Aero-engine supporting structure and supporting device

Abstract

The invention provides an aero-engine supporting structure and a supporting device. The aero-engine supporting structure comprises an adapter shaft, a base and a supporting seat. A connecting part is arranged at one end of the adapter shaft and used for being connected with an intermediate case of the aero-engine, a square shaft is arranged at the other end of the adapter shaft, and the section of the square shaft is square. The base is provided with a square groove, and the section shape of the square groove is matched with that of the square shaft. The square shaft is installed in the square groove, and the size of the cross section of the square groove is larger than that of the cross section of the square shaft, so that the square shaft is in clearance fit with the square groove. One circumferential side of the square groove is opened to form an opening for the square shaft to enter and exit from the square groove. The supporting seat is movably connected with the base to open or close the opening, the square shaft is arranged on the adapter shaft, and the square shaft is in small clearance fit with the square groove, so that accurate positioning of the adapter shaft on the base can be guaranteed, and the butt joint assembly quality is improved.

Description

Technical Field

[0001] This invention relates to the field of aero-engine assembly structure technology, and more specifically, to an aero-engine support structure and support device. Background Technology

[0002] Aero engines are complex in structure, require precise manufacturing and assembly, and are large in size and weight. They are difficult to lift and adjust in attitude, making assembly and manufacturing extremely challenging. Ensuring the safe and stable support and precise positioning of the engine during assembly is crucial. In the assembly of civil aero engines, they need to be supported on assembly racks or transport vehicles, requiring the use of support structures for connection.

[0003] Currently, the support structure of aero engines generally adopts the following... Figure 1 and Figure 2 The structure shown consists of a support 1, a connecting sleeve 2, a circular support shaft 3, and a pin 4. One end of the circular support shaft 3 is mounted on the adapter seat of the intermediate casing 5 of the aircraft engine load-bearing casing and is fixed with bolts; it is the main load-bearing pin. The other end of the circular support shaft 3 is supported in the square groove 6 of the connecting sleeve 2, and the circular support shaft 3 is fixed above the square groove 6 with the pin 4. The connecting sleeve 2 is mounted on the support 1, and the support 1 is connected to the column 7 for support on the bottom surface. However, the inventors discovered that in actual assembly and use, this structure presents several challenges. First, aligning the square groove of the connecting sleeve with the circular support shaft is difficult. During installation, the circular support shaft frequently jams, resulting in inaccurate positioning within the groove of the connecting sleeve. This prevents the engine axis from aligning with the axis of the entire support column, hindering on-site judgment and adjustment of the engine axis's alignment with the track using the relative position of the columns. Furthermore, the critical processes in engine assembly—the core engine main unit docking and assembly, and the low-voltage main unit docking and assembly (including assembly and disassembly)—both place strict requirements on the engine's posture. Inconsistent axes can easily lead to parts jamming during docking, affecting assembly progress and quality. Second, the support columns are located on both sides of the intermediate casing, and the components close to the casing surface can obstruct some parts, preventing assembly. Summary of the Invention

[0004] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0005] The purpose of this invention is to provide an aircraft engine support structure that can provide stable and reliable support for the aircraft engine and ensure assembly performance.

[0006] Another objective of this invention is to provide an aircraft engine support device that can provide stable and reliable support for the aircraft engine and ensure assembly performance.

[0007] Embodiments of the present invention can be implemented in the following ways:

[0008] An aircraft engine support structure is provided for supporting an aircraft engine during assembly; the aircraft engine support structure includes:

[0009] The adapter shaft has a connecting part at one end for connecting to the intermediate casing of the aircraft engine, and a square shaft at the other end for connecting to the intermediate casing of the aircraft engine.

[0010] A base having a square groove whose cross-sectional shape matches that of a square shaft; the square shaft being installed in the square groove, wherein the cross-sectional dimension of the square groove is larger than that of the square shaft, so that the square shaft and the square groove have a clearance fit; one circumferential side of the square groove is open to allow the square shaft to enter and exit the square groove; and a support seat being movably connected to the base to open or close the opening.

[0011] Optionally, the base includes a base plate, a first limiting part, and a second limiting part. One end of the first limiting part is fixedly connected to the base plate, and the other end of the first limiting part is fixedly connected to the second limiting part. The second limiting part is spaced apart from the base plate so that the base plate, the first limiting part, and the second limiting part together define the square groove. The opening of the square groove is located on the side directly opposite to the first limiting part.

[0012] Optionally, the support base includes a support plate, a first connecting arm, and a second connecting arm. The first connecting arm and the second connecting arm are fixedly connected to both ends of the support plate, and the first connecting arm and the second connecting arm extend in opposite directions. The first connecting arm is connected to the second limiting part, and the second connecting arm is connected to the bottom plate on the side of the square groove away from the first limiting part. When the support base closes the opening, the support plate is located at the opening to form a circumferentially closed square groove through the bottom plate, the first limiting part, the second limiting part, and the support plate.

[0013] Optionally, the base plate has a first bolt hole, the second connecting arm has a second bolt hole, and the aircraft engine support structure further includes a connecting bolt, which passes through the first bolt hole and the second bolt hole to lock the base plate and the second connecting arm together.

[0014] Optionally, the support base is rotatably connected to the base.

[0015] Optionally, the gap between the square groove and the square shaft is d, where 0.5mm ≤ d ≤ 1mm.

[0016] Optionally, the aircraft engine support structure further includes a side support end cap, which is fixedly connected to the base and located at one axial end of the square groove to limit the position of the square shaft in the axial direction of the square groove.

[0017] Optionally, the adapter shaft further includes a tapered shaft segment connected between the square shaft and the connecting portion, wherein the cross-sectional dimensions of the tapered shaft segment decrease along the direction from the square shaft to the connecting portion.

[0018] Optionally, the connecting part includes a connecting flange and a cylindrical mating section located on the side of the connecting flange away from the square shaft. The cylindrical mating section is used to mate with the intermediate housing, and the connecting flange is used to be fixedly connected to the intermediate housing.

[0019] An aircraft engine support device includes a C-ring and an aircraft engine support structure as described above. Two aircraft engine support structures are fixedly connected to both sides of the C-ring. The two aircraft engine support structures are used to connect to the radial ends of an intermediate casing to support the intermediate casing. The C-ring is a C-shaped structure with a notch at the lower end.

[0020] The beneficial effects of the aero-engine support structure and support device provided by the embodiments of the present invention include:

[0021] Embodiments of the present invention provide an aircraft engine support structure, comprising an adapter shaft, a base, and a support seat. One end of the adapter shaft has a connecting portion for connecting to an intermediate casing of the aircraft engine, and the other end of the adapter shaft has a square shaft with a square cross-section. The base has a square groove, the cross-sectional shape of which matches the cross-sectional shape of the square shaft. The square shaft is installed in the square groove, and the cross-sectional dimension of the square groove is larger than that of the square shaft, so that the square shaft and the square groove have a clearance fit. One circumferential side of the square groove is open to form an opening for the square shaft to enter and exit the groove. The support base and the base are movably connected to open or close the opening. When the opening is open, the square shaft can pass through the opening and exit the square slot. When the opening is closed, the square slot is circumferentially closed, and the square shaft is confined in the square slot. By setting the square shaft on the adapter shaft and cooperating with the square slot, the precise positioning of the adapter shaft on the base can be ensured. At the same time, the small clearance between the square shaft and the square slot ensures the attitude of the aircraft engine after support, making it easier to align the aircraft engine axis with the crane axis and improve the docking and assembly quality.

[0022] Embodiments of the present invention also provide an aircraft engine support device, which includes the above-mentioned aircraft engine support structure. Therefore, it also has the beneficial effects of ensuring the precise positioning of the adapter shaft on the base, ensuring the attitude of the aircraft engine after support, facilitating the alignment of the aircraft engine axis with the vehicle axis, and improving the docking and assembly quality. Attached Figure Description

[0023] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0024] Figure 1 A schematic diagram of the supporting structure in the prior art is shown;

[0025] Figure 2 This shows a schematic diagram of the support structure in the prior art from another perspective;

[0026] Figure 3 A schematic diagram of the structure of an aircraft engine support device provided according to one aspect of the present invention is shown;

[0027] Figure 4 A schematic diagram of an aircraft engine support structure according to one aspect of the present invention is shown;

[0028] Figure 5 A schematic diagram of the structure of the aircraft engine support structure provided according to one aspect of the present invention is shown when the support seat opens the opening of the square slot;

[0029] Figure 6 A schematic diagram of the base in an aircraft engine support structure provided according to one aspect of the present invention is shown;

[0030] Figure 7 A schematic diagram of the structure at the junction of the base and the square shaft in an aircraft engine support structure provided according to one aspect of the present invention is shown.

[0031] Figure 8 A schematic diagram of the support base in an aircraft engine support structure provided according to one aspect of the present invention is shown;

[0032] Figure 9 A schematic diagram of the side support end cap in an aircraft engine support structure provided according to one aspect of the present invention is shown;

[0033] Figure 10 A schematic diagram of the structure of the adapter shaft in the aircraft engine support structure provided according to one aspect of the present invention is shown.

[0034] 10-Aircraft engine support device; 100-Aircraft engine support structure; 110-Base; 111-Base plate; 112-First plate section; 113-Second plate section; 114-First limiting section; 115-Second limiting section; 116-Square groove; 117-Groove; 118-First bolt hole; 119-Mounting groove; 120-Support seat; 121-First connecting arm; 122-Rotating shaft hole; 123-Support plate; 124-Second connecting arm; 125-Second bolt hole; 130-Adapter shaft; 131-Square shaft; 132-Conical shaft section; 133-Connecting part; 134-Connecting flange; 135-Cylindrical mating section; 140-Side support end cap; 150-Connecting bolt;

[0035] 200-C-ring; 300-intermediate casing. Detailed Implementation

[0036] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0037] In the description of this invention, it should be noted that if terms such as "upper," "lower," "inner," "outer," or "vertical" appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use, and does not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0038] At the same time, it should be noted that the terms "first" and "second" are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.

[0039] In the description of this invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, an integral connection, or a detachable connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or a connection within two components, etc. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0040] Figure 3 A schematic diagram of the structure of the aircraft engine support device 10 provided for this embodiment. Figure 4 This is a schematic diagram of the aero-engine support structure 100 provided in this embodiment. Figure 5 This is a schematic diagram of the structure of the aircraft engine support structure 100 provided in this embodiment, in which the support base 120 opens the opening of the square slot 116. Figure 6 This is a structural diagram of the base 110 in the aircraft engine support structure 100 provided in this embodiment. Please refer to the diagram for further details. Figures 3-6 This embodiment provides an aircraft engine support structure 100 and an aircraft engine support device 10.

[0041] Specifically, the aircraft engine support device 10 includes a C-ring 200 and the aforementioned aircraft engine support structure 100. Two aircraft engine support structures 100 are fixed relative to each other on both sides of the C-ring 200, and are used to connect to the radial ends of the intermediate casing 300, thereby supporting the intermediate casing 300 between the two aircraft engine support structures 100. Furthermore, the C-ring 200 has a C-shaped structure with a notch at the lower end, thus eliminating the need for a column near the intermediate casing 300, thereby avoiding the problem of some components being unable to be assembled due to column obstruction.

[0042] Optionally, the aircraft engine support structure 100 can be fixedly connected to the C-ring 200 by welding the base 110 to it. It is understood that in other embodiments, other methods can be used to achieve the fixed connection between the aircraft engine support structure 100 and the C-ring, for example, by providing bolt holes at the upper and / or lower ends of the base plate 111 of the base 110, and fixing the base 110 to the C-ring 200 with bolts. The specific structure of the base plate 111 of the base 110 will be described later.

[0043] It should be noted that the C-ring 200 can be a component of the upper assembly system of an aero-engine. In some other embodiments, the base 110 can also be fixed to the engine assembly rack or other positions, providing basic technical support for the intelligent assembly of aero-engines.

[0044] The aircraft engine support structure 100 includes a transition shaft 130, a base 110, and a support seat 120. One end of the transition shaft 130 has a connecting portion 133 for connecting to the intermediate casing 300 of the aircraft engine, and the other end of the transition shaft 130 has a square shaft 131 with a square cross-section. The base 110 has a square groove 116, the cross-sectional shape of which matches the cross-sectional shape of the square shaft 131. The square shaft 131 is installed in the square groove 116, and the cross-sectional dimension of the square groove 116 is larger than that of the square shaft 131, so that the square shaft 131 and the square groove 116 have a clearance fit. One circumferential side of the square groove 116 is open to allow the square shaft 131 to enter and exit the square groove 116. The support seat 120 is movably connected to the base 110 to open or close the opening, such that when the opening is open (e.g.... Figure 5 As shown), the square shaft 131 can enter and exit the square slot 116 through the opening, and when the opening is closed (as shown in the diagram), the square shaft 131 can enter and exit the square slot 116. Figure 4 As shown, the square groove 116 is circumferentially closed, and the square shaft 131 is limited in the square groove 116. By setting the square shaft 131 on the adapter shaft 130 and cooperating with the square groove 116 through the square shaft 131, the precise positioning of the adapter shaft 130 on the base 110 can be guaranteed. At the same time, the square shaft 131 and the square groove 116 are in close clearance fit to ensure the attitude of the aircraft engine after support, which makes it easy to adjust the aircraft engine axis to be consistent with the vehicle axis and improve the docking and assembly quality.

[0045] The following is a further description of the aircraft engine support structure 100 provided in this embodiment:

[0046] Figure 7 This is a schematic diagram of the structure at the mating point between the base 110 and the square shaft 131 in the aircraft engine support structure 100 provided in this embodiment. Please refer to the diagram. Figures 3-7 In this embodiment, the base 110 includes a base plate 111, a first limiting part 114, and a second limiting part 115. One end of the first limiting part 114 is fixedly connected to the base plate 111, and the other end of the first limiting part 114 is fixedly connected to the second limiting part 115. The second limiting part 115 is spaced apart from the base plate 111, thereby defining a square groove 116 together with the base plate 111, the first limiting part 114, and the second limiting part 115. The opening of the square groove 116 is located on the side directly opposite to the first limiting part 114.

[0047] Specifically, one end of the first limiting part 114 is fixedly connected to the middle of the base plate 111, and the first limiting part 114 is arranged perpendicular to the base plate 111. Thus, the base plate 111 has a first plate part 112 located above the first limiting part 114 and a second plate part 113 located below the first limiting part 114. The upper end of the second limiting part 115 is fixedly connected to the end of the first limiting part 114 away from the base plate 111, and the second limiting part 115 and the second plate part 113 are arranged at intervals relative to each other. Thus, the square groove 116 is located between the second limiting part 115 and the second plate part 113, and the upper end of the square groove 116 is limited by the first limiting part 114. The lower end of the square groove 116 is open to form an opening. Thus, the base 110 forms a structure with a cross-section that is approximately h-shaped, and the square groove 116 formed is a structure that is open at both ends in the axial direction, closed on three sides in the circumferential direction, and open on one side. Setting the opening of the square slot 116 downwards makes it easier to observe the position of the square shaft 131, keeping the massive aircraft engine body stationary, and allowing for the smooth assembly of the aircraft engine by adjusting the position of this support structure.

[0048] It should be noted that, in the description of this embodiment, "circumferential direction of square groove 116" refers to the direction surrounding the axial direction of square groove 116, and "axial direction of square groove 116" refers to the direction along the length of square groove 116, i.e. Figure 4 The left and right directions are shown.

[0049] Optionally, the base plate 111, the first limiting part 114, and the second limiting part 115 may be integrally formed, or they may be welded structural components to ensure support strength.

[0050] Furthermore, the base 110 also includes a reinforcing rib, which is a rib-like structure with a triangular cross-section. One side of the rib is fixedly connected to the first plate portion 112, and the other side is fixedly connected to the upper side of the first limiting portion 114.

[0051] In this embodiment, the support base 120 and the base 110 are rotatably connected. The rotation of the support base 120 and the base 110 helps to ensure the stability of the position of the support base 120. When the support base 120 moves to close the opening, the fit clearance size between the square groove 116 and the square shaft 131 can be effectively guaranteed.

[0052] Optionally, the clearance dimension between the square groove 116 and the square shaft 131 is d, where 0.5mm ≤ d ≤ 1mm. Optionally, the clearance dimension d between the square groove 116 and the square shaft 131 can be, but is not limited to, 0.5mm, 0.8mm, or 1mm. It should be noted that the clearance dimension between the square groove 116 and the square shaft 131 refers to the dimension in a certain direction where the square groove 116 is larger than the square shaft 131. Figure 7The clearance dimension d shown refers to the dimension in which the square groove 116 is larger than the square shaft 131 in the vertical direction after the support 120 closes the opening.

[0053] Figure 8 This diagram illustrates the structure of the support base 120 in the aircraft engine support structure 100 provided in this embodiment. Please refer to the attached diagram. Figures 3-8 In this embodiment, the support base 120 includes a support plate 123, a first connecting arm 121, and a second connecting arm 124. The first connecting arm 121 and the second connecting arm 124 are fixedly connected to both ends of the support plate 123, and the first connecting arm 121 and the second connecting arm 124 extend in opposite directions. The first connecting portion 133 is connected to the second limiting portion 115, and the second connecting arm 124 is connected to the bottom plate 111 on the side of the square groove 116 away from the first limiting portion 114. When the support base 120 is closed, the support plate 123 is located at the opening, so that the bottom plate 111, the first limiting portion 114, the second limiting portion 115, and the support plate 123 form a circumferentially closed square groove 116.

[0054] Specifically, the support plate 123 is a plate-shaped component. A first connecting arm 121 is fixed to one end of the support plate 123 and extends upwards from it. A second connecting arm 124 is fixedly connected to the other end of the support plate 123 and extends downwards from it. Since the support base 120 is rotatably connected to the base 110, a pivot hole 122 is provided on the first connecting arm 121. A mounting groove 119 is provided at the lower end of the second limiting part 115. The first connecting arm 121 is rotatably installed in the mounting groove 119 and is rotatably connected to the second limiting part 115 via a pivot hole 122. Through the fixed connection between the second connecting arm 124 and the base plate 111, the support base 120 is locked onto the base 110. At this time, the support plate 123 is located at the opening of the square groove 116 and closes the opening.

[0055] Optionally, the base plate 111 is provided with a first bolt hole, and the second connecting arm 124 is provided with a second bolt hole 125. The aircraft engine support structure 100 also includes a connecting bolt 150, which is installed through the first bolt hole and the second bolt hole to lock the base plate 111 and the second connecting arm 124, thereby fastening the support seat 120 to the base 110.

[0056] Specifically, in this embodiment, the second bolt hole 125 is a slot that passes through the second connecting arm 124 at its lower end. It is understood that in some other embodiments, the second bolt hole 125 may also be configured as a waist-shaped hole or other structures.

[0057] Figure 9This diagram illustrates the structure of the side support end cap 140 in the aircraft engine support structure 100 provided in this embodiment. Please refer to the attached diagram. Figures 3-9 In this embodiment, the aircraft engine support structure 100 also includes a side support end cover 140, which is fixedly connected to the base 110 and is located at one axial end of the square shaft 131 to limit the position of the square shaft 131 in the axial direction of the square groove 116.

[0058] Specifically, a side support end cover 140 is fixedly installed at the tail end of the square groove 116. The side support end cover 140 is a square plate with an outer dimension larger than that of the square groove 116. The side support end cover plate fixedly installed on the base 110 can close the opening of the square groove 116 at this end, thereby playing a radial (radial) limiting role and bearing the radial support load of the aero-engine. It is convenient to roll and adjust during the assembly process, so that the difficult-to-operate positions directly below and above the aero-engine can be assembled and inspected.

[0059] Optionally, the side support cover is fixedly connected to the base 110 by high-strength bolts provided at the four corners. Furthermore, the base 110 is also provided with a groove 117 located on one side of the square slot 116, and the side support cover is installed by embedding it into the groove 117.

[0060] Figure 10 This is a schematic diagram of the adapter shaft 130 in the aircraft engine support structure 100 provided in this embodiment. Please refer to the diagram for further details. Figures 3-10 In this embodiment, the adapter shaft 130 further includes a tapered shaft segment 132 connecting the square shaft 131 and the connecting portion 133. The cross-sectional dimensions of the tapered shaft segment 132 decrease along the direction from the square shaft 131 to the connecting portion 133. By providing the tapered shaft segment 132, a certain space can be provided between the base 110 and the intermediate housing 300, thus avoiding the adapter shaft 130 from affecting the assembly of the aero-engine components.

[0061] The connecting part 133 includes a connecting flange 134 and a cylindrical mating section 135 located on the side of the connecting flange 134 away from the square shaft 131. The cylindrical mating section 135 is used to mate with the intermediate housing 300, and the connecting flange 134 is used to fixally connect with the intermediate housing 300.

[0062] The aero-engine support structure 100 and support device provided in the embodiments of the present invention achieve support for the aero-engine by setting a square shaft 131 on the adapter shaft 130 and using the square shaft 131 to cooperate with the square groove 116 on the base 110. Moreover, the square shaft 131 and the square groove 116 adopt a small clearance fit, ensuring the accuracy of the aero-engine support positioning, ensuring the attitude of the aero-engine after support, facilitating the alignment of the aero-engine axis with the vehicle axis, and improving the assembly quality of the entire large unit assembly. A side support end cap 140 is provided at one axial end of the square groove 116. The side support end cap 140, fixedly connected to the base 110, can act as a radial limit and bear the radial support load of the aero-engine. When the aero-engine is in the intelligent assembly rack or pulse line upper assembly system, it can be rolled and adjusted to facilitate assembly and inspection of positions that are difficult to operate directly below or above the engine. This aero-engine support structure 100 has a simple structure, is quick to install and disassemble, and allows the engine to be stably and accurately supported on the assembly rack or transport vehicle.

[0063] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. An aircraft engine support structure for supporting an aircraft engine during assembly; characterized in that, The aircraft engine support structure includes: The adapter shaft has a connecting part at one end for connecting to the intermediate casing of the aircraft engine, and a square shaft at the other end for connecting to the intermediate casing of the aircraft engine. A base having a square groove whose cross-sectional shape matches that of a square shaft; the square shaft is installed in the square groove, and the cross-sectional dimension of the square groove is larger than that of the square shaft, so that the square shaft and the square groove have a clearance fit; one circumferential side of the square groove is open to allow the square shaft to enter and exit the square groove; and A support base, which is movably connected to the base to open or close the opening.

2. The aircraft engine support structure according to claim 1, characterized in that, The base includes a base plate, a first limiting part and a second limiting part. One end of the first limiting part is fixedly connected to the base plate, and the other end of the first limiting part is fixedly connected to the second limiting part. The second limiting part is spaced apart from the base plate so that the base plate, the first limiting part and the second limiting part together define the square groove. The opening of the square groove is located on the side directly opposite to the first limiting part.

3. The aircraft engine support structure according to claim 2, characterized in that, The support base includes a support plate, a first connecting arm, and a second connecting arm. The first connecting arm and the second connecting arm are fixedly connected to both ends of the support plate, and the first connecting arm and the second connecting arm extend in opposite directions. The first connecting arm is connected to the second limiting part, and the second connecting arm is connected to the bottom plate on the side of the square groove away from the first limiting part. When the support base closes the opening, the support plate is located at the opening to form a circumferentially closed square groove through the base plate, the first limiting part, the second limiting part, and the support plate.

4. The aero-engine support structure according to claim 3, characterized in that, The base plate has a first bolt hole, and the second connecting arm has a second bolt hole. The aircraft engine support structure also includes a connecting bolt, which passes through the first bolt hole and the second bolt hole to lock the base plate and the second connecting arm together.

5. The aircraft engine support structure according to claim 1, characterized in that, The support base is rotatably connected to the base.

6. The aircraft engine support structure according to claim 1, characterized in that, The gap between the square groove and the square shaft is d, where 0.5mm ≤ d ≤ 1mm.

7. The aircraft engine support structure according to claim 1, characterized in that, The aircraft engine support structure also includes a side support end cap, which is fixedly connected to the base and located at one axial end of the square groove to limit the position of the square shaft in the axial direction of the square groove.

8. The aircraft engine support structure according to claim 1, characterized in that, The adapter shaft also includes a tapered shaft segment connecting the square shaft and the connecting part, and the cross-sectional dimensions of the tapered shaft segment decrease along the direction from the square shaft to the connecting part.

9. The aircraft engine support structure according to claim 1, characterized in that, The connecting part includes a connecting flange and a cylindrical mating section located on the side of the connecting flange away from the square shaft. The cylindrical mating section is used to mate with the intermediate housing, and the connecting flange is used to be fixedly connected to the intermediate housing.

10. An aircraft engine support device, characterized in that, The aero-engine support device includes a C-ring and an aero-engine support structure as described in any one of claims 1-9. Two aero-engine support structures are fixedly connected to both sides of the C-ring. The two aero-engine support structures are used to connect to the radial ends of the intermediate casing to support the intermediate casing. The C-ring is a C-shaped structure with a notch at the lower end.

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