Aero-engine spigot connecting structure

Abstract

The invention provides a spigot connecting structure of an aero-engine, a flange mounting edge comprises a radial limiting part and an axial limiting part, a flange structure comprises a radial connecting part and an axial connecting part, and the radial limiting part and the axial limiting part are in one-to-one correspondence with the side walls of the radial connecting part and the axial connecting part respectively to abut against the side walls of the radial connecting part and the axial connecting part. Deformation containing grooves are formed in the sides, facing the flange structure, of the radial limiting parts and the axial limiting parts, and bolts penetrate through the first bolt holes and the second bolt holes to fix the flange structure and the flange mounting edge. According to the seam allowance connecting structure of the aero-engine, the radial rigidity of the convex seam allowance structure is reduced through the deformation containing groove, when the temperature of the seam allowance connecting structure rises, the radial limiting part and the axial limiting part are flexibly deformed in the axis direction under the extrusion effect of the flange structure in the axis direction, and therefore the seam allowance connecting structure of the aero-engine is formed. Therefore, deformation matching of the convex seam allowance structure and the concave seam allowance structure under different thermal expansion amounts is achieved, and the connecting stress between the flange structure and the flange mounting edge is relieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of spigot connectors, and particularly relates to a spigot connection structure for an aero-engine. Background Art

[0002] The connection and centering of the stator parts inside the engine are crucial for the stable operation of the engine. Currently, flanges and spigot structures are widely used inside the engine to achieve the connection and centering of the stator parts. This structural design plays an important role in ensuring the relative position accuracy between parts and the stability of the overall structure.

[0003] Among the parts with different materials inside the engine, and based on the large differences in the thermal expansion coefficients of parts with different materials, parts made of low-expansion coefficient materials are often designed as concave spigots, and parts made of high-thermal expansion coefficient materials are designed as convex spigots. The spigot structure adopts an interference fit method. During the operation of the engine, as the temperature rises, the thermal expansion deformation of the low-expansion coefficient parts is small, and the thermal expansion deformation of the high-thermal expansion coefficient material parts is large, enabling the concave spigot with small thermal deformation to tightly sleeve the convex spigot structure with large thermal deformation, thereby ensuring the tightness of the spigot connection in a high-temperature environment and maintaining the high precision and stability of the internal structure of the engine.

[0004] However, there are obvious defects in the application of this design in the prior art; that is, when the difference in the thermal expansion coefficients of the two materials is too large, the difference in the thermal expansion amounts of the two materials caused by the temperature change during the operation of the engine also becomes significant, resulting in an increase in the deformation stress borne by the spigot position. The excessive deformation stress will not only damage the structural integrity of the parts, but also easily cause harmful deformation at the connection position, resulting in cracks on the surface of the parts and even connection failure, affecting the normal operation and service life of the engine. Summary of the Invention

[0005] In view of the above problems, the present invention provides a spigot connection structure for an aero-engine, including: a flange structure, a flange mounting edge, and bolts. The flange mounting edge includes a radial limiting portion and an axial limiting portion. The free end of the radial limiting portion is connected to the inner wall of the high-temperature sleeve member. The flange structure includes a radial connecting portion and an axial connecting portion. The free end of the axial connecting portion is connected to the outer wall of the low-temperature sleeve member;

[0006] The radial limiting portion and the axial limiting portion respectively form abutments with the side walls of the radial connecting portion and the axial connecting portion one by one, and deformation receiving grooves are provided on the sides of the radial limiting portion and the axial limiting portion facing the flange structure;

[0007] A plurality of first bolt holes and second bolt holes arranged in alignment are respectively provided on the side walls of the radial connecting portion and the radial limiting portion, and the bolts pass through the first bolt holes and the second bolt holes to fix the flange structure and the flange mounting edge.

[0008] Further, a plurality of weight-reducing lace patterns are formed on the side wall of the radial connecting portion facing away from the flange mounting edge, and the plurality of weight-reducing lace patterns are respectively arranged between adjacent first bolt holes.

[0009] Further, a plurality of weight-reducing grooves are also formed on the side wall of the radial connecting portion facing away from the flange mounting edge, and the plurality of weight-reducing grooves are respectively arranged between adjacent first bolt holes, and the weight-reducing grooves and the weight-reducing lace patterns are arranged inside and outside with respect to the axis line of the flange mounting edge.

[0010] Further, when the radius of the axial limiting portion is less than 100 mm, the edge distances between the weight-reducing grooves, the weight-reducing lace patterns and the adjacent first bolt holes are all equal to 2 mm;

[0011] When the radius of the axial limiting portion is greater than or equal to 100 mm, the edge distances between the weight-reducing grooves, the weight-reducing lace patterns and the adjacent first bolt holes are all 0.02 times the radius of the axial limiting portion.

[0012] Further, the edge distance between the side wall of the weight-reducing groove away from the weight-reducing lace pattern and the edge of the weight-reducing lace pattern is 1.9 - 2.1 mm.

[0013] Further, the outer radius of the radial connecting portion is greater than the edge distance between the weight-reducing lace pattern and the adjacent first bolt hole.

[0014] Further, the deformation receiving groove includes a radial groove formed in the radial limiting portion and an axial groove formed in the axial limiting portion, and the radial groove and the axial groove communicate with each other.

[0015] Further, the thickness of the axial limiting portion at the axial groove is 1 - 2.5 mm;

[0016] The axial length of the axial groove is greater than the thickness of the axial limiting portion at the axial groove, and the axial length of the axial groove is less than three times the thickness of the axial limiting portion at the axial groove.

[0017] Further, a predetermined distance is maintained between the radial groove and the second bolt hole.

[0018] Further, the inner walls of the deformation receiving grooves all adopt curved surface transitions.

[0019] Compared with the prior art, the embodiments of the present invention have at least the following advantages:

[0020] The stop connection structure of the aero-engine of the present invention, on the basis that the expansion coefficient of the low-temperature sleeve part is lower than that of the high-temperature sleeve part, realizes the fixed connection of the flange structure and the flange mounting edge by bolts passing through the first bolt hole and the second bolt hole, and deforms and stores grooves on one side of the radial limiting part and the axial limiting part facing the flange structure to provide deformation space for the flange mounting edge; the radial stiffness of the convex stop structure is reduced through the deformation storage groove. When the temperature of the stop connection structure rises, under the extrusion of the flange structure in the axial direction of the axis, the radial limiting part and the axial limiting part flexibly deform in the axial direction of the axis, so as to realize the deformation matching of the convex stop structure and the concave stop structure under different thermal expansion amounts, relieve the stress between the flange structure and the flange mounting edge, and ensure the safety and reliability of the stop connection structure.

[0021] Other features and advantages of the present invention will be described in the following description, and, in part, will be obvious from the description, or will be understood by implementing the present invention. The objectives and other advantages of the present invention can be achieved and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to explain the technical solutions in the embodiments of the present invention or the prior art more clearly, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative work.

[0023] Figure 1 It shows a partial structural schematic diagram of the flange structure in the embodiment of the present invention;

[0024] Figure 2 It shows a partial structural schematic diagram of the flange mounting edge in the embodiment of the present invention;

[0025] Figure 3 It shows a cross-sectional schematic diagram of the stop connection structure of the aero-engine in the embodiment of the present invention;

[0026] Figure 4 It shows a schematic diagram of the flange structure in the embodiment of the present invention;

[0027] Figure 5 It shows a schematic diagram of the flange mounting edge in the embodiment of the present invention.

[0028] In the figure, low-temperature sleeve part 1', high-temperature sleeve part 2', flange structure 1, radial connection part 101, axial connection part 102, flange mounting edge 2, radial limiting part 201, axial limiting part 202, bolt 3, deformation storage groove 4, radial groove 401, axial groove 402, first bolt hole 5, second bolt hole 6, weight-reducing lace 7, weight-reducing groove 8. Detailed implementation manners

[0029] The following description provides many different embodiments or examples for implementing different features of the present invention. The components and arrangements described in the following specific examples are only used to concisely express the present invention, and they are only examples and not intended to limit the present invention.

[0030] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the scope of protection of the present invention.

[0031] The present invention provides a spigot connection structure for an aeroengine. Figure 1 The partial structural schematic diagram of the flange structure in the embodiment of the present invention is shown. Refer to Figure 1 , Figure 2 and Figure 3 , the spigot connection structure for an aeroengine includes: a flange structure 1, a flange mounting edge 2, and bolts 3. The flange mounting edge 2 includes a radial limiting portion 201 and an axial limiting portion 202. The free end of the radial limiting portion 201 is connected to the inner wall of the high-temperature sleeve member 2'. The flange structure 1 includes a radial connecting portion 101 and an axial connecting portion 102. The free end of the axial connecting portion 102 is connected to the outer wall of the low-temperature sleeve member 1'.

[0032] The radial limiting portion 201 and the axial limiting portion 202 respectively form abutments with the side walls of the radial connecting portion 101 and the axial connecting portion 102 one by one. A deformation receiving groove 4 is formed on one side of the radial limiting portion 201 and the axial limiting portion 202 facing the flange structure 1.

[0033] A plurality of first bolt holes 5 and second bolt holes 6 arranged in alignment are respectively formed on the side walls of the radial connecting portion 101 and the radial limiting portion 201. The bolt 3 passes through the first bolt hole 5 and the second bolt hole 6 to realize the fixed connection between the flange structure 1 and the flange mounting edge 2.

[0034] Corresponding to the low-temperature sleeve member 1' and the high-temperature sleeve member 2' that are sleeved at intervals inside and outside, on the basis of the production and processing of the low-temperature sleeve member 1', a flange structure 1 is added to form a concave spigot structure. On the basis of the production and processing of the high-temperature sleeve member 2', a flange mounting edge 2 is added to form a convex spigot structure.

[0035] It should be additionally noted that both the flange structure 1 and the flange mounting edge 2 adopt an annular structure.

[0036] During the actual use of the device of the present invention, with the increase in the working environment temperature, the low-temperature sleeve member 1', the flange structure 1, the high-temperature sleeve member 2', and the flange mounting edge 2 all expand. However, based on the fact that the expansion coefficient of the low-temperature sleeve member 1' is lower than that of the high-temperature sleeve member 2', the concave stop structure with a small expansion deformation and the convex stop structure with a large expansion deformation further improve the socket tightness between the concave stop structure and the convex stop structure on the basis of the original socket state, ensuring the basic operation requirement of the tight connection of the stop connection structure of the present invention.

[0037] Meanwhile, on the basis of opening the deformation receiving groove 4 on the side of the radial limiting portion 201 and the axial limiting portion 202 facing the flange structure 1, the stress intensity of the flange mounting edge 2 at the deformation receiving groove 4 is reduced, enabling the flange mounting edge 2 to have a deformation margin at the receiving groove 101; with the further increase in the environmental temperature, the difference in the deformation degrees of the low-temperature sleeve member 1' and the high-temperature sleeve member 2' further increases. The receiving groove 101 provides a margin space for the deformation of the flange mounting edge 2, thereby alleviating the force between the flange structure 1 and the flange mounting edge 2, preventing harmful deformation or cracks from occurring at the stop connection position and causing the stop connection to fail, which may endanger the normal operation of the aero-engine.

[0038] The device provided by the present invention refers to Figure 4 and Figure 5 , on the basis that the expansion coefficient of the low-temperature sleeve member 1' is lower than that of the high-temperature sleeve member 2', the bolt 3 passes through the first bolt hole 5 and the second bolt hole 6 to realize the fixed connection between the flange structure 1 and the flange mounting edge 2, and the deformation receiving groove 4 is opened on the side of the radial limiting portion 201 and the axial limiting portion 202 facing the flange structure 1 to provide a deformation space for the flange mounting edge 2; the radial stiffness of the convex stop structure is reduced through the deformation receiving groove 4. When the temperature of the stop connection structure rises, under the squeezing action of the flange structure 1 in the axial direction of the axis, the radial limiting portion 201 and the axial limiting portion 202 undergo flexible deformation in the axial direction of the axis, thereby realizing the deformation matching of the convex stop structure and the concave stop structure under different thermal expansion amounts, alleviating the stress between the flange structure 1 and the flange mounting edge 2, and ensuring the safety and reliability of the stop connection structure.

[0039] Among them, a plurality of weight-reducing lace patterns 7 are provided on the radial connection portion 101 in a circumferential arrangement, and the plurality of weight-reducing lace patterns 7 are correspondingly arranged between adjacent first bolt holes 5. In Figure 4 the example shown, a plurality of first bolt holes 5 are arranged in a circumferential array with respect to the axis of the flange structure 1. Correspondingly, a plurality of weight-reducing lace patterns 7 are arranged in a circumferential array with respect to the axis of the flange structure 1;

[0040] In addition, the cross-section of the weight-reducing lace pattern 7 adopts a fan-shaped structure.

[0041] Meanwhile, a plurality of weight reduction grooves 8 are also formed on the side wall of the radial connection portion 101 facing away from the flange mounting edge 2 to ensure the airtightness of the side wall of the radial connection portion 101 facing the flange mounting edge 2, thereby ensuring the tight fitting between the flange mounting edge 2 and the radial connection portion 101; the stiffness of the flange structure 1 is reduced by the weight reduction grooves 8, and thus the circumferential stiffness of the spigot connection structure is effectively reduced.

[0042] In this embodiment, a plurality of the weight reduction grooves 8 are correspondingly arranged between adjacent first bolt holes 5 one by one, and the plurality of weight reduction grooves 8 are arranged in a circumferential array about the axis of the flange mounting edge 2, and the weight reduction grooves 8 and the weight reduction lace 7 are arranged inside and outside about the axis of the flange mounting edge 2 to ensure the balance of the overall structure of the flange mounting edge 2.

[0043] In this embodiment, the distance between the weight reduction lace 7 and the edge of the adjacent first bolt hole 5 and the distance between the weight reduction groove 8 and the edge of the adjacent first bolt hole 5 are both kept the same.

[0044] When the radius of the axial limiting portion 202 is less than 100 mm, the distances between the weight reduction groove 8, the weight reduction lace 7 and the edge of the adjacent first bolt hole 5 are all equal to 2 mm;

[0045] When the radius of the axial limiting portion 202 is greater than or equal to 100 mm, the distances between the weight reduction groove 8, the weight reduction lace 7 and the edge of the adjacent first bolt hole 5 are all 0.02 times the radius of the axial limiting portion 202, and the formula is:

[0046] t2 = t3 = r * 0.02 (1)

[0047] In the formula, t2 represents the distance between the weight reduction lace 7 and the edge of the adjacent first bolt hole 5, t3 represents the distance between the weight reduction groove 8 and the edge of the adjacent first bolt hole 5, and r represents the inner radius of the axial limiting portion 202.

[0048] Among them, the distance between the side wall of the weight reduction groove 8 far from the weight reduction lace 7 and the edge of the weight reduction lace 7 is 1.9 - 2.1 mm to ensure the thickness requirement of the axial connection portion 102.

[0049] Meanwhile, the distance between the outer side wall of the radial connection portion 101 and the edge of the adjacent first bolt hole 5 is greater than the distance between the weight reduction lace 7 and the edge of the adjacent first bolt hole 5; for example, the distance t1 between the outer side wall of the radial connection portion 101 and the edge of the adjacent first bolt hole 5 is 0.01 mm greater than the distance t2 between the weight reduction lace 7 and the edge of the adjacent first bolt hole 5.

[0050] Correspondingly, the deformation storage groove 4 includes a radial groove 401 formed in the radial limiting portion 201 and an axial groove 402 formed in the axial limiting portion 202, and the radial groove 401 and the axial groove 402 communicate with each other; the radial groove 401 provides a deformation space for the radial limiting portion 201, and the axial groove 402 provides a deformation space for the axial limiting portion 202. Furthermore, during the expansion of the flange mounting edge 2, the deformation space and the deformation angle range of the radial limiting portion 201 and the axial limiting portion 202 are increased, and the stress relief effect of the deformation storage groove 4 on the flange mounting edge 2 is further expanded.

[0051] Exemplarily, a predetermined distance is set between the radial groove 401 and the second bolt hole 6 to prevent the radial groove 401 from intersecting with the second bolt hole 6, thereby affecting the fixing effect of the bolt 3 on the flange structure 1 and the flange mounting edge 2.

[0052] Meanwhile, the thickness δ of the axial limiting portion 202 at the axial groove 402 is 1 - 2.5 mm; specifically:

[0053] When the radius r of the axial limiting portion 202 is less than 100 mm, the thickness δ of the axial limiting portion 202 at the axial groove 402 is 1 mm;

[0054] When the radius r of the axial limiting portion 202 is greater than 250 mm, the thickness δ of the axial limiting portion 202 at the axial groove 402 is 2.5 mm;

[0055] When the radius r of the axial limiting portion 202 is greater than or equal to 100 mm and less than or equal to 250 mm, the thickness δ of the axial limiting portion 202 at the axial groove 402 is 0.01 times the radius r of the axial limiting portion 202.

[0056] Correspondingly, in Figure 3 the example shown, the axial length L of the axial groove 402 is greater than the thickness δ of the axial limiting portion 202 at the axial groove 402, and the axial length L of the axial groove 402 is less than three times the thickness δ of the axial limiting portion 202 at the axial groove 402. The formula is:

[0057] 3δ>L>δ (2)

[0058] In the formula, δ represents the thickness of the axial limiting portion 202 at the axial groove 402, and L represents the axial length of the axial groove 402.

[0059] In addition, the inner walls of the deformation storage groove 4 all adopt curved surface transitions to avoid right angles on the inner walls of the deformation storage groove 4 and improve the limit of the expansion or contraction space of the storage groove 4.

[0060] To further illustrate the device of the present application, taking the low-temperature sleeve part 1' made of titanium alloy and the high-temperature sleeve part 2' made of superalloy as an example, the thermal expansion coefficient of the low-temperature sleeve part 1' is 8.6×10⁻⁶ m / K, and the thermal expansion coefficient of the high-temperature sleeve part 2' is 15×10⁻⁶ m / K.

[0061] The inner radius of the axial limiting part 202 is 180 mm, the distance t2 between the weight-reducing lace 7 and the edge of the adjacent first bolt hole 5 is 3.6 mm, the distance t3 between the weight-reducing groove 8 and the edge of the adjacent first bolt hole 5 is 3.6 mm, and the distance t1 between the outer side wall of the straight part 101 and the edge of the adjacent first bolt hole 5 is 3.7 mm.

[0062] The thickness δ of the axial limiting part 202 at the axial groove 402 is 1.8 mm, and the axial length L of the axial groove 402 is 4 mm.

[0063] The axial connection part 102 and the axial limiting part 202 are installed by interference fit, and the flange structure 1 and the flange mounting edge 2 are fixed by bolts 3 passing through the first bolt holes 5 and the second bolt holes 6.

[0064] During cold-state assembly, H7 / r6 is used for interference fit, and the interference amount is 0.1 to 0.15 mm. In the working state, the temperature at the mating surface connection position can rise to 500 °C, and its interference amount will increase to 0.6 mm. Through the deformation receiving groove 4, the radial limiting part 201 and the axial limiting part 202 of the flange mounting edge 2 deform, realizing the mitigation of stress and avoiding the generation of cracks and damage to the mating surface connection structure.

[0065] Among them, H7 / r6 indicates that the tolerance zone of the hole is H7 (basic hole, tolerance grade 7), and the tolerance zone of the shaft is r6 (tolerance grade 6).

[0066] In the description of the present invention, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present invention, "a plurality" means two or more unless otherwise specifically defined.

[0067] In the description of the present invention, it should be noted that, unless otherwise clearly specified and defined, the terms "installed", "connected", and "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or a connection that allows mutual communication; it can be a direct connection, or an indirect connection through an intermediate medium, and it can be the internal communication of multiple components or the interaction relationship between multiple components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0068] In the description of the present invention, it should be understood that all terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and should not be construed as a limitation of the present invention.

[0069] Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An abutting connection structure for an aero-engine, which is used to connect a low-temperature sleeve component (1’) and a high-temperature sleeve component (2’), and is characterized in that, Including: A flange structure (1), a flange mounting edge (2) and bolts (3). The flange mounting edge (2) includes a radial limiting portion (201) and an axial limiting portion (202). The free end of the radial limiting portion (201) is connected to the inner wall of a high-temperature sleeve member (2'), and the flange structure (1) includes a radial connecting portion (101) and an axial connecting portion (102). The free end of the axial connecting portion (102) is connected to the outer wall of a low-temperature sleeve member (1'); The radial limiting portion (201) and the axial limiting portion (202) respectively and correspondingly abut against the side walls of the radial connecting portion (101) and the axial connecting portion (102). A deformation receiving groove (4) is formed on the side facing the flange structure (1) of the radial limiting portion (201) and the axial limiting portion (202); A plurality of first bolt holes (5) and second bolt holes (6) arranged in alignment are respectively formed on the side walls of the radial connecting portion (101) and the radial limiting portion (201). The bolts (3) pass through the first bolt holes (5) and the second bolt holes (6) to fix the flange structure (1) and the flange mounting edge (2).

2. The spigot connection structure of the aero-engine according to claim 1, wherein A plurality of weight-reducing lace patterns (7) are formed on the side wall of the radial connecting portion (101) facing away from the flange mounting edge (2). The plurality of weight-reducing lace patterns (7) are respectively arranged corresponding to the spaces between adjacent first bolt holes (5).

3. The spigot connection structure of an aeroengine according to claim 2, characterized in that A plurality of weight-reducing grooves (8) are also formed on the side wall of the radial connecting portion (101) facing away from the flange mounting edge (2). The plurality of weight-reducing grooves (8) are respectively arranged corresponding to the spaces between adjacent first bolt holes (5), and the weight-reducing grooves (8) and the weight-reducing lace patterns (7) are arranged inside and outside with respect to the axis line of the flange mounting edge (2).

4. The aviation engine spigot connection structure according to claim 3, characterized in that, When the radius of the axial limiting portion (202) is less than 100 mm, the distances between the weight-reducing grooves (8), the weight-reducing lace patterns (7) and the edges of the adjacent first bolt holes (5) are all equal to 2 mm; When the radius of the axial limiting portion (202) is greater than or equal to 100 mm, the distances between the weight-reducing grooves (8), the weight-reducing lace patterns (7) and the edges of the adjacent first bolt holes (5) are all 0.02 times the radius of the axial limiting portion (202).

5. The aviation engine spigot connection structure according to claim 4, characterized in that The distance between the side wall of the weight-reducing groove (8) away from the weight-reducing lace pattern (7) and the edge of the weight-reducing lace pattern (7) is 1.9 - 2.1 mm.

6. The spigot connection structure of an aero-engine according to claim 5, characterized in that, The outer radius of the radial connecting portion (101) is greater than the distance between the weight-reducing lace pattern (7) and the edge of the adjacent first bolt hole (5).

7. The butt-joint connection structure of an aero-engine according to any one of claims 1-6, characterized in that, The deformation receiving groove (4) includes a radial groove (401) formed on the radial limiting portion (201) and an axial groove (402) formed on the axial limiting portion (202), and the radial groove (401) and the axial groove (402) communicate with each other.

8. The spigot connection structure of an aero-engine according to claim 7, characterized in that, The thickness of the axial limiting portion (202) at the axial groove (402) is 1 - 2.5 mm; The axial length of the axial groove (402) is greater than the thickness of the axial limiting portion (202) at the axial groove (402), and the axial length of the axial groove (402) is less than three times the thickness of the axial limiting portion (202) at the axial groove (402).

9. The aviation engine spigot connection structure according to claim 8, wherein, A predetermined distance is maintained between the radial groove (401) and the second bolt hole (6).

10. The aviation engine spigot connection structure according to claim 7, characterized in that, The inner walls of the deformation storage groove (4) are all transitioned by curved surfaces.

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