Aircraft engine centrifugal ventilation impeller assembly disassembly device

Abstract

The invention discloses a decomposition device for centrifugal ventilation impeller assembly of an aircraft engine, comprising a base, a sleeve clamping claw and a core rod; the base is provided with a clearance groove, a vertically arranged gear shaft support column is fixed in the clearance groove, a plurality of pin support rods are detachably provided on the top of the base, and the pin support rods are vertically arranged on the base; the sleeve clamping claw is composed of a sleeve and a plurality of clamping claws, the plurality of clamping claws are threadedly connected in the sleeve and can open or close the clamping claws relative to the axial center line of the sleeve through relative rotation between the clamping claws and the sleeve; the core rod passes through the sleeve and faces the center of the base, and the end of the core rod is provided with a clamping tooth. The invention can stably limit and fix each connection point of the ventilation impeller assembly, reduce the difficulty of decomposition and improve the decomposition efficiency; at the same time, no hard tool directly contacts the peripheral surface of the gear shaft during the decomposition process, thereby avoiding secondary damage to the workpiece to be repaired.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine maintenance equipment, in particular to an aircraft engine centrifugal ventilation impeller component disassembly device. Background Art

[0002] Parts disassembly is an important part of aircraft engine maintenance, and the difficulty of parts disassembly is the key factor affecting maintenance efficiency.

[0003] The ventilation impeller assembly of the aircraft engine is sealed by two sealing rings after being assembled with the gear shaft. At the same time, an elastic clamp ring and a pin arranged on the ventilation impeller assembly are used to fix the ventilation impeller assembly and the gear shaft. When the ventilation impeller assembly is disassembled from the gear shaft, the elastic clamp ring is stuck in the clamping groove of the ventilation impeller assembly and the gear shaft through its own elastic expansion, and it is difficult to clamp the clamp ring for disassembly using ordinary disassembly tools. In addition, since both the sealing ring and the pin are installed in an interference fit manner, under the harsh working environment of the aircraft engine, factors such as thermal expansion and load stress cause the pin to deform and the sealing ring to expand, which increases the difficulty of disassembly. The disassembly can only be completed by using tools such as a knife and a needle and a complex disassembly method. In addition, it is easy to scratch the axial sealing surface of the gear shaft during the disassembly process, and in severe cases, it may even cause human damage. Therefore, the existing ventilation impeller assembly disassembly process is not only time-consuming and labor-intensive, but also may cause great economic losses. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a device for disassembling a centrifugal ventilation impeller assembly of an aero-engine which can reduce the difficulty of disassembly and improve the efficiency of disassembly.

[0005] In order to solve the above technical problems, the technical solution adopted by the present invention is: a disassembly device for a centrifugal ventilation impeller assembly of an aircraft engine, comprising a base, a sleeve clamping claw and a core rod; a clearance groove is provided on the base, a vertically arranged gear shaft support column is fixed inside the clearance groove, and a plurality of pin support rods are detachably provided on the top of the base, and the pin support rods are vertically arranged on the base; the sleeve clamping claw is composed of a sleeve and a plurality of clamping claws, and the plurality of clamping claws are threadedly connected in the sleeve and can open or close the clamping claws relative to the axial center line of the sleeve through relative rotation between the clamping claws and the sleeve; the core rod passes through the sleeve and is opposite to the center of the base, and the end of the core rod is provided with clamping teeth.

[0006] Furthermore, a vertically arranged enclosure is fixed on the base, the enclosure is arranged in a ring shape and connected end to end to form a clearance groove, and the gear shaft support column is fixed at the center of the clearance groove.

[0007] Furthermore, a limit baffle is fixed on the pin support rod, and an adjustment hole corresponding to the pin support rod is provided on the top of the base, and the bottom of the pin support rod passes through the adjustment hole and is fixed to the base by a locking screw.

[0008] Furthermore, it also includes an adjustment window arranged on the enclosure, which corresponds one-to-one to the adjustment holes and is connected to the corresponding adjustment holes; a locking screw threadedly connected to the bottom of the pin support rod extends from the adjustment hole into the adjustment window.

[0009] Furthermore, the size of the limit baffle and the end size of the locking screw are both larger than the aperture of the adjustment hole. The limit baffle and the locking screw are respectively abutted against the top and bottom of the adjustment hole to form a limit fit with the adjustment hole and clamp the pin support rod on the base.

[0010] Furthermore, the number of the pin support rods is three, and the three pin support rods are evenly distributed in a ring shape on the top of the base.

[0011] Furthermore, four claws are arranged on the sleeve claw, and the four claws are evenly distributed in the sleeve in a ring shape, and the bottoms of the claws extend out of the sleeve.

[0012] The beneficial effects of the present invention are as follows: the present invention fixes and limits the lower part of the ventilation impeller assembly and the gear shaft through the base, compresses the elastic clamping ring arranged between the ventilation impeller assembly and the gear shaft through the sleeve claw, and limits the upper part of the gear shaft through the core rod, so that the core rod is used to apply axial force to the gear shaft to overcome the tension of the two sealing rings, thereby completing the disassembly of the ventilation impeller assembly from the gear shaft; the present invention can stably limit and fix each connection point of the ventilation impeller assembly, which is convenient for the staff to apply force to the ventilation impeller assembly through the core rod, reducing the difficulty of disassembly and improving the disassembly efficiency; at the same time, during the disassembly process, no hard tool directly contacts the circumferential surface of the gear shaft, thereby avoiding secondary damage to the workpiece to be repaired. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of the present invention after being assembled with a ventilation impeller assembly;

[0014] Figure 2 It is a structural schematic diagram of the base in the present invention;

[0015] Figure 3 It is a schematic diagram of the structure of the sleeve claw in the present invention;

[0016] Markings in the figure are: 100-base, 110-gap groove, 120-gear shaft support column, 130-pin support rod, 131-limit baffle, 132-locking screw, 140-enclosure, 141-adjustment window, 200-sleeve claw, 210-sleeve, 220-claw, 300-core rod, 400-ventilation impeller assembly. DETAILED DESCRIPTION

[0017] In order to facilitate the understanding of the present invention, the present invention is further described below in conjunction with the accompanying drawings.

[0018] In the description of the present invention, it should be noted that the directions or positional relationships indicated by terms such as “front”, “rear”, “left”, “right”, “up”, “down”, and “inside” are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of description. They do not indicate or imply that the device or component referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0019] like Figure 1 As shown, the aircraft engine centrifugal ventilation impeller assembly disassembly device disclosed in the present invention is composed of a base 100, a sleeve claw 200 and a core rod 300. The ventilation impeller assembly 400 can be disassembled from the gear shaft through the cooperation of the base 100, the sleeve claw 200 and the core rod 300.

[0020] In order to be compatible with the ventilation impeller assembly and the gear shaft, the present invention specifically defines the structures of the base 100, the sleeve claw 200 and the core rod 300, such as Figure 1 and Figure 2 As shown, a clearance groove 110 is provided on the base 100, and a gear shaft support column 120 is fixed in the clearance groove 110; specifically, the clearance groove 110 is formed by a circle of vertically arranged enclosures 140 arranged in a ring shape and connected end to end, and the clearance groove 110 is the space enclosed by the enclosures 140 on the base 100, and the gear shaft support column 120 is vertically fixed at the center of the clearance groove 110. The clearance groove 110 is used to make way for the lower part of the gear shaft. The lower part of the gear shaft has a connecting hole, and the gear shaft support column 120 can be directly inserted into the connecting hole at the lower part of the gear shaft, which supports the assembly structure of the ventilation impeller assembly 400 and the gear shaft on the one hand, and limits the gear shaft on the other hand. In order to improve the limiting effect of the gear shaft support column 120 on the gear shaft, the optimal solution is to use a cylinder that matches the shape of the connecting hole at the bottom of the gear shaft, and the outer diameter of the gear shaft support column 120 should match the hole diameter of the connecting hole at the bottom of the gear shaft.

[0021] like Figure 1 and Figure 2As shown, a pin support rod 130 is also provided on the base 100, and the pin support rod 130 is vertically fixed on the top of the enclosure 140 of the base 100. The pin support rod 130 is provided to support the pins on the ventilation impeller assembly 400 and provide a support point for the ventilation impeller assembly 400 when it is disassembled; therefore, the number and setting positions of the pin support rods 130 in the present invention should correspond one-to-one to the pins on the ventilation impeller assembly 400. Since the number of pins on the ventilation impeller assembly 400 is three and is evenly distributed in a ring shape, the pin support rods 130 in the present invention are also set to three, and the three pin support rods 130 are evenly distributed in a ring shape on the top of the base 100.

[0022] Since the pins on the ventilation impeller assembly 400 are installed on the ventilation impeller assembly 400 by means of interference fit, they are affected by the harsh working environment of the aircraft engine for a long time. Due to factors such as thermal expansion and load stress, the pins and the aircraft engine itself will be deformed, which will cause the position of the pins to shift compared to the original design position. Furthermore, in order to enable the pin support rod 130 to be accurately aligned with the corresponding pin, the pin support rod 130 is set as a detachable and adjustable structure in the present invention. Specifically, Figure 1 and Figure 2 As shown, a limit baffle 131 is vertically fixed on the pin support rod 130, and at the same time, an adjustment hole corresponding to the pin support rod 130 is opened on the top of the base 100, that is, the enclosure 140, and a locking screw 132 is threadedly connected to the bottom of the pin support rod 130. The size of the limit baffle 131 and the end size of the locking screw 132 are both larger than the aperture of the adjustment hole; the pin support rod 130 is passed through the corresponding adjustment hole so that the limit baffle 131 and the locking screw 132 respectively abut against the upper and lower ends of the adjustment hole, thereby clamping the pin support rod 130 at the adjustment hole. The adjustment hole adopts a round hole or a long hole with an aperture larger than the outer diameter of the pin support rod 130. The position of the pin support rod 130 can be adjusted by adjusting the position of the pin support rod 130 in the adjustment hole and then clamping the pin support rod 130.

[0023] Furthermore, in order to facilitate the staff to operate the locking screw 132 to adjust the position of the pin support rod 130, the present invention also provides an adjustment window 141, such as Figure 1 and Figure 2 As shown, adjustment windows 141 corresponding to the adjustment holes are opened on the circumferential surface of the enclosure 140, and the adjustment window 141 is connected to the corresponding adjustment hole. Then, the locking screw 132 threadedly connected to the bottom of the pin support rod 130 extends from the adjustment hole to the adjustment window 141, and the staff can insert tools such as wrenches into the adjustment window 141 to tighten the locking screw 132.

[0024] like Figure 1 and Figure 3 As shown, the sleeve claw 200 used in the present invention is composed of a sleeve 210 and a claw 220. The number of the claws 220 can be selected according to needs. Four claws 220 are used in the present invention. The four claws 220 are evenly distributed in the sleeve 210 in a ring shape. The bottom of the claw 220 extends out of the sleeve 210. The upper part of the claw 220 is threadedly connected in the sleeve 210. The claw 220 is opened or closed relative to the axial center line of the sleeve 210 through the relative rotation between the claw 220 and the sleeve 210, thereby realizing the clamping action of the claw 220; the claw 220 is used to clamp the elastic clamp ring on the gear shaft. The core rod 300 passes through the sleeve 210 and faces the center of the base 100. Since there is a latch tooth in the upper connecting hole of the gear shaft, a latch tooth engaged with the core rod 300 is provided at the end of the core rod 300. The core rod 300 is inserted into the connecting hole at the upper end of the gear shaft and forms a latching fit with the latch tooth in the gear shaft.

[0025] When the centrifugal ventilation impeller assembly disassembly device for an aircraft engine disclosed in the present invention is used to disassemble the ventilation impeller assembly 400 installed on the gear shaft, the following steps are performed:

[0026] S1, passing the sleeve claw 200 through the upper part of the gear shaft, rotating the sleeve claw 200 so that the claw 220 clamps the elastic clamp ring to compress the elastic claw;

[0027] S2. Place the base 100 on a horizontal ground, align the connection hole of the lower half of the gear shaft with the gear shaft support column 120 on the base 100, insert the gear shaft support column 120 into the connection, rotate the ventilation impeller assembly 400 so that the pin on the ventilation impeller assembly 400 is aligned with the pin support rod 130 on the base 100, so that the ventilation impeller assembly 400 is supported on the base 100;

[0028] S3. Insert the mandrel 300 into the connecting hole of the upper part of the gear shaft so that the teeth at the end of the mandrel 300 are clamped with the internal teeth in the connecting hole of the upper part of the gear shaft. Apply force in the axial direction of the gear shaft through the mandrel 300 to overcome the tension of the two sealing rings and disassemble the ventilation impeller assembly 400 from the gear shaft.

Claims

1. A device for disassembling centrifugal fan impeller components of an aircraft engine, characterized in that: The invention comprises a base (100), a sleeve clamping claw (200) and a core rod (300); the base (100) is provided with a clearance groove (110), a vertically arranged gear shaft support column (120) is fixed inside the clearance groove (110), a plurality of pin support rods (130) are detachably provided on the top of the base (100), and the pin support rods (130) are vertically arranged on the base (100); the sleeve clamping claw (200) is formed by the sleeve (210) and a plurality of claws (220), the plurality of claws (220) are threadedly connected in the sleeve (210) and can open or close the claws (220) relative to the axial center line of the sleeve (210) through relative rotation between the claws (220) and the sleeve (210); the mandrel (300) passes through the sleeve (210) and faces the center of the base (100), and the end of the mandrel (300) is provided with a tooth; A vertically arranged enclosure (140) is fixed on the base (100), the enclosure (140) is arranged in a ring shape and connected end to end to form a clearance groove (110), and the gear shaft support column (120) is fixed at the center of the clearance groove (110); a limit baffle (131) is fixed on the pin support rod (130), and an adjustment hole corresponding to the pin support rod (130) is provided on the top of the base (100), and the bottom of the pin support rod (130) passes through the adjustment hole and is fixed to the base (100) by a locking screw (132).

2. The aircraft engine centrifugal fan impeller assembly disassembly device according to claim 1, characterized in that: It also includes an adjustment window (141) arranged on the enclosure (140), wherein the adjustment window (141) corresponds to the adjustment hole one by one and is connected to the corresponding adjustment hole; a locking screw (132) threadedly connected to the bottom of the pin support rod (130) extends from the adjustment hole into the adjustment window (141).

3. The aircraft engine centrifugal fan impeller assembly disassembly device according to claim 2, characterized in that: The size of the limit baffle (131) and the end size of the locking screw (132) are both larger than the diameter of the adjustment hole. The limit baffle (131) and the locking screw (132) are respectively abutted against the top and bottom of the adjustment hole to form a limit fit with the adjustment hole and clamp the pin support rod (130) on the base (100).

4. The aircraft engine centrifugal fan impeller assembly disassembly device according to claim 1, characterized in that: The number of the pin support rods (130) is three, and the three pin support rods (130) are evenly distributed in a ring shape on the top of the base (100).

5. The aircraft engine centrifugal fan impeller assembly disassembly device according to claim 1, characterized in that: The sleeve clamping claw (200) is provided with four clamping claws (220), the four clamping claws (220) are evenly distributed in the sleeve (210) in a ring shape, and the bottoms of the clamping claws (220) extend out of the sleeve (210).

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