CN108080925B - Device and method for disassembling outer ring of roller bearing in annular cavity - Google Patents

Abstract

The invention belongs to the technical field of aircraft engine assembly, and particularly relates to a device and a method for decomposing a bearing outer ring in an annular cavity, which aim to solve the problem of decomposition of a roller bearing outer ring which is arranged in a narrow annular cavity in a large interference fit manner. The method is characterized in that: the pulling claws 6 for decomposing the outer ring of the bearing are circumferentially and uniformly hinged on the linkage ring 4 to form a linkage ring assembly, the linkage ring assembly is integrally installed in the annular cavity, and the pulling claws 6 are aligned by rotating the linkage ring 4. The claw 6 realizes radial expansion through a revolute pair at the hinged position and is attached to the process opening by utilizing the molded surface of the head of the claw. A precise limiting cylinder 1 is arranged between the pulling claws to realize the radial reliable constraint of the pulling claws. And finally, the coupling ring 4 and the pulling claw 6 are driven to move along the axial direction by a screw pair between the jackscrew 3 and the coupling ring 4, so that the bearing outer ring is driven to move along the axial direction, and the bearing outer ring is disassembled. The device is suitable for disassembling interference fit zero (assembly) components installed in the annular cavity.

Description

Device and method for disassembling outer ring of roller bearing in annular cavity

Technical Field

The invention belongs to the technical field of aircraft engine assembly, and particularly relates to a device for decomposing a roller bearing outer ring which is arranged in an annular cavity in a large interference fit manner.

Background

The assembly work is a later process in the manufacturing process of the aero-engine, occupies an important position in the whole production process, and is an independent production stage. The engine assembly process is not a simple stacking process of zero components, but is performed according to specified technical standards, technical requirements and a series of process procedures and quality control procedures of different complexity. These procedures are performed by an assembly worker using a special or general purpose tooling fixture. Whether the design of the tooling fixture for assembling the aero-engine is scientific and reasonable directly influences the assembly progress of the engine and also concerns the performance, service life and working reliability of the engine. Because the structures and the overall dimensions of various engines are different, the working conditions, the technical requirements and the manufacturing precision of various components are different, and different engines are assembled, and different assembling tool fixtures need to be customized for the engines. The advanced assembly fixture is an important guarantee for solving the assembly of a complex structure, ensuring the safety of engine components, meeting the technical requirements of complex structure design and improving the labor productivity.

Rolling bearings are components that rely on rolling contact between major elements to support the high speed rotation of an aircraft engine rotor. In aircraft engine rotor systems and accessories, single-row radial thrust roller bearings are mainly used for the case of transmitting only radial loads. The outer ring of the roller bearing is sometimes mounted in an annular cavity, subject to the structural constraints of the engine rotor. The outer race of a roller bearing sometimes requires a large interference fit with the bearing mount, depending on the magnitude and direction of the bearing load and the nature of the load. The bearing which is arranged in the annular cavity in a large interference fit mode is safely and efficiently decomposed, and is important content for assembling the aero-engine.

Disclosure of Invention

1) Objects of the invention

At present, for the disassembly of the bearing, a three-jaw puller, a diagonal puller and a puller are generally adopted, or the bearing is pushed out by a press. These methods require a large operating space around the bearing to be disassembled (which can be fitted into a puller or press adapter). For the decomposition of the outer ring of the roller bearing in a narrow annular cavity of an aircraft engine rotor by adopting interference fit, a tool clamp is required to be specially developed and designed. The special tool fixtures have the common problems that the axial direction is not positioned, the whole fixture is difficult to be arranged in an annular cavity, the radial constraint of the working position of the tool fixture is unreliable, the damage to the working surface of the bearing is easily caused in the decomposition process, and the like. The invention provides a special device for bearing decomposition, which can realize the integral assembly of a decomposition device, has accurate axial positioning and reliable radial constraint and eliminates the risk of damaging a bearing in the operation process.

2) Technical scheme

The utility model provides a roller bearing outer lane decomposition device in annular chamber, contains: the device comprises a limiting cylinder (1), a screw (2), a jackscrew (3), a linkage ring (4), a blocking cover (5), a pulling claw (6), a pin (7) and a cotter pin (8). Wherein, the pulling claws (6) are uniformly hinged in the linkage ring (4) through pins (7) and cotter pins (8) to form a linkage ring component. When the linkage ring assembly pulling device works, the linkage ring assembly is integrally arranged in the annular cavity, the linkage ring assembly pulling claw (6) is inserted into the limiting cylinder (1), and the radial limiting of the pulling claw (6) is realized through the outer cylindrical surface of the limiting cylinder (1); a jackscrew (3) is screwed into the linkage ring (4). Jackscrew (3) directly or indirectly (bearing frame terminal surface installation protective sheath etc.) support the bearing frame and keep away from the terminal surface of one side of annular chamber, synchronous screw in jackscrew (3) drive linkage ring (4), claw (6) drive bearing inner race along axial displacement, realize the separation of bearing inner race and bearing frame.

A method for disassembling an outer ring of a roller bearing in an annular cavity comprises the following steps:

step 1: and (3) installing the limiting stop end of the plug cover (5) to the outer end face of the rotor bearing seat to enable the plug cover (5) to be attached to the outer end face of the bearing seat.

Step 2: the non-threaded hole end of a pulling claw (6) of the linkage ring assembly faces the bearing seat and is installed in an annular cavity between the rotor bearing seat and the shaft, so that the end face of the linkage ring (4) is in contact with the blocking cover (5); the linkage ring assembly is rotated in the circumferential direction properly to finish the alignment of the pulling claw (6).

And step 3: and enabling the limiting cylinder (1) to penetrate through the shaft of the rotor and be installed between the pulling claws of the linkage ring assembly. And (3) properly rotating the limiting cylinder (1) to align the unthreaded hole on the limiting cylinder with the threaded hole of the pulling claw (6) on the linkage ring assembly and attach the unthreaded hole to the end surface of the pulling claw (6). The limiting cylinder (1) and the pulling claw (6) are connected and fastened through a screw (2).

And 4, step 4: and synchronously screwing the jackscrew (3) into the threaded hole on the linkage ring (4) until the jackscrew (3) is contacted with the plug cover (5). And continuously synchronously screwing the jackscrew (3) until the outer ring of the roller bearing is completely separated from the bearing seat by a claw (6) on the bearing disassembling device.

And 5: and taking down the outer ring of the roller bearing from the decomposition device of the outer ring of the roller bearing in the annular cavity.

The beneficial effects are as follows:

the device and the method for decomposing the outer ring of the roller bearing in the annular cavity provided by the invention realize the safe and efficient decomposition of the outer ring of the bearing under the conditions that the operation space for decomposing the rear fulcrum bearing of the low-pressure turbine rotor of a certain type of aircraft engine is narrow (the width of the annular cavity is 19mm), the size of the process gap between the outer ring of the bearing and the flange is small (the radial distance between the deepest part of the process gap and the inner diameter of the outer ring of the bearing is 1.2mm), and the outer ring of the bearing is in large interference fit with the bearing mounting seat (the outer diameter of the outer ring of the bearing is phi 140mm, and the interference is-0.11 to-0.16 mm.

Drawings

Fig. 1 is a structural diagram of a disassembling device for an outer ring of a roller bearing in an annular cavity according to the invention. The device comprises a limiting cylinder 1, a screw 2, a jackscrew 3, a linkage ring 4, a blocking cover 5, a pulling claw 6, a pin 7 and a cotter pin 8. Wherein the linkage ring 4, the pulling claw 6, the pin 7 and the cotter pin 8 form a linkage ring component, which is shown in figure 2. When the linkage ring assembly is used, the linkage ring assembly is integrally arranged in an annular cavity for mounting a bearing, and the outer ring of the lower bearing 9 is disassembled by rotating the jackscrew 6 arranged on the linkage ring 4.

FIG. 2 is a structural view of a link ring assembly in a disassembling apparatus according to the present invention

Fig. 3 is a schematic view of a low pressure turbine rotor 10 of an engine embodying the present invention. The shaft of this type rotor is longer, and wherein bearing frame outer end face distance axle head is (1119.4mm), and the bearing frame and the axle that install roller bearing 9 outer lane adopt overall structure scheme, and bearing frame and axle constitute narrow annular chamber, and the annular chamber width is 19 mm. The fit value of the bearing 9 and the bearing seat is interference: -0.11mm to-0.16 mm.

Fig. 4 shows a cross-sectional view (right side view) of a low pressure turbine rotor 10 of an engine embodying the present invention. The radial maximum distance between the bottom of the technological notch of the bearing seat flange and the outer ring of the roller bearing 9 is 1 mm-1.2 mm, which is obviously smaller than the size of the conventional bearing decomposition technological notch.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings, which are referred to in fig. 1 to 4.

The device for decomposing the outer ring of the roller bearing in the annular cavity to complete the decomposition of the outer ring of the roller bearing of the low-pressure turbine rotor of the aircraft engine comprises the following steps:

step 1: and (3) installing the limiting spigot of the plug cover 5 to the outer end face of the bearing seat of the low-pressure turbine rotor 10 towards the annular cavity side, so that the plug cover 5 is attached to the outer end face of the bearing seat, and the axial positioning and the radial limiting of the plug cover 5 are completed.

Step 2: the threaded hole end of the pulling claw 6 faces the outer side of the annular cavity, the linkage ring assembly is arranged in the annular cavity between the bearing seat and the shaft of the low-pressure turbine rotor 10, and the linkage ring 4 is attached to the front end face of the blocking cover 5; and rotating the linkage ring assembly until the pulling claw 6 is aligned with the technological notch of the bearing flange.

And step 3: the limiting cylinder 1 is sleeved from the shaft end of the low-pressure turbine rotor 10. The limiting cylinder 1 is properly rotated to align and attach the 4 unthreaded holes on the limiting cylinder with the threaded holes of the 4 pulling claws 6 on the linkage ring assembly. The limiting cylinder 1 and the pulling claw 6 are connected and fastened through 4 screws 2.

And 4, step 4: and synchronously screwing the jackscrew 3 into the threaded hole on the linkage ring 4 until the jackscrew 3 is contacted with the plug cover 5. And continuously synchronously screwing the jackscrew 3 to enable the linkage ring assembly to axially move until the pulling claw 6 on the linkage ring assembly completely separates the outer ring of the roller bearing 9 from the bearing seat.

And 5: the outer ring of the roller bearing 9 is taken down from a roller bearing outer ring disassembling device in an annular cavity.

Claims (2)

1. A roller bearing outer ring decomposing device in an annular cavity comprises a limiting cylinder (1), a screw (2), a jackscrew (3), a linkage ring (4), a blanking cover (5), a pulling claw (6), a pin (7) and a cotter pin (8); the device is characterized in that the pulling claws (6) are uniformly hinged in the linkage ring (4) through pins (7) and cotter pins (8) to form a linkage ring assembly; when the linkage ring assembly pulling device works, the linkage ring assembly is integrally arranged in the annular cavity, the linkage ring assembly pulling claw (6) is inserted into the limiting cylinder (1), and the radial limiting of the pulling claw (6) is realized through the outer cylindrical surface of the limiting cylinder (1); screwing a jackscrew (3) into the linkage ring (4); the jackscrew (3) directly or indirectly supports against the end face of one side of the bearing seat far away from the annular cavity, and the synchronous screw-in jackscrew (3) drives the linkage ring (4) and the pulling claw (6) to drive the bearing outer ring to move axially, so that the bearing outer ring is separated from the bearing seat.

2. A method for disassembling an outer ring of a roller bearing in an annular cavity comprises the following steps:

step 1: mounting a limiting stop end of the plug cover (5) to the outer end face of the rotor bearing seat to enable the plug cover (5) to be attached to the outer end face of the bearing seat;

step 2: the non-threaded hole end of a pulling claw (6) of the linkage ring assembly faces the bearing seat and is installed in an annular cavity between the rotor bearing seat and the shaft, so that the end face of the linkage ring (4) is in contact with the blocking cover (5); the linkage ring assembly is rotated in the circumferential direction properly to finish the alignment of the pulling claw (6);

and step 3: enabling the limiting cylinder (1) to penetrate through a shaft of the rotor and be installed between the pulling claws of the linkage ring assembly; rotating the limiting cylinder (1) to align the unthreaded hole on the limiting cylinder with the threaded hole of the pulling claw (6) on the linkage ring assembly and attach the unthreaded hole to the end face of the pulling claw (6); the limiting cylinder (1) and the pulling claw (6) are connected and fastened through a screw (2);

and 4, step 4: synchronously screwing the jackscrew (3) into the threaded hole on the linkage ring (4) until the jackscrew (3) is contacted with the plug cover (5); the jackscrew (3) is continuously and synchronously screwed in until the outer ring of the roller bearing is completely separated from the bearing seat by a pulling claw (6) on the bearing disassembling device;

and 5: and taking down the outer ring of the roller bearing from the decomposition device of the outer ring of the roller bearing in the annular cavity.