Mounting structure and assembling method for speed reducer and engine of helicopter

Abstract

The invention belongs to the technical field of engines, and particularly relates to a mounting structure and an assembling method of a helicopter speed reducer and an engine. Comprising an engine front shaft sleeve and a speed reducer casing, the speed reducer casing is connected with a spherical supporting sleeve; a spherical cover is arranged between one end of the inner wall of the spherical supporting sleeve and the spherical supporting body; the spherical cover is connected with the spherical support body; the spherical supporting body, the spherical cover and the spherical supporting sleeve are matched through a spherical surface sharing the same sphere center to form a rotatable connecting structure; connection of the main speed reducer and the engine and compensation requirements of angular positions of a speed reducer casing and a front shaft sleeve of the engine are met through spherical fit.

Description

Technical Field

[0001] The present invention belongs to the technical field of engines, and particularly relates to an installation structure and an assembly method for a helicopter reducer and an engine. Background Art

[0002] The existing connection structures between the main reducer of the helicopter transmission system and the engine in China mainly include a universal joint ring and an elastic front bushing. The universal joint ring has poor structural compactness and large external dimensions, and is not suitable for the situation where space is severely restricted on a helicopter; the elastic front bushing is structurally compact, but its load-bearing capacity is weak, and it is not suitable for connecting the main reducer and the engine of a large-power and large-tonnage helicopter.

[0003] Therefore, there is an urgent need for a new connection structure between the main reducer and the engine, which has the characteristics of structural compactness and strong load-bearing capacity, and can not only meet the strict requirements of space limitation on a helicopter, but also meet the structural strength requirements of a large-power engine under large impact loads. Summary of the Invention

[0004] In view of the above problems, the present invention provides an installation structure for a helicopter reducer and an engine, including an engine front bushing and a reducer casing. A spherical support is rigidly connected to the engine front bushing; a spherical support sleeve is rigidly connected to the reducer casing; a spherical cover is arranged between one end of the inner wall of the spherical support sleeve and the spherical support; the spherical cover is connected to the spherical support;

[0005] The spherical support, the spherical cover and the spherical support sleeve form a rotatable connection structure through spherical mating with a common center of the sphere.

[0006] Further, the cross-section of the inner wall of the spherical support sleeve is stepped, and the step includes a first step and a second step; the first step cooperates with the spherical cover, and the second step cooperates with the spherical cover and the spherical support.

[0007] Further, a lubrication cavity is arranged on the spherical support at the junction with the spherical cover and the spherical support sleeve.

[0008] Further, a sealing groove is formed on the spherical support at the position where it mates with the spherical cover and the spherical support sleeve, and a sealing member is installed in the sealing groove.

[0009] Further, the sum of the distance from the spherical boundary of the spherical cover to the center of the sphere and the distance from the spherical boundary of the spherical support sleeve to the center of the sphere is less than half of the spherical radius of the spherical support.

[0010] Further, the sum of the distance from the spherical boundary of the spherical cover to the center of the sphere and the distance from the spherical boundary of the spherical support sleeve to the center of the sphere is greater than one-third of the spherical radius of the spherical support.

[0011] Further, the center of the mating spherical surfaces of the spherical support, the spherical cover, and the spherical support sleeve lies on the center line of the power shaft.

[0012] Further, the power shaft passes through the front engine bushing, the spherical support, the spherical cover, the spherical support sleeve, and the reducer housing, and the power shaft is fixedly connected to the spherical support.

[0013] The present invention provides an assembly method for an installation structure of a helicopter reducer and an engine, characterized in that the method is applicable to the installation structure of a helicopter reducer and an engine described in any one of the claims, and the method comprises the following steps:

[0014] Assemble the spherical support and the spherical support sleeve;

[0015] Assemble the spherical cover between the spherical support and the spherical support sleeve, and fixedly connect the outer sides of the spherical cover and the spherical support sleeve through a flange.

[0016] Further, before assembling the spherical support and the spherical support sleeve,

[0017] Install a seal in the seal groove to improve the overall sealing effect;

[0018] Fill the lubrication cavity with grease to lubricate the positions of the spherical support sleeve, the spherical cover, and the spherical support.

[0019] Advantageous Effects

[0020] The beneficial effects of the present invention compared with the prior art are as follows:

[0021] 1. In this application, the installation joint structure composed of the spherical support, the spherical support sleeve, and the spherical cover realizes the connection between the main reducer and the engine through spherical mating, and meets the compensation requirement for the angular position of the reducer housing and the front engine bushing.

[0022] 2. In this application, through the mutual cooperation of the assembly positions of the spherical support, the spherical support sleeve, and the spherical cover, combined with the lubrication cavity, an installation connection structure with an angular compensation function that is easy to assemble, has a compact structure, and a strong load-bearing capacity is formed.

[0023] 3. In this application, by limiting the distance from the spherical surface boundary of the spherical cover to the center of the sphere and the distance from the spherical surface boundary of the spherical support sleeve to the center of the sphere, it is ensured that the installation structure forms a fitting and slidable spherical structure, and the load-bearing capacity of the spherical support is ensured.

[0024] Other features and advantages of the present invention will be described in the following specification, and, in part, will be obvious from the specification, or will be understood by implementing the present invention. The objectives and other advantages of the present invention can be realized and obtained through the structures pointed out in the specification, the claims, and the drawings. Brief Description of the Drawings

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0026] Figure 1 Shows a schematic installation diagram of an engine, a main reducer, and a rotor on a helicopter platform in the prior art.

[0027] Figure 2 Shows a schematic structural diagram of a universal joint ring in the prior art.

[0028] Figure 3 Shows a schematic structural diagram of an elastic front axle sleeve in the prior art.

[0029] Figure 4 Shows a sectional view of the whole in the embodiment of the present invention.

[0030] Figure 5 Shows Figure 4 A partial enlarged view at position B in

[0031] Figure 6 Shows a sectional view of a spherical support body, a spherical support sleeve, and a spherical cover in the embodiment of the present invention.

[0032] In the figure, 1, front axle sleeve of the engine; 2, spherical support body; 3, spherical cover;

[0033] 4, spherical support sleeve; 41, first step; 42, second step;

[0034] 5, reducer housing; 6, sealing groove; 7, lubrication cavity; 8, seal; 9, power shaft. Detailed Description of the Embodiments

[0035] In order to make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the 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 fall within the scope of protection of the present invention.

[0036] The engine, main reducer, and rotor system are the three major moving components of a helicopter. Among them, the engine provides power, the main reducer is responsible for transmitting the power of the engine to the main rotor, driving the rotor to work and ultimately providing lift for the helicopter. The installation of the engine, main reducer, and rotor on the helicopter is shown in Figure 1 the figure; where a is the main rotor, b is the main rotor shaft, c is the main accelerator, d is the engine mounting joint of the main reducer, e is the engine, and f is the helicopter platform;

[0037] As Figure 1 shown, the connection structure between the engine and the main reducer is called the engine mounting joint of the main reducer, which is used to support the engine on the main reducer. There are mainly two types of existing engine mounting joints of the main reducer in China: the universal joint ring and the elastic front shaft sleeve.

[0038] The structure of the universal joint ring is as Figure 2 shown, where g is the main reducer side, h is the universal joint ring, and j is the engine side; the universal joint ring is evenly distributed with 4 bolt connection holes along the circumference. The 4 connection holes are divided into 2 groups and are respectively connected to the main reducer side structure (referred to as the front shaft sleeve) and the engine side structure (referred to as the rear shaft sleeve) to form the angular compensation function in the axial direction of the engine.

[0039] The structure of the elastic front shaft sleeve is shown in Figure 3 the figure; where k is the rubber layer, l is the engine side, m is the elastic front shaft sleeve, and n is the main reducer side; the elastic front shaft sleeve is mainly composed of the flange on the main reducer side, the flange on the engine side, the rubber layer, and the connecting piece. By adding a rubber layer between the two flanges, the two flanges can generate a certain angular compensation ability along the axial direction of the engine.

[0040] This application provides an installation structure for a helicopter reducer and an engine. Referring to Figure 4 , it includes an engine front shaft sleeve 1 and a reducer casing 5. A spherical support 2 is connected to the engine front shaft sleeve 1; a spherical support sleeve 4 is connected to the reducer casing 5; a spherical cover 3 is arranged between one end of the inner wall of the spherical support sleeve 4 and the spherical support 2; the spherical cover 3 is connected to the spherical support 2;

[0041] The spherical support 2, the spherical cover 3, and the spherical support sleeve 4 form a rotatable connection structure through the spherical surface fit of the spherical support 2 with a common center of the sphere.

[0042] During the implementation process, the engine front axle sleeve 1 and the reducer housing 5 are connected through the spherical support 2 and the spherical support sleeve 4. The spherical support 2 and the spherical support sleeve 4 are assembled, and then the spherical cover 3 is assembled between the spherical support 2 and the spherical support sleeve 4. The spherical cover 3 presses the internal spherical support 2, and the spherical cover 3 positions the spherical support 2. Then, the spherical cover 3 and the spherical support sleeve 4 are locked through a flange or bolts to achieve the overall assembly. When disassembly is required, first disassemble the spherical cover 3, and then sequentially disassemble the spherical support 2 and the spherical support sleeve 4.

[0043] The spherical support 2 is rigidly connected to the engine front axle sleeve 1, and the spherical support sleeve 4 is rigidly connected to the reducer housing 5. The rigid connection body between the spherical support 2 and the engine front axle sleeve 1 and the rigid connection body between the spherical support sleeve 4 and the reducer housing 5 can rotate 360° around the sphere as the center, realizing the angular compensation requirement during the assembly process between the engine and the main reducer.

[0044] In this application, the mounting joint structure composed of the spherical support 2, the spherical support sleeve 4, and the spherical cover 3 realizes the connection between the main reducer and the engine through spherical mating, and meets the angular position compensation requirements of the reducer housing 5 and the engine front axle sleeve 1.

[0045] In an embodiment of the present invention, the inner wall cross-section of the spherical support sleeve 4 is stepped, and the step includes a first step 41 and a second step 42. The first step 41 cooperates with the spherical cover 3, and the second step 42 cooperates with the spherical cover 3 and the spherical support 2.

[0046] Reference Figure 5 , the first step 41 is the vertical and horizontal surfaces on the left. The vertical surface of the first step 41 fits against the opposite surface of the spherical cover 3, and a part of the horizontal surface of the first step 41 fits against the outer surface of the convex part of the spherical cover 3. The part of the horizontal surface of the first step 41 opposite to the lubrication cavity 7 and the vertical surface of the second step 42 form the whole of the lubrication cavity 7. The horizontal surface of the second step 42 fits against the spherical support 2. Through the mutual cooperation of the positions of the three, an installation connection structure with an angular compensation function that is easy to assemble, has a compact structure, and strong load-bearing capacity is formed.

[0047] In an embodiment of the present invention, a lubrication cavity 7 is provided on the spherical support 2 at the junction with the spherical cover 3 and the spherical support sleeve 4.

[0048] In an embodiment of the present invention, a sealing groove 6 is provided on the spherical support 2 at the position where it cooperates with the spherical cover 3 and the spherical support sleeve 4, and a seal 8 is installed in the sealing groove 6.

[0049] Reference Figure 5, the lubrication chamber 7 actually consists of two parts as a whole. One part of the lubrication chamber 7 is opened on the spherical support 2 for pre-filling grease. After the spherical support 2, the spherical support sleeve 4, and the spherical cover 3 are assembled in sequence, the vertical end of the second step 42, the horizontal end of the first step 41, and the protruding side wall part of the spherical cover 3 sandwiched between the spherical support 2 and the spherical support cover form another lubrication position, which is connected to the lubrication chamber 7. The grease installed in the lubrication chamber 7 can lubricate among these three components. Multiple lubrication chambers 7 can be evenly distributed circumferentially along the spherical surface of the spherical support 2 to further improve the lubrication effect.

[0050] Figure 5 The position of T in it is a groove body opened on the spherical support sleeve 4. On the one hand, it provides a moving space for the spherical support to avoid interference and collision during the rotation of the spherical support. On the other hand, when machining is required for the spherical support, it is convenient for the machining tool to withdraw, which is equivalent to a tool withdrawal groove.

[0051] Two sets of seals 8 are provided and distributed at both ends of the lubrication chamber 7. The seal 8 is a rubber sealing ring, which seals the whole. While ensuring the lubrication effect of the grease, it avoids the leakage of the grease along the spherical surface.

[0052] In an embodiment of the present invention, the sum of the distance from the spherical surface boundary of the spherical cover 3 to the center of the sphere and the distance from the spherical surface boundary of the spherical support sleeve 4 to the center of the sphere is less than half of the spherical radius.

[0053] In an embodiment of the present invention, the sum of the distance from the spherical surface boundary of the spherical cover 3 to the center of the sphere and the distance from the spherical surface boundary of the spherical support sleeve 4 to the center of the sphere is greater than one-third of the spherical radius.

[0054] During the implementation process, referring to Figure 6 , the spherical support 2, the spherical cover 3, and the spherical support sleeve 4 share the same center of the sphere, the center of the sphere is O, the spherical radius is R, P is the central axis, and the center of the sphere is located on the central axis. The distance from the spherical surface boundary of the spherical cover 3 to the center of the sphere is represented by B, and the distance from the spherical surface boundary of the spherical support sleeve 4 to the center of the sphere is represented by A. In order to better ensure the axial bearing capacity of the spherical support, A and B need to meet the following conditions;

[0055] 1) A > 0, B > 0;

[0056] 2) R / 3 < A + B < R / 2;

[0057] 3)

[0058] When A = 42 mm, B = 41.98 mm, and R = 194 mm;

[0059] A + B = 83.98 mm, R / 3 ≈ 64.7 mm, R / 2 = 97 mm; |A - B| = 0.02

[0060] 64.7 < 83.98 < 97;

[0061] When A = 52 mm, B = 31 mm, and R = 185 mm;

[0062] A + B = 83 mm, R / 3 ≈ 61.7 mm, R / 2 = 92.5 mm; |A - B| = 21

[0063] 61.7 < 83 < 92.5;

[0064] In an embodiment of the present invention, the center of the mating spherical surfaces of the spherical support 2, the spherical cover 3, and the spherical support sleeve 4 is located on the center line of the power shaft 9.

[0065] In an embodiment of the present invention, the power shaft 9 passes through the front engine bushing 1, the spherical support 2, the spherical cover 3, the spherical support sleeve 4, and the reducer housing 5, and the power shaft 9 is fixedly connected to the spherical support 2.

[0066] During implementation, during operation, the power shaft 9 drives the spherical support 2 to rotate; the spherical support 2, the spherical cover 3, and the spherical support sleeve 4 are used to compensate for angular deviations during installation or operation, without affecting the synchronism of power transmission.

[0067] The present application provides an assembly method for an installation structure of a helicopter reducer and an engine. This method is applicable to the above-mentioned installation structure of a helicopter reducer and an engine, and this method includes the following steps:

[0068] Assemble the spherical support 2 and the spherical support sleeve 4;

[0069] Assemble the spherical cover 3 between the spherical support 2 and the spherical support sleeve 4, and fixedly connect the outer sides of the spherical cover 3 and the spherical support sleeve 4.

[0070] In an embodiment of the present invention, before assembling the spherical support and the spherical support sleeve 4,

[0071] Install the seal 8 in the seal groove 6;

[0072] Fill the lubrication cavity 7 with grease.

[0073] During implementation, the seal 8 is an O-ring seal, which forms a sealing function through the seal ring to prevent the lubricating grease from leaking along the spherical surface. By filling the lubricating cavity 7 with lubricating grease, which is a thick, grease-like semi-solid, the lubrication requirements during the relative movement of the spherical surfaces of the spherical support 2, the spherical cover 3, and the spherical support sleeve 4 are met, avoiding spherical surface wear.

[0074] 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. A helicopter reducer and engine mounting structure, characterized in that: The invention comprises an engine front shaft sleeve (1) and a reducer casing (5), wherein the engine front shaft sleeve (1) is connected to a spherical support body (2); the reducer casing (5) is connected to a spherical support sleeve (4); a spherical cover (3) is arranged between one end of the inner wall of the spherical support sleeve (4) and the spherical support body (2); and the spherical cover (3) is connected to the spherical support body (2); The spherical support body (2), the spherical cover (3) and the spherical support sleeve (4) form a rotatable connection structure through spherical matching with a common spherical center.

2. The installation structure of a helicopter reducer and an engine according to claim 1, characterized in that: The inner wall cross section of the spherical support sleeve (4) is stepped, and the stepped shape includes a first step (41) and a second step (42); the first step (41) matches the spherical cover (3), and the second step (42) matches the spherical cover (3) and the spherical support body (2).

3. The installation structure of a helicopter reducer and an engine according to claim 1, characterized in that: The spherical support body (2) is provided with a lubrication cavity (7) at the junction with the spherical cover (3) and the spherical support sleeve (4).

4. The installation structure of a helicopter reducer and engine according to claim 1, characterized in that: The spherical support body (2) is provided with a sealing groove (6) at a position matching with the spherical cover (3) and the spherical support sleeve (4), and a sealing member (8) is installed in the sealing groove (6).

5. The installation structure of a helicopter reducer and an engine according to claim 1, characterized in that: The sum of the distance from the spherical surface boundary of the spherical cover (3) to the sphere center and the distance from the spherical surface boundary of the spherical support sleeve (4) to the sphere center is less than half of the spherical surface radius of the spherical support body (2).

6. The installation structure of a helicopter reducer and an engine according to claim 1, characterized in that: The sum of the distance from the spherical surface boundary of the spherical cover (3) to the sphere center and the distance from the spherical surface boundary of the spherical support sleeve (4) to the sphere center is greater than one third of the spherical surface radius of the spherical support body (2).

7. The installation structure of a helicopter reducer and engine according to claim 1, characterized in that: The centers of the matching spherical surfaces of the spherical support body (2), the spherical cover (3) and the spherical support sleeve (4) are located on the center line of the power shaft (9).

8. The installation structure of a helicopter reducer and engine according to claim 7, characterized in that: The power shaft (9) passes through the engine front shaft sleeve (1), the spherical support body (2), the spherical cover (3), the spherical support sleeve (4) and the reducer casing (5), and the power shaft (9) is fixedly connected to the spherical support body (2).

9. A method for assembling a helicopter reducer and an engine mounting structure, characterized in that: The method is applicable to a helicopter reducer and engine mounting structure as described in any one of claims 1 to 8, and the method comprises the following steps: Assembling the spherical support body (2) and the spherical support sleeve (4); The spherical cover (3) is assembled between the spherical support body (2) and the spherical support sleeve (4), and the outer sides of the spherical cover (3) and the spherical support sleeve (4) are fixedly connected.

10. The method for assembling the installation structure of a helicopter reducer and an engine according to claim 9, characterized in that: Before assembling the spherical support body (2) and the spherical support sleeve (4), Installing a sealing member (8) in the sealing groove (6); The lubrication chamber (7) is filled with grease.

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