Hoop structure for connecting generator and engine of aircraft

Abstract

The utility model relates to the technical field of engine and generator installation, and provides a clamp structure for connecting an aircraft generator and an engine, which comprises an outer ring, a flange and an inner ring, the outer ring is a complete circular ring, and a locking bulge is arranged on one side of the outer ring; the flange is fixed to the generator and arranged in the outer ring, the locking protrusion is attached to the outer portion of the flange so that the flange can be locked in the outer ring, and a receding groove matched with the locking protrusion is formed in the outer portion of the flange; the inner ring is fixed to an engine and arranged in the outer ring, the inner ring abuts against the side, away from the locking protrusion, of the flange, and the outer ring can rotate relative to the flange and the inner ring. The clamp structure for connecting the aircraft generator and the engine adopts an integral structure, is mounted and fixed on the engine, can realize the mounting and dismounting of the generator without dismounting the clamp, and is smaller in mounting and dismounting space compared with a V-shaped clamp, thereby being more beneficial to the maintenance and assembly operation of the generator.

Description

Technical Field

[0001] The utility model relates to the technical field of engine and generator installation, in particular to a clamp structure for connecting an aircraft generator and an engine. Background Art

[0002] The connection between aircraft engines and generators is crucial in modern aircraft, especially in commercial and military aircraft. Their combination ensures that the aircraft's power supply meets various flight needs. The engine and generator are mechanically connected through drive shafts and gear boxes to transfer the power of the engine to the generator to generate the electricity required by the aircraft. For example, a flexible shaft-driven generator with a publication number of CN101783538A proposes a flexible shaft-driven generator that can effectively compensate for the unevenness of the engine speed and the eccentricity between the shafts, thereby improving the reliability of the entire unit system. The power conversion is achieved by connecting the flexible shaft to the engine output shaft.

[0003] In the actual installation process, the aircraft generator has a high speed and a large weight, and needs to be connected to the engine through a clamp or other structure to avoid relative displacement between the engine and the generator under vibration. The connection parts currently used in the market are all V-type clamps, which use two semicircular structures, one end of which is fixed by a pin. After the clamp is installed, the other end is fixed by a locking screw. The disadvantage of using this V-type clamp is that it needs to be installed and removed at the same time as the generator, and the installation space required is large, which is not convenient for maintenance and assembly. Utility Model Content

[0004] In view of this, the utility model proposes a clamp structure for connecting an aircraft generator to an engine. The structure adopts an integral structure and is fixedly mounted on the engine. The generator can be installed and removed without removing the clamp. Compared with a V-shaped clamp, the space required for installation and removal is smaller, which is more conducive to the maintenance and assembly of the generator.

[0005] The technical solution of the utility model is implemented as follows: The utility model provides a clamp structure for connecting an aircraft generator and an engine, comprising an outer ring, a flange and an inner ring, wherein:

[0006] The outer ring is a complete circular ring, and a locking protrusion is provided on one side of the outer ring;

[0007] The flange is fixed to the generator and arranged in the outer ring, the locking protrusion is fitted with the outer part of the flange so that the flange is locked in the outer ring, and the outer part of the flange is provided with a clearance groove matching the locking protrusion;

[0008] The inner ring is fixed to the engine and arranged in the outer ring. The inner ring abuts against the side of the flange away from the locking protrusion. The outer ring can rotate relative to the flange and the inner ring so that the clearance groove is aligned with the locking protrusion for the flange to detach from the outer ring.

[0009] On the basis of the above technical solution, preferably, the flange includes a protrusion, an annular inner groove is provided on the inner ring, the protrusion extends into the annular inner groove and abuts against the locking protrusion.

[0010] Further preferably, the number of the protrusions is the same as the number of the relief grooves, and they are spaced and distributed around the center of the flange.

[0011] On the basis of the above technical solution, preferably, it also includes a locking component, which is arranged on the outer ring and the inner ring, and is used to adjust the relative rotation angle between the outer ring and the inner ring.

[0012] Further preferably, the locking assembly includes two connecting parts and an adjusting member, wherein:

[0013] The two connecting parts are respectively arranged on the outer circumference of the inner ring and the outer ring, and extend to a side of the outer circumference away from the center of the circle;

[0014] The adjusting piece is threadedly connected to the two connecting parts.

[0015] More preferably, the connecting portion includes a fixed block and a movable member, wherein:

[0016] The fixing block is fixed to one of the inner ring and the outer ring;

[0017] The movable part is rotatably arranged on the fixed block, and the adjusting part is threadably connected to the movable part.

[0018] More preferably, the adjustment member includes a first connecting section and a second connecting section, both of which are cylindrical, and the first connecting section and the second connecting section are provided with threads with opposite spiral directions, and the first connecting section and the second connecting section are respectively threadedly connected to the two connecting parts.

[0019] On the basis of the above technical solution, preferably, the inner diameter of the outer ring matches the outer diameter of the inner ring, and the outer ring is threadedly connected to the inner ring.

[0020] On the basis of the above technical solution, preferably, a mounting hole is opened on the inner ring, and the inner ring is fixed to the engine through the mounting hole.

[0021] The clamp structure for connecting the aircraft generator and the engine of the utility model has the following beneficial effects compared with the prior art:

[0022] (1) By providing the outer ring, the inner ring and the flange, if the generator needs to be disassembled for inspection or maintenance, it is only necessary to rotate the outer ring so that the clearance groove is aligned with the locking protrusion to disconnect the connection between the engine and the generator, and then remove the generator for operation. During this operation, the outer ring, the inner ring and the flange do not need to be removed from the generator and the engine, thereby making it more convenient to perform maintenance and inspection of the generator. Compared with the V-type clamp, the space required for installation and removal is smaller;

[0023] (2) A locking assembly is provided to hinder the relative rotation of the outer ring and the inner ring, and the outer ring can be pushed to rotate relative to the inner ring and the flange through the locking assembly, so as to unlock the flange or lock the flange. Moreover, the setting of the locking assembly only requires the operator to operate the locking assembly to complete the connection between the inner ring and the flange, thereby further improving the convenience of the relative fixation of the inner ring and the flange. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0025] Figure 1 A three-dimensional diagram of a clamp structure for connecting an aircraft generator and an engine according to the utility model;

[0026] Figure 2 A three-dimensional view from another perspective of the clamp structure for connecting the aircraft generator and the engine of the utility model;

[0027] Figure 3 It is a side view of the clamp structure for connecting the aircraft generator and the engine of the utility model;

[0028] Figure 4 for Figure 3 Structural cross-section view at AA in the middle;

[0029] Figure 5 A three-dimensional diagram of a clamp structure flange for connecting an aircraft generator and an engine according to the utility model;

[0030] Figure 6 The utility model is a three-dimensional diagram of a clamp structure adjustment member for connecting an aircraft generator and an engine. DETAILED DESCRIPTION

[0031] The following will be combined with the implementation of the utility model to clearly and completely describe the technical solutions in the implementation of the utility model. Obviously, the described implementation is only a part of the implementation of the utility model, not all of the implementations. Based on the implementation of the utility model, all other implementations obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0032] like Figure 1-6 As shown, the clamp structure for connecting the aircraft generator and the engine of the utility model comprises an outer ring 1, a flange 2 and an inner ring 3.

[0033] The outer ring 1 is a complete circular ring, and a locking protrusion 11 is arranged on one side of the outer ring 1. For the convenience of explanation, the two sides on the axis of the outer ring 1 are respectively used as the insertion side and the connection side. The locking protrusion 11 is arranged on the insertion side of the outer ring 1, and the number of the locking protrusions 11 is multiple. The locking protrusions 11 are specifically arranged on the inner wall of the outer ring 1 and are distributed at equal angles around the center of the outer ring 1.

[0034] The flange 2 is fixed to the generator and arranged in the outer ring 1. The locking protrusion 11 fits with the outside of the flange 2 to lock the flange 2 in the outer ring 1. The outside of the flange 2 is provided with a clearance groove 201 matching the locking protrusion 11. In this embodiment, the clearance groove 201 on the flange 2 is staggered with the locking protrusion 11 to avoid the flange 2 being unable to be relatively fixed after the locking protrusion 11 is aligned with the clearance groove 201. The outer diameter of the flange 2 matches the inner diameter of the outer ring 1 to improve the mechanical fit during locking and improve the connection strength.

[0035] The inner ring 3 is fixed to the engine and arranged in the outer ring 1. The inner ring 3 abuts against the side of the flange 2 away from the locking protrusion 11. The outer ring 1 can rotate relative to the flange 2 and the inner ring 3 so that the clearance groove 201 is aligned with the locking protrusion 11 to allow the flange 2 to detach from the outer ring 1.

[0036] In this solution, the flange 2 is directly mounted on the generator, while the inner ring 3 is fixed to the engine, and the outer ring 1 is arranged in advance on the outside of the inner ring 3, specifically on the connection side of the outer ring 1. When connecting, the clearance groove 201 on the flange 2 is aligned with the locking protrusion 11, and the flange 2 is inserted into the outer ring 1 through the insertion side of the outer ring 1. The inner ring 3 supports the side of the flange 2 inserted into the outer ring 1. By rotating the outer ring 1, the clearance groove 201 and the locking protrusion 11 are offset, thereby completing the relative fixation of the flange 2 and the inner ring 3, and then connecting the aircraft engine to the generator.

[0037] Accordingly, if the generator needs to be disassembled for inspection or maintenance, it is only necessary to rotate the outer ring 1 so that the clearance groove 201 is aligned with the locking protrusion 11, and the connection between the engine and the generator can be disconnected, and then the generator can be removed for operation. During this operation, the outer ring 1, the inner ring 3 and the flange 2 do not need to be removed from the generator and the engine, thereby making it more convenient to perform maintenance and inspection of the generator.

[0038] In this embodiment, the flange 2 includes a protrusion 21 , and an annular inner groove is provided on the inner ring 3 . The protrusion 21 extends into the annular inner groove and abuts against the locking protrusion 11 .

[0039] After the protrusion 21 is inserted between the locking protrusion 11 and the inner ring 3, it will be locked between the two components. Specifically, a clearance groove 201 is formed between two adjacent protrusions 21, and the cross-section of the locking protrusion 11 along the radial direction of the flange 2 is stepped. The end of the stepped part is inserted into the annular inner groove, and the other stepped part contacts the locking protrusion 11 and cooperates with it.

[0040] In addition, the number of the protrusions 21 is the same as the number of the clearance grooves 201, and they are arranged at intervals around the center of the flange 2, so that the flange 2 can be inserted into the outer ring 1 at multiple relative positions, and by rotating the arc corresponding to a locking protrusion 11, multiple protrusions 21 can be matched with the corresponding number of locking protrusions 11 to achieve the locking of the flange 2 and make it have better stability.

[0041] As a preferred embodiment, a locking assembly 4 is further provided. The locking assembly 4 is provided on the outer ring 1 and the inner ring 3 . The locking assembly 4 is used to adjust the relative rotation angle between the outer ring 1 and the inner ring 3 .

[0042] The locking assembly 4 is provided to hinder the relative rotation of the outer ring 1 and the inner ring 3, and the outer ring 1 can be pushed to rotate relative to the inner ring 3 and the flange 2 through the locking assembly 4, so as to release the lock on the flange 2 or lock the flange 2. Specifically, an operating end is provided on the locking assembly 4, and the locking or unlocking is performed by reversing the operating end, which is more convenient for the operator to perform installation or disconnection operations.

[0043] Specifically, the locking assembly 4 includes two connecting parts 41 and an adjusting piece 42 . The two connecting parts 41 are respectively arranged on the outer circumference of the inner ring 3 and the outer ring 1 , and extend to a side of the outer circumference away from the center of the circle. The adjusting piece 42 is threadedly connected to the two connecting parts 41 .

[0044] The operating end of the locking assembly 4 is arranged on the adjusting member 42. By rotating the adjusting member 42, the two connecting parts 41 on the inner ring 3 and the outer ring 1 can be moved away from or close to each other through the thread. In actual operation, since the inner ring 3 is fixed on the engine, that is, the inner ring 3 always remains fixed, under the relative action, the outer ring 1 rotates to achieve or release the locking of the flange 2, and the relative activity angle of the two connecting parts 41 should not be greater than the angle corresponding to the single locking protrusion 11.

[0045] In addition, the connecting portion 41 includes a fixed block 411 and a movable member 412 . The fixed block 411 is fixed to one of the inner ring 3 and the outer ring 1 . The movable member 412 is rotatably disposed on the fixed block 411 . The adjusting member 42 is threadedly connected to the movable member 412 .

[0046] The movable member 412 is a rotatable shaft, which is disposed on the fixed block 411 to cooperate with the angle deviation of the adjusting member 42 when the two fixed blocks 411 move away from or close to each other, thereby avoiding angle blocking that causes the two fixed blocks 411 to be unable to move relative to each other.

[0047] Specifically, the adjustment member 42 includes a first connecting section 421 and a second connecting section 422, both of which are cylindrical, and the first connecting section 421 and the second connecting section 422 are provided with threads with opposite spiral directions, and the first connecting section 421 and the second connecting section 422 are respectively threadedly connected to the two connecting parts 41.

[0048] A bracket is also fixed on the inner ring 3, and the bracket is fixed to a fixed block 411 arranged on the inner ring 3, while another fixed block 411 is directly fixed on the outer ring 1. The segmented setting of the adjustment member 42 can directly pass through the first fixed block 411 and be inserted into the other fixed block 411 to realize the synchronous connection of the two fixed blocks 411, and the segmented reverse thread setting of the first connecting segment 421 and the second connecting segment 422 can maximize the relative displacement of the two fixed blocks 411 during the twisting process of the adjustment member 42, that is, the relative rotation amplitude of the outer ring 1 is larger under a smaller rotation amount.

[0049] As a preferred embodiment, the inner diameter of the outer ring 1 matches the outer diameter of the inner ring 3 , and the outer ring 1 is threadedly connected to the inner ring 3 .

[0050] The threaded connection between the outer ring 1 and the inner ring 3 can make the connection between the two components more stable and reliable, and can be rotated relative to each other through the thread. In addition, considering that when the two components rotate relative to each other, an axial relative displacement will be generated under the action of the thread, the adjustment member 42 can be set to be at an angle to its axial direction to match the displacement and reduce mechanical hard friction. It should be noted that if the adjustment member 42 is directly set to be perpendicular to the axial direction of the outer ring 1, it can also be directly rotated under a smaller relative rotation between the outer ring 1 and the inner ring 3.

[0051] Finally, mounting holes are provided on the inner ring 3, and the inner ring 3 is fixed to the engine through the mounting holes. The mounting holes are arranged at equal angles on the inner ring 3, and the flange 2 is also provided with fixing holes for connecting the generator. The fixing holes are respectively arranged on multiple protrusions 21, and each protrusion 21 is provided with two fixing holes.

[0052] In this embodiment, the number of the bumps 21 is set to six.

[0053] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A clamp structure for connecting an aircraft generator to an engine, characterized in that: It comprises an outer ring (1), a flange (2) and an inner ring (3), wherein: The outer ring (1) is a complete circular ring, and a locking protrusion (11) is provided on one side of the outer ring (1); The flange (2) is fixed to the generator and arranged in the outer ring (1); the locking protrusion (11) is fitted with the outside of the flange (2) so that the flange (2) is locked in the outer ring (1); and the outside of the flange (2) is provided with a clearance groove (201) matching the locking protrusion (11); The inner ring (3) is fixed to the engine and arranged inside the outer ring (1). The inner ring (3) abuts against a side of the flange (2) away from the locking protrusion (11). The outer ring (1) can rotate relative to the flange (2) and the inner ring (3) so that the clearance groove (201) is aligned with the locking protrusion (11) to allow the flange (2) to be separated from the outer ring (1).

2. The clamp structure for connecting an aircraft generator to an engine as claimed in claim 1, characterized in that: The flange (2) comprises a protrusion (21), and the inner ring (3) is provided with an annular inner groove. The protrusion (21) extends into the annular inner groove and abuts against the locking protrusion (11).

3. The clamp structure for connecting an aircraft generator to an engine as claimed in claim 2, characterized in that: The number of the protrusions (21) is the same as the number of the clearance grooves (201), and they are arranged in a spaced manner around the center of the flange (2).

4. The clamp structure for connecting an aircraft generator to an engine as claimed in claim 1, characterized in that: It also comprises a locking assembly (4), which is arranged on the outer ring (1) and the inner ring (3), and is used to adjust the relative rotation angle between the outer ring (1) and the inner ring (3).

5. The clamp structure for connecting an aircraft generator to an engine as claimed in claim 4, characterized in that: The locking assembly (4) comprises two connecting parts (41) and an adjusting member (42), wherein: The two connecting portions (41) are respectively arranged on the outer circumference of the inner ring (3) and the outer ring (1), and extend to a side of the outer circumference away from the center of the circle; The adjusting member (42) is threadedly connected to the two connecting parts (41).

6. The clamp structure for connecting an aircraft generator to an engine as claimed in claim 5, characterized in that: The connecting portion (41) comprises a fixed block (411) and a movable member (412), wherein: The fixing block (411) is fixed to one of the inner ring (3) and the outer ring (1); The movable member (412) is rotatably arranged on the fixed block (411), and the adjusting member (42) is threadedly connected to the movable member (412).

7. The clamp structure for connecting an aircraft generator to an engine as claimed in claim 5, characterized in that: The adjusting member (42) comprises a first connecting section (421) and a second connecting section (422); the first connecting section (421) and the second connecting section (422) are both cylindrical, and the first connecting section (421) and the second connecting section (422) are provided with threads with opposite spiral directions; the first connecting section (421) and the second connecting section (422) are respectively threadedly connected to the two connecting parts (41).

8. The clamp structure for connecting an aircraft generator to an engine as claimed in claim 1, characterized in that: The inner diameter of the outer ring (1) matches the outer diameter of the inner ring (3), and the outer ring (1) and the inner ring (3) are threadedly connected.

9. The clamp structure for connecting an aircraft generator to an engine as claimed in claim 1, characterized in that: The inner ring (3) is provided with a mounting hole, and the inner ring (3) is fixed to the engine through the mounting hole.

Images