Aero-engine transportation lifting lug integrated with supporting rod mounting seat

Abstract

The invention provides an aero-engine transportation lifting lug integrated with a supporting rod mounting seat, and belongs to the technical field of aero-engines, the transportation lifting lug comprises two lug pieces arranged in parallel, the two lug pieces form a split type transportation lifting lug, the lower sides of the lug pieces are fixedly connected with an engine case, and the lower sides of the lug pieces are fixedly connected with the supporting rod mounting seat. The upper sides of the lug pieces are connected through a first bolt assembly, a sleeve is installed on the first bolt assembly, and the sleeve is located between the two lug pieces. And one side of the supporting rod mounting seat is fixedly arranged on the upper sides of the two parallel lug pieces through a second bolt assembly, and the other side of the supporting rod mounting seat is used for mounting a supporting rod. According to the aero-engine transportation lifting lug integrated with the supporting rod mounting base, the supporting rod mounting structure and the lifting lug are integrated together, the lifting lug function is increased, the engine structure is simplified, a mounting structure can be provided for the engine outer cover supporting rod mounting base, meanwhile, mutual influence can be avoided, and the over-positioning problem of a lifting lug connecting structure is solved.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engines, and particularly relates to an aero-engine transportation lifting lug structure integrated with a support rod mounting seat. BACKGROUND

[0002] An aero-engine is provided with a transportation lifting lug structure, which is used for lifting the engine during engine installation, transportation, ground maintenance and other operations. The engine is generally provided with two lifting planes in front and back, wherein the front lifting plane is in a fan case, and there is one lifting lug on the left and right in the plane, which is arranged at a symmetrical position on the upper side of the case and mounted on the mounting edge or mounting seat of the outer wall of the case.

[0003] As shown in Figure 1 , the aero-engine is generally installed in the engine cabin of the aircraft fuselage or a separate engine lifting cabin 11, which is covered by an outer cover 12. When the engine is installed / dismounted or during maintenance, the outer cover 12 needs to be opened for operation. A common opening mode of the outer cover 12 is to open upward from the front and sides, and then use a support rod 13 to support it, so that the outer cover 12 remains in an open state. The mounting seat is usually two pieces in the circumferential direction and arranged at a position on the upper side of the case. According to the design scheme of the aircraft, one end of the support rod 13 is connected to the inner wall of the outer cover 12, and the other end is connected to the mounting seat 15 arranged on the engine case 14, so as to connect the support rod 13 and the engine case 14. When working, the outer cover 12 is opened, one end of the support rod 13 is connected to the mounting seat 15 through a quick-release pin 16, and the outer cover 12 is supported, and after the work is completed, one end of the support rod 13 is removed and fixed to the outer cover 12, as shown in Figure 2 and Figure 3 .

[0004] However, various types of accessories and related pipelines, cables, supports, clamps and other components are mounted on the outer wall of the engine case, and the number is large, the shape of the accessories and pipelines / cables is complex, and they cover a large proportion of the area of the outer wall of the case. In this case, the arrangement of the transportation lifting lug and the support rod mounting seat on the outer wall of the case has certain difficulty. In addition, the installation of the transportation lifting lug and the support rod mounting seat requires the design of related mounting edges / installing seats on the case, which makes the structure of the case more complex and increases the weight.

[0005] As shown in Figure 4 and Figure 5 , the engine transportation lifting lug and the outer cover support rod mounting seat 15 in the prior art are separate structures, which are respectively connected to the case, and separate connection structures need to be designed on the case. This scheme has the following disadvantages:

[0006] 1) Multiple connection structures need to be designed on the engine case, the structure is more complex, the processing difficulty is large, the cost is high, and the weight is large;

[0007] 2) The number of components and accessories installed on the outer wall of the engine case is large, and the space is tight. It is easy to interfere with other components when a separate connecting structure is designed for the support rod mounting seat 15.

[0008] Therefore, there is a need for a new transport lug structure to simplify the structure outside the engine case. SUMMARY

[0009] The purpose of the present application is to provide an integrated support rod mounting seat for an aero-engine transport lug to solve or alleviate at least one problem in the background art.

[0010] The technical solution of the present application is: an integrated support rod mounting seat for an aero-engine transport lug, comprising:

[0011] Two ear pieces arranged in parallel, two said ear pieces constitute a split transport lug, the lower side of the ear piece is fixedly connected with the engine case, the upper side of the ear piece is connected through a first bolt assembly, a sleeve is installed on the first bolt assembly, and the sleeve is located between the two ear pieces.

[0012] A support rod mounting seat is fixedly arranged on the upper side of the two ear pieces through a second bolt assembly, and the other side of the support rod mounting seat is used for mounting a support rod.

[0013] In at least one embodiment, the side edge of the ear piece connected with the engine case is arc-shaped, and a plurality of connecting holes are arranged near the arc-shaped edge.

[0014] In at least one embodiment, the upper side of the ear piece is provided with a first bolt hole for mounting the support rod mounting seat and a second bolt hole for mounting the first bolt assembly, wherein the diameter of the first bolt hole is smaller than the diameter of the second bolt hole.

[0015] In at least one embodiment, the positions of the connecting holes, the first bolt holes and the second bolt holes on the ear piece are thickened.

[0016] In at least one embodiment, both ends of the support rod mounting seat are double-ear structures, wherein the distance between the double-ear structure at one end of the support rod mounting seat connected with the support rod is smaller than the distance between the double-ear structure at the other end of the support rod mounting seat connected with the ear piece.

[0017] In at least one embodiment, the distance between the support rod mounting seat on the ear piece and the sleeve satisfies that the support rod mounting seat does not interfere with the lifting tool when lifting the engine, and the ear piece and the sleeve do not interfere with the support rod when the support rod is opened.

[0018] In at least one embodiment, the first bolt assembly is provided with a first bushing in the bolt hole of the lug on either side, and the length of the first bushing is greater than the thickness of the lug on the side;

[0019] The second bolt assembly is provided with a second bushing in the bolt hole of the lug on either side, and the length of the second bushing is greater than the thickness of the lug on the side.

[0020] In at least one embodiment, the lug, the strut mounting seat and the sleeve are made of metal material.

[0021] The integrated strut mounting seat transport lug of the aero-engine provided in the application cancels the connection structure of the outer cover strut mounting seat on the casing, increases the lug function by integrating the mounting structure of some components and the lug together, simplifies the engine structure, can provide the mounting structure for the engine outer cover strut mounting seat, and can avoid mutual influence in the integrated structure design of the strut mounting seat and the transport lug, and solves the over-positioning problem of the lug connection structure. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical solutions provided in the application, the following will briefly introduce the drawings. Obviously, the drawings described below are only some embodiments of the application.

[0023] Figure 1 The figure is a schematic diagram of the open state of the engine nacelle outer cover.

[0024] Figure 2 The figure is a schematic diagram of the connection structure of the outer cover strut and the engine casing.

[0025] Figure 3 The figure is a schematic diagram of the retracted state of the outer cover strut.

[0026] Figure 4 The figure is a schematic diagram of the existing engine transport lug.

[0027] Figure 5 The figure is a schematic diagram of the existing outer cover strut mounting seat.

[0028] Figure 6 The figure is a schematic diagram of the integrated strut mounting seat transport lug structure of the application.

[0029] Figure 7 The figure is a schematic diagram of the sleeve and lug connection structure in the application.

[0030] Figure 8 The figure is a schematic diagram of the strut mounting seat and lug connection structure in the application. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme in the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

[0032] The present application provides an aero-engine transportation lug with integrated support rod mounting seat, which can provide mounting seat for engine cover support rod and realize engine lifting function at the same time, and meanwhile reduces the connection structure of support rod mounting seat on the engine case.

[0033] As shown in the drawings, Figures 6 to 8 The aero-engine transportation lug with integrated support rod mounting seat 20 provided by the present application comprises lug plates 21, support rod mounting seats 22, sleeves 23, first bushings 241, second bushings 242, first bolt assemblies 251 and second bolt assemblies 252.

[0034] The lug plates 21 are two and symmetrical, and are arranged in parallel. The lower edge 211 of the lug plate 21 is arc-shaped, which is used for adapting to the engine case. A plurality of connection holes 212 are arranged near the lower edge of the lug plate 21 along the length direction thereof, and the lug plate 21 is fixedly connected with the mounting edge of the engine case through the connection holes 212 by a connecting member. The upper side of the lug plate 21 is provided with a first bolt hole for mounting the support rod mounting seat 22 and a second bolt hole for the first bolt assembly 251 to pass through, wherein the diameter of the first bolt hole is smaller than that of the second bolt hole.

[0035] In some embodiments of the present application, in order to improve the carrying capacity of the lug plate 21, the positions where the connection holes 212 and the first bolt hole and the second bolt hole are arranged are thickened, that is, the thickness of the positions where the connection holes 212 and the first bolt hole and the second bolt hole are arranged is greater than that of other positions of the lug plate 21.

[0036] The support rod mounting seat 22 is in a structure with double ears at both ends, and the double ear structure at the lower side thereof is arranged outside the two parallel lug plates 21. The support rod mounting seat 22 is connected with the lug plate 21 through four second bolt assemblies 252 (i.e. small bolt and nut assemblies), and the double ear structure at the upper side of the support rod mounting seat 22 is used for connecting with the support rod (not shown). In some embodiments of the present application, the distance between the double ear structures for connecting with the support rod in the support rod mounting seat 22 is smaller than the distance between the double ear structures on the other side of the support rod mounting seat 22, so that the support rod mounting seat 22 can provide more stable support.

[0037] The first bolt assembly 251 (i.e. large bolt and nut assembly) is arranged on the two lug plates 21 through the first bolt assembly 251 at a position away from the support rod mounting seat 22 on the upper side of the lug plate 21. The sleeve 23 is arranged on the first bolt assembly 251 between the two lug plates 21. During lifting, the lifting appliance contacts the sleeve 23 to avoid direct contact with the first bolt assembly 251 and generate abrasion. The engine with large weight is borne by the two lug plates 21 and the first bolt assembly 251.

[0038] In the preferred embodiment of the present application, the distance between the strut mounting seat 22 and the first bolt assembly 251 is determined according to the condition that the strut mounting seat 22 does not interfere with the lifting device when the engine is lifted and the tabs 21 and the sleeve 23 do not interfere with the strut when the strut is used to prop open the outer cover. Since the engine lifting and the strut propping open the outer cover do not occur simultaneously, the relative position or distance between the strut mounting seat 22 and the sleeve 23 is determined based on the actual conditions of the engine in the present application, i.e., the strut mounting seat 22 does not interfere with the lifting device when the engine is lifted and the tabs 21 and the sleeve 23 do not interfere with the strut when the strut is used to prop open the outer cover. For example, the distance between the strut mounting seat 22 and the first bolt assembly 251 can be set to be not less than the diameter of the strut and the width of the lifting device

[0039] In the present application, the strut mounting seat 22 is arranged at one end of the upper side of the tab 21 to limit the outward expansion of the tab 21, and the sleeve 23 is arranged at the other end of the upper side of the tab 21 to limit the inward closing of the tab 21, thereby forming a stable connection structure on the upper side of the tab 21.

[0040] In the present application, the tab 21 is designed in a split structure for weight reduction, and the two tabs 21 are connected to the engine casing, so their positions are limited. In this case, the connection between the first bolt assembly 251 and the two tabs 21 cannot be rigid, otherwise over-positioning and internal stress will occur. When the first bolt assembly 251 is connected to the two tabs 21, a first bushing 241 is arranged in the bolt hole of one tab 21, and the length of the first bushing 241 is greater than the thickness of the tab 21. When the first bolt assembly 251 is tightened, the bolt presses the sleeve 23 and the first bushing 241 against the other tab 23, and a gap is left between the first bushing 241 and the tab 23, so that the two tabs 23 will not be over-positioned by the engine casing and the first bolt assembly 251.

[0041] When the strut mounting seat 22 is mounted on the two tabs 21, the same structure is used, i.e., the mutual position of the strut mounting seat 22 and the tab 21 on one side is fixed, and a gap is left between the strut mounting seat 22 and the tab on the other side to avoid over-positioning.

[0042] In some embodiments of the present application, in order to improve the structural strength of the lifting lug, the tab 21, the strut mounting seat 22 and the sleeve 23 can be made of metal materials, such as titanium alloy.

[0043] The integrated support rod mounting seat of the aero-engine transport lug provided by the application cancels the connecting structure of the outer cover support rod mounting seat on the casing, increases the lug function by integrating the mounting structure of some components and the lug together, simplifies the engine structure, can provide the mounting structure for the engine outer cover support rod mounting seat, and can avoid mutual influence in the integrated structure design of the support rod mounting seat and the transport lug, and solves the over-positioning problem of the lug connecting structure. Compared with the existing structure, the application reduces the connecting structure on the engine casing, reduces the machining difficulty and cost of the casing, reduces the occupation of the external space of the casing, provides favorable conditions for the layout of the components, pipelines, cables and the like outside the casing, and reduces the design and manufacturing cost.

[0044] The above is only a specific embodiment of the application, but the protection scope of the application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the application, which should be covered within the protection scope of the application. Therefore, the protection scope of the application should be subject to the protection scope of the claims.

Claims

1. An aircraft engine transport lifting eye with an integrated strut mounting base, characterized in that: include: Two lugs (21) are arranged parallel to each other, and the two lugs (21) constitute a split transport lifting lug, the lower side of the lug (21) is fixedly connected to the engine casing, and the upper side of the lug is connected via a first bolt assembly (251), and a sleeve (23) is installed on the first bolt assembly (251), and the sleeve (23) is located between the two lugs (21); A support rod mounting seat (22) has one side fixedly arranged on the upper sides of two parallel lugs (21) through a second bolt assembly (252), and the other side of the support rod mounting seat (22) is used for mounting a support rod.

2. The aircraft engine transport lifting eye with integrated strut mount according to claim 1, characterized in that: A side edge (211) of the ear piece (21) connected to the engine casing is arc-shaped, and a plurality of connection holes (212) are arranged near the arc-shaped edge.

3. The aircraft engine transport lifting eye with integrated strut mount according to claim 2, characterized in that: The upper side of the ear piece (21) is provided with a first bolt hole for mounting a strut mounting seat (22) and a second bolt hole for mounting a first bolt assembly (251), wherein the diameter of the first bolt hole is smaller than the diameter of the second bolt hole.

4. The aircraft engine transport lifting eye with integrated strut mount according to claim 3, characterized in that: The locations where the connection hole (212), the first bolt hole, and the second bolt hole are arranged on the ear piece (21) are thickened.

5. The aircraft engine transport lifting eye with integrated strut mount according to claim 1, wherein: Both ends of the support rod mounting seat (22) are double-ear structures, wherein the distance between the double-ear structures at one end where the support rod mounting seat (22) is connected to the support rod is smaller than the distance between the double-ear structures at one end where the support rod mounting seat (22) is connected to the ear piece (21).

6. The aircraft engine transport lifting eye with integrated strut mount according to any one of claims 1 to 5, characterized in that: The spacing between the strut mounting seat (22) and the sleeve (23) on the ear piece (21) satisfies the requirement that the strut mounting seat (22) does not interfere with the sling when the engine is hoisted, and that the ear piece (21) and the sleeve (23) do not interfere with the strut when the strut opens the outer cover.

7. The aircraft engine transport lifting eye with integrated strut mount according to claim 6, characterized in that: A first bushing (241) is provided in the bolt hole of the first bolt assembly (251) and the ear piece (21) on either side, and the length of the first bushing (241) is greater than the thickness of the side ear piece (21); A second bushing (242) is provided in the bolt hole of the second bolt assembly (252) and the ear piece (21) on either side, and the length of the second bushing (242) is greater than the thickness of the side ear piece (21).

8. The aircraft engine transport lifting eye with integrated strut mount according to claim 1, wherein: The ear piece (21), the support rod mounting seat (22) and the sleeve (23) are made of metal material.

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