Aero-engine turbine shaft spline grinding device and grinding method

Abstract

The invention discloses an aero-engine turbine shaft spline grinding device and method. The aero-engine turbine shaft spline grinding device comprises a machine body, an adjusting mechanism is arranged on the inner side of the machine body, a grinding assembly is arranged below the adjusting mechanism, a limiting mechanism is arranged below the grinding assembly, and an aero-engine turbine shaft body is clamped on the inner side of the limiting mechanism; the adjusting mechanism comprises a first positive and negative screw rod, the first positive and negative screw rod is erected on the inner side of the bottom of the machine body, and a driving wheel is fixedly connected to the right end of the first positive and negative screw rod. And at the moment, the first forward and reverse screw rod and the second forward and reverse screw rod rotate in the same direction, so that a group of limiting frames and a group of movable blocks are driven to be far away from or close to each other, the distance between the group of limiting frames and the group of movable blocks is adjusted, clamping limiting and dismounting of an aero-engine turbine shaft body and a grinding roller can be achieved at the same time, and the dismounting efficiency is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine turbine shaft processing, and in particular to an aircraft engine turbine shaft spline grinding device and a grinding method. Background Art

[0002] The turbine shaft is an important mechanical transmission component, which is widely used in various rotating mechanical devices. It has a unique structure and working principle, and can convert fluid power into mechanical energy and transmit it to the driven equipment. The turbine shaft plays an important role in the fields of automobile, wind power generation, aerospace, etc. The turboshaft engine uses the airflow generated by the combustion chamber to drive the free turbine output shaft power instead of jet thrust. In the production process of aircraft engine turbine shaft, it is necessary to use a grinding device to grind the spline on its surface.

[0003] The existing aircraft engine turbine shaft spline grinding device needs to replace grinding rollers of different lengths according to the turbine shafts of different lengths during use. Therefore, the turbine shaft and the grinding roller need to be limited and fixed separately before the grinding process, which is time-consuming and increases the complexity of the process. Therefore, we propose an aircraft engine turbine shaft spline grinding device and grinding method. Summary of the invention

[0004] The object of the present invention is to provide an aircraft engine turbine shaft spline grinding device and a grinding method to solve the problem that the existing aircraft engine turbine shaft spline grinding device proposed in the above background technology needs to replace grinding rollers of different lengths according to turbine shafts of different lengths during use. Therefore, the turbine shaft and the grinding roller need to be limited and fixed separately before the grinding process, which is time-consuming and increases the complexity of the process.

[0005] To achieve the above-mentioned object, the present invention provides the following technical solutions: an aircraft engine turbine shaft spline grinding device and grinding method, comprising a body, an adjusting mechanism is provided inside the body, a grinding assembly is provided below the adjusting mechanism, a limiting mechanism is provided below the grinding assembly, and an aircraft engine turbine shaft body is clamped inside the limiting mechanism;

[0006] The adjustment mechanism includes a first forward and reverse screw rod, which is mounted on the inner side of the bottom of the machine body, a driving wheel is fixedly connected to the right end of the first forward and reverse screw rod, and a first motor is connected to the right end of the driving wheel. A group of limit frames are symmetrically sleeved on the surface of the first forward and reverse screw rod, a driven wheel is arranged above the driving wheel, and a transmission belt is sleeved on the outside of the driving wheel and the driven wheel, a second forward and reverse screw rod is fixedly connected to the left end of the driven wheel, and a group of movable blocks are symmetrically sleeved on the surface of the second forward and reverse screw rod.

[0007] Preferably, the driving wheel forms a transmission structure through the first motor, a transmission belt and a driven wheel.

[0008] Preferably, the first forward and reverse screw rod and the second forward and reverse screw rod are parallel to each other, and the first forward and reverse screw rod and the second forward and reverse screw rod are respectively threadedly connected to the limit frame and the movable block.

[0009] Preferably, the grinding assembly includes a multi-stage hydraulic cylinder, a group of the multi-stage hydraulic cylinders are respectively arranged at the lower end of a group of movable blocks, a group of movable ends of the multi-stage hydraulic cylinders are symmetrically connected to a group of brackets, a grinding roller is clamped between a group of brackets, the end of the grinding roller is connected to a second motor, and a positioning frame is fixed to the outside of the second motor.

[0010] Preferably, the bracket forms a lifting structure through a multi-stage hydraulic cylinder and a movable block, and the bracket is fixedly connected to the positioning frame.

[0011] Preferably, the limiting mechanism includes a T-shaped shaft, a group of the T-shaped shafts are symmetrically clamped on the inner side of a group of limiting frames, the small diameter end of the T-shaped shaft is fixedly connected to a groove frame, the large diameter end of the right T-shaped shaft is connected to a third motor, the third motor is provided with a tube frame on the outside, a number of electric push rods are evenly distributed on the inner wall of the groove frame, the movable end of the electric push rod is connected to a limiting arc plate, and an anti-slip rubber pad is bonded to the inside of the limiting arc plate.

[0012] Preferably, the T-shaped shaft is movably engaged in the limiting frame, and the third motor forms a rotating structure with the slot frame through the T-shaped shaft.

[0013] Preferably, the limiting arc plate and the slot frame form a telescopic structure through an electric push rod, and the anti-slip rubber pad fits well on the inner arc surface of the limiting arc plate.

[0014] Preferably, the

[0015] S1. The staff drives the driving wheel and the first forward and reverse screw rod to rotate through the first motor. At the same time, the driven wheel rotates with the action of the transmission belt. At this time, the first forward and reverse screw rod and the second forward and reverse screw rod rotate in the same direction, thereby driving a group of limit frames and a group of movable blocks to move away from each other, thereby adjusting the distance between a group of limit frames and a group of movable blocks;

[0016] S2. After the spacing between a set of limit frames and a set of movable blocks is adjusted, the aircraft engine turbine shaft body and the grinding roller are placed between the set of limit frames and the set of movable blocks respectively, and then the first forward and reverse screw rods and the second forward and reverse screw rods are driven by the first motor to rotate so that the set of limit frames and the set of movable blocks are close to each other, so that the clamping and limiting of the aircraft engine turbine shaft body and the grinding roller can be achieved at the same time, thereby improving the limiting efficiency;

[0017] S3. Then, the electric push rod drives the limit arc plate to move, so that the anti-skid rubber pad fits the surface of the aircraft engine turbine shaft body, increases the friction with the surface of the aircraft engine turbine shaft body, and simultaneously places the aircraft engine turbine shaft body in the center of the slot frame;

[0018] S4, then the grinding roller is driven to rotate by the second motor, and at the same time, the multi-stage hydraulic cylinder drives the bracket and the grinding roller to move downward, so that the grinding roller contacts the surface of the aircraft engine turbine shaft body to achieve grinding;

[0019] S5. Then, the multi-stage hydraulic cylinder drives the bracket and the grinding roller to move upward, and at the same time, the third motor drives the T-shaped shaft rod and the slot frame to rotate, thereby driving a group of aircraft engine turbine shaft bodies inside the slot frame to rotate, and adjusting the angle of the aircraft engine turbine shaft body to facilitate grinding of different parts of the surface of the aircraft engine turbine shaft body;

[0020] S6. After the spline grinding is completed, the electric push rod drives the limit arc plate to move, so that the anti-skid rubber pad is away from the surface of the aircraft engine turbine shaft body, and then the first motor drives the first forward and reverse screw rods and the second forward and reverse screw rods to rotate so that a group of limit frames and a group of movable blocks are away from each other, so that the aircraft engine turbine shaft body and the grinding roller can be removed synchronously.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. The present invention effectively drives the driving wheel and the first forward and reverse screw to rotate through the first motor, and at the same time, the driven wheel rotates with the action of the transmission belt. At this time, the first forward and reverse screw and the second forward and reverse screw rotate in the same direction, thereby driving a group of limit frames and a group of movable blocks to move away from or close to each other, and then adjusting the distance between a group of limit frames and a group of movable blocks, which can simultaneously realize the clamping, limiting and removal of the aircraft engine turbine shaft body and the grinding roller, thereby improving the disassembly and assembly efficiency.

[0023] 2. The present invention effectively drives the grinding roller to rotate through the second motor, and at the same time the multi-stage hydraulic cylinder effectively drives the bracket and the grinding roller to move downward, so that the grinding roller contacts the surface of the aircraft engine turbine shaft body to achieve grinding.

[0024] 3. The present invention drives the limit arc plate to move through the electric push rod, so that the anti-skid rubber pad fits the surface of the aircraft engine turbine shaft body, increases the friction with the surface of the aircraft engine turbine shaft body, and at the same time, the aircraft engine turbine shaft body is placed centrally in the slot frame. The third motor effectively drives the T-shaped shaft rod and the slot frame to rotate, thereby driving a group of aircraft engine turbine shaft bodies on the inner side of the slot frame to rotate, adjusts the angle of the aircraft engine turbine shaft body, and facilitates the grinding of different parts of the surface of the aircraft engine turbine shaft body. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0026] Figure 2 It is another perspective overall structural schematic diagram of the present invention;

[0027] Figure 3 It is a schematic diagram of the three-dimensional structure of the adjustment mechanism of the present invention;

[0028] Figure 4 It is a schematic diagram of the three-dimensional structure of the grinding assembly of the present invention;

[0029] Figure 5 It is a schematic diagram of the partial disassembly structure of the limiting mechanism of the present invention;

[0030] In the figure: 1. body; 2. adjustment mechanism; 3. grinding assembly; 4. limit mechanism; 5. aircraft engine turbine shaft body;

[0031] 201, first forward and reverse screw rod; 202, driving wheel; 203, first motor; 204, limit frame; 205, driven wheel; 206, transmission belt; 207, second forward and reverse screw rod; 208, movable block;

[0032] 301, multi-stage hydraulic cylinder; 302, bracket; 303, grinding roller; 304, second motor; 305, positioning frame;

[0033] 401, T-shaped shaft; 402, slot frame; 403, third motor; 404, cylinder frame; 405, electric push rod; 406, limit arc plate; 407, anti-skid rubber pad. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] See also Figure 1-5 The present invention provides a technical solution: a grinding device and a grinding method for a turbine shaft spline of an aircraft engine, comprising a body 1, an adjusting mechanism 2 is provided inside the body 1, a grinding assembly 3 is provided below the adjusting mechanism 2, a limiting mechanism 4 is provided below the grinding assembly 3, and an aircraft engine turbine shaft body 5 is clamped inside the limiting mechanism 4;

[0036] The adjustment mechanism 2 includes a first forward and reverse screw rod 201, which is mounted on the inner side of the bottom of the body 1. The right end of the first forward and reverse screw rod 201 is fixedly connected to a driving wheel 202, and the right end of the driving wheel 202 is connected to a first motor 203. A set of limit frames 204 are symmetrically sleeved on the surface of the first forward and reverse screw rod 201, and a driven wheel 205 is arranged above the driving wheel 202. A transmission belt 206 is sleeved on the outside of the driving wheel 202 and the driven wheel 205, wherein the driving wheel 202 forms a transmission structure through the first motor 203, the transmission belt 206 and the driven wheel 205, the left end of the driven wheel 205 is fixedly connected to the second forward and reverse screw rod 207, and a group of movable blocks 208 are symmetrically sleeved on the surface of the second forward and reverse screw rod 207. Furthermore, the first forward and reverse screw rod 201 and the second forward and reverse screw rod 207 are parallel to each other, and the first forward and reverse screw rod 201 and the second forward and reverse screw rod 207 are threadedly connected to the limit frame 204 and the movable block 208 respectively. The present invention effectively drives the driving wheel 202 and the first forward and reverse screw rod 201 to rotate through the first motor 203, and at the same time, under the action of the transmission belt 206, the driven wheel 205 follows the rotation. At this time, the first forward and reverse screw rod 201 and the second forward and reverse screw rod 207 rotate in the same direction, thereby driving a group of limit frames 204 and a group of movable blocks 208 to move away from or close to each other, and then adjusting the distance between a group of limit frames 204 and a group of movable blocks 208, which can simultaneously realize the clamping, limiting and removal of the aircraft engine turbine shaft body 5 and the grinding roller 303, thereby improving the disassembly and assembly efficiency.

[0037] The grinding assembly 3 includes a multi-stage hydraulic cylinder 301, a group of multi-stage hydraulic cylinders 301 are respectively arranged at the lower end of a group of movable blocks 208, a group of brackets 302 are symmetrically connected to the movable ends of a group of multi-stage hydraulic cylinders 301, a grinding roller 303 is clamped between a group of brackets 302, a second motor 304 is connected to the end of the grinding roller 303, and a positioning frame 305 is fixedly connected to the outside of the second motor 304, wherein the bracket 302 forms a lifting structure with the movable block 208 through the multi-stage hydraulic cylinder 301, and the bracket 302 and the positioning frame 305 are fixedly connected. The present invention effectively drives the grinding roller 303 to rotate through the second motor 304, and at the same time, the multi-stage hydraulic cylinder 301 effectively drives the bracket 302 and the grinding roller 303 to move downward, so that the grinding roller 303 contacts the surface of the aircraft engine turbine shaft body 5 to achieve grinding.

[0038] The limiting mechanism 4 includes a T-shaped shaft 401, a group of T-shaped shafts 401 are symmetrically clamped on the inner side of a group of limiting frames 204, the small diameter end of the T-shaped shaft 401 is fixedly connected to a slot frame 402, and the large diameter end of the right T-shaped shaft 401 is connected to a third motor 403, wherein the T-shaped shaft 401 is movably clamped inside the limiting frame 204, the third motor 403 forms a rotating structure with the slot frame 402 through the T-shaped shaft 401, the outer side of the third motor 403 is sleeved with a cylinder frame 404, and a plurality of electric push rods 405 are evenly distributed on the inner wall of the slot frame 402, the movable end of the electric push rod 405 is connected to a limiting arc plate 406, and an anti-skid rubber pad 407 is bonded to the inner side of the limiting arc plate 406, further, the limiting arc plate 406 forms a telescopic structure with the slot frame 402 through the electric push rod 405, and the anti-skid rubber pad 407 matches and fits the inner arc surface of the limiting arc plate 406. The present invention drives the limiting arc plate 406 to move through the electric push rod 405, so that the anti-skid rubber pad 407 fits the surface of the aircraft engine turbine shaft body 5, increases the friction with the surface of the aircraft engine turbine shaft body 5, and at the same time, the aircraft engine turbine shaft body 5 is placed centrally in the slot frame 402. The third motor 403 effectively drives the T-shaped shaft rod 401 and the slot frame 402 to rotate, thereby driving a group of aircraft engine turbine shaft bodies 5 on the inner side of the slot frame 402 to rotate, adjust the angle of the aircraft engine turbine shaft body 5, and facilitate grinding different parts of the surface of the aircraft engine turbine shaft body 5.

[0039] Working principle: The grinding device and grinding method for this type of aircraft engine turbine shaft spline are as follows:

[0040] S1. The staff drives the driving wheel 202 and the first forward and reverse screw rod 201 to rotate through the first motor 203. At the same time, the driven wheel 205 rotates with the action of the transmission belt 206. At this time, the first forward and reverse screw rod 201 and the second forward and reverse screw rod 207 rotate in the same direction, thereby driving a group of limit frames 204 and a group of movable blocks 208 to move away from each other, thereby adjusting the distance between a group of limit frames 204 and a group of movable blocks 208;

[0041] S2. After the spacing between a set of limit frames 204 and a set of movable blocks 208 is adjusted, the aircraft engine turbine shaft body 5 and the grinding roller 303 are placed between a set of limit frames 204 and a set of movable blocks 208, respectively. Then, the first forward and reverse screw rod 201 and the second forward and reverse screw rod 207 are driven by the first motor 203 to rotate so that the set of limit frames 204 and a set of movable blocks 208 are close to each other, and the clamping and limiting of the aircraft engine turbine shaft body 5 and the grinding roller 303 can be achieved at the same time, thereby improving the limiting efficiency.

[0042] S3, then the electric push rod 405 drives the limit arc plate 406 to move, so that the anti-slip rubber pad 407 fits the surface of the aircraft engine turbine shaft body 5, increases the friction with the surface of the aircraft engine turbine shaft body 5, and makes the aircraft engine turbine shaft body 5 centered in the slot frame 402;

[0043] S4, the grinding roller 303 is then driven to rotate by the second motor 304, and at the same time the multi-stage hydraulic cylinder 301 drives the bracket 302 and the grinding roller 303 to move downward, so that the grinding roller 303 contacts the surface of the aircraft engine turbine shaft body 5 to perform grinding;

[0044] S5, then the multi-stage hydraulic cylinder 301 drives the bracket 302 and the grinding roller 303 to move upward, and at the same time the third motor 403 drives the T-shaped shaft 401 and the slot frame 402 to rotate, thereby driving a group of aircraft engine turbine shaft bodies 5 inside the slot frame 402 to rotate, and adjusting the angle of the aircraft engine turbine shaft body 5, so as to facilitate grinding of different parts of the surface of the aircraft engine turbine shaft body 5;

[0045] S6. After the spline grinding is completed, the electric push rod 405 drives the limit arc plate 406 to move, so that the anti-skid rubber pad 407 is away from the surface of the aircraft engine turbine shaft body 5, and then the first motor 203 drives the first forward and reverse screw rod 201 and the second forward and reverse screw rod 207 to rotate so that a group of limit frames 204 and a group of movable blocks 208 are away from each other, so that the aircraft engine turbine shaft body 5 and the grinding roller 303 can be removed synchronously.

[0046] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft engine turbine shaft spline grinding device, comprising a body (1), characterized in that: An adjusting mechanism (2) is provided inside the body (1), a grinding assembly (3) is provided below the adjusting mechanism (2), a limiting mechanism (4) is provided below the grinding assembly (3), and an aircraft engine turbine shaft body (5) is clamped inside the limiting mechanism (4); The adjusting mechanism (2) comprises a first forward and reverse screw rod (201), the first forward and reverse screw rod (201) is mounted on the inner side of the bottom of the machine body (1), the right end of the first forward and reverse screw rod (201) is fixedly connected to a driving wheel (202), the right end of the driving wheel (202) is connected to a first motor (203), a group of limit frames (204) are symmetrically sleeved on the surface of the first forward and reverse screw rod (201), a driven wheel (205) is arranged above the driving wheel (202), a transmission belt (206) is sleeved on the outside of the driving wheel (202) and the driven wheel (205), a second forward and reverse screw rod (207) is fixedly connected to the left end of the driven wheel (205), and a group of movable blocks (208) are symmetrically sleeved on the surface of the second forward and reverse screw rod (207).

2. The aero-engine turbine shaft spline grinding device according to claim 1, characterized in that: The driving wheel (202) forms a transmission structure with the driven wheel (205) through the first motor (203), the transmission belt (206) and the driven wheel (205).

3. The aero-engine turbine shaft spline grinding device according to claim 1, characterized in that: The first forward and reverse screw rod (201) and the second forward and reverse screw rod (207) are parallel to each other, and the first forward and reverse screw rod (201) and the second forward and reverse screw rod (207) are respectively threadedly connected to the limit frame (204) and the movable block (208).

4. The aero-engine turbine shaft spline grinding device according to claim 1, characterized in that: The grinding assembly (3) comprises a multi-stage hydraulic cylinder (301), a group of the multi-stage hydraulic cylinders (301) are respectively arranged at the lower end of a group of movable blocks (208), a group of movable ends of the multi-stage hydraulic cylinders (301) are symmetrically connected to a group of brackets (302), a grinding roller (303) is clamped between a group of brackets (302), the end of the grinding roller (303) is connected to a second motor (304), and a positioning frame (305) is fixed to the outside of the second motor (304).

5. The aero-engine turbine shaft spline grinding device according to claim 4, characterized in that: The support (302) forms a lifting structure through a multi-stage hydraulic cylinder (301) and a movable block (208), and the support (302) and the positioning frame (305) are fixedly connected.

6. The aero-engine turbine shaft spline grinding device according to claim 1, characterized in that: The limiting mechanism (4) comprises a T-shaped shaft (401), a group of the T-shaped shafts (401) are symmetrically clamped on the inner side of a group of limiting frames (204), a small diameter end of the T-shaped shaft (401) is fixedly connected to a slot frame (402), a large diameter end of the right T-shaped shaft (401) is connected to a third motor (403), a cylinder frame (404) is sleeved on the outside of the third motor (403), a plurality of electric push rods (405) are evenly distributed on the inner wall of the slot frame (402), a movable end of the electric push rod (405) is connected to a limiting arc plate (406), and an anti-slip rubber pad (407) is bonded to the inner side of the limiting arc plate (406).

7. The aero-engine turbine shaft spline grinding device according to claim 6, characterized in that: The T-shaped shaft (401) is movably engaged in the interior of the limiting frame (204), and the third motor (403) forms a rotating structure through the T-shaped shaft (401) and the slot frame (402).

8. The aero-engine turbine shaft spline grinding device according to claim 6, characterized in that: The limiting arc plate (406) forms a telescopic structure with the slot frame (402) through the electric push rod (405), and the anti-slip rubber pad (407) matches and fits the inner arc surface of the limiting arc plate (406).

9. An aircraft engine turbine shaft spline grinding device and grinding method according to claims 1-8, characterized in that: S1, the staff drives the driving wheel (202) and the first forward and reverse screw rod (201) to rotate through the first motor (203), and at the same time, the driven wheel (205) rotates with the action of the transmission belt (206). At this time, the first forward and reverse screw rod (201) and the second forward and reverse screw rod (207) rotate in the same direction, thereby driving a group of limit frames (204) and a group of movable blocks (208) to move away from each other, thereby adjusting the distance between a group of limit frames (204) and a group of movable blocks (208); S2. After the spacing between a set of limiting frames (204) and a set of movable blocks (208) is adjusted, the aircraft engine turbine shaft body (5) and the grinding roller (303) are respectively placed between the set of limiting frames (204) and the set of movable blocks (208). Then, the first forward and reverse screw rods (201) and the second forward and reverse screw rods (207) are driven by the first motor (203) to rotate so that the set of limiting frames (204) and the set of movable blocks (208) are close to each other, so that the clamping and limiting of the aircraft engine turbine shaft body (5) and the grinding roller (303) can be achieved at the same time, thereby improving the limiting efficiency. S3, then the electric push rod (405) drives the limit arc plate (406) to move, so that the anti-skid rubber pad (407) fits the surface of the aircraft engine turbine shaft body (5), increases the friction force with the surface of the aircraft engine turbine shaft body (5), and simultaneously places the aircraft engine turbine shaft body (5) in the center of the slot frame (402); S4, the grinding roller (303) is then driven to rotate by the second motor (304), and at the same time, the multi-stage hydraulic cylinder (301) drives the bracket (302) and the grinding roller (303) to move downward, so that the grinding roller (303) contacts the surface of the aircraft engine turbine shaft body (5) to achieve grinding; S5, the multi-stage hydraulic cylinder (301) then drives the bracket (302) and the grinding roller (303) to move upward, and at the same time the third motor (403) drives the T-shaped shaft (401) and the slot frame (402) to rotate, thereby driving a group of aircraft engine turbine shaft bodies (5) inside the slot frame (402) to rotate, and adjusting the angle of the aircraft engine turbine shaft body (5) to facilitate grinding of different parts of the surface of the aircraft engine turbine shaft body (5); S6. After the spline grinding is completed, the electric push rod (405) drives the limit arc plate (406) to move, so that the anti-skid rubber pad (407) is away from the surface of the aircraft engine turbine shaft body (5), and then the first motor (203) drives the first forward and reverse screw rod (201) and the second forward and reverse screw rod (207) to rotate so that a group of limit frames (204) and a group of movable blocks (208) are away from each other, so that the aircraft engine turbine shaft body (5) and the grinding roller (303) can be removed synchronously.

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