding structure and the shape of the stress release structure using finite element analysis.

[0072] According to another aspect of the present invention, there is also provided an aircraft engine, which comprises the above-mentioned frame supporting structure.

[0073] Embodiment 1

[0074] In order to verify the effectiveness of the frame support structure proposed in the present invention, the stress and low cycle fatigue life of the existing frame support structure and the frame support structure proposed in the present invention under working conditions were simulated, and the comparison results are shown in Table 1:

[0075] Table 1 Comparison of simulation results of frame support structure stress and low cycle fatigue life

[0076]

[0077] Compared with the existing frame support structure, the maximum stress of the frame support structure proposed by the present invention is reduced by 29.8% under working condition (see the comparison of finite element stress simulation results). Figure 2 and Figure 6 ), the estimated low-cycle fatigue life increased by 894%. Currently, the frame support structure has been successfully applied to a certain type of civil turboshaft engine, and the low-cycle fatigue test of the whole machine has been completed.

[0078] 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 frame support structure, applied to an aircraft engine, used to be arranged between a stator casing and a rotor support, characterized in that: The frame support structure comprises: An outer mounting edge (100) is used to connect with the stator casing for centering and load transmission; An inner mounting edge (700) for connecting with a rotor support for centering and transferring loads; An outer wall (400) connected to the outer mounting edge (100); An inner wall (600) is connected to the inner mounting edge (700) and forms an outer flow channel (401) with the outer wall (400), and an inner surface of the inner wall (600) forms an inner flow channel (601); A support plate structure (500) is respectively connected to the inner wall (600) and the outer wall (400), and a plurality of the support plate structures (500) are arranged along the circumference of the frame support structure to transfer loads; The arc-shaped folding structure (200) is respectively arranged between the outer mounting edge (100) and the outer wall (400) and between the inner mounting edge (700) and the inner wall (600), and is used to bear the load transmitted from the support plate structure (500) area in a high temperature state to the stator casing and rotor support in a low temperature state, so as to alleviate the radial thermal deformation limitation of the support structure when subjected to high temperature.

2. The frame support structure according to claim 1, characterized in that: The arc-shaped folding structure (200) includes an arc-shaped portion (202) and a first connecting portion (201) and a second connecting portion (203) arranged at intervals along the radial direction of the frame support structure, wherein the two ends of the arc-shaped portion (202) are respectively connected to the first end of the first connecting portion (201) and the first end of the second connecting portion (203), the second end of the first connecting portion (201) is used to connect to the outer mounting edge (100), and the second end of the second connecting portion (203) is used to connect to the outer wall (400), or the second end of the first connecting portion (201) is used to connect to the inner mounting edge (700), and the second end of the second connecting portion (203) is used to connect to the inner wall (600).

3. The frame support structure according to claim 2, characterized in that: The arc-shaped folding structure (200) is provided with a plurality of stress release structures (300), and the circumferential distribution positions of the stress release structures (300) match the circumferential distribution positions of the support plate structure (500).

4. The frame support structure according to claim 3, characterized in that: The stress release structure (300) is a hole-shaped structure, and the circumferential dimension of the stress release structure (300) is 1.5-2 times the circumferential dimension of the support plate structure (500).

5. The frame support structure according to claim 2, characterized in that: The support plate structure (500) is a hollow structure, and two ends of the support plate structure (500) are respectively connected to the outer surface of the outer wall (400) and the inner surface of the inner wall (600).

6. The frame support structure according to claim 5, characterized in that: The frame support structure comprises an oil pipeline, which is connected to the lubricating oil pipeline of the engine and is used to pass through the support plate structure (500) to the support point of the rotor support so as to introduce lubricating oil to the support point of the rotor support.

7. The frame support structure according to any one of claims 2 to 6, characterized in that: The design method of the arc-shaped folding structure comprises: S1. Calculate the loads transmitted to the rotor support and / or to the stator casing due to the radial thermal expansion of the support plate structure. The calculation formula is: （1） In the formula, k is the stiffness of the arc part, and x is the radial displacement of the high-temperature support plate; S2. Calculate the structural stiffness of the arc part, the first connection part and the second connection part using equations (2)-(4). The design formula includes （2） （3） （4） In the formula, is the stiffness of the first connection, is the stiffness of the second connection, is the elastic modulus, and are the outer diameters of the first connecting part and the second connecting part, respectively, and are the inner diameter of the first connecting part and the inner diameter of the second connecting part, respectively, and are the length of the first connecting portion and the length of the second connecting portion respectively.

8. The frame support structure according to claim 7, characterized in that: The arc-shaped folding structure is provided with a plurality of hole-shaped stress release structures, and the design method further comprises step S3: designing the stiffness of the stress release structure region, the design formula is: （5） In the formula, is the stiffness of the stress relief structure, and are the outer radius and inner radius of the arc part respectively, is the number of stress relief structures, The major axis width is constructed for stress relief, Construct the minor axis length for stress relief.

9. The frame support structure according to claim 8, characterized in that: The design method also includes: setting spatial structure size constraints and process constraints, and using finite element analysis to iteratively optimize the length of the first connection part and / or the length of the second connection part and / or the length of the third connection part and / or the outer diameter of the first connection part and / or the outer diameter of the second connection part and / or the outer arc radius of the third connection part and / or the inner diameter of the first connection part and / or the inner diameter of the second connection part and / or the inner arc radius of the third connection part and / or the number of stress release structures and / or the major axis width of the stress release structure and / or the minor axis length of the stress release structure of the arc folding structure.

10. An aircraft engine, characterized in that: The frame supporting structure according to any one of claims 1 to 9 is used.

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