Stop device for decomposition of low-pressure turbine of aero-engine and decomposition method

Abstract

The invention provides a stopping device for disassembling a low-pressure turbine of an aero-engine and a disassembling method. The stopping device comprises a mounting plate, a mandrel and a spline housing. The mandrel is arranged in the center of the mounting plate and connected with the mounting plate through a spline housing, and one end of the mandrel is provided with a bolt hole corresponding to an engine fan shaft bolt and used for fixing. And the outer edge of the mounting plate is connected with the mounting edge of the engine fan casing through bolts and nuts. In addition, a hanging ring is arranged on the mounting plate, and hoisting is convenient. The whole device is exquisite in structure and reliable in fixation, spline tooth matching is adopted, torque is evenly and reliably transmitted, and the defects that the decomposed torque is not easy to control and a large nut, a low-pressure turbine shaft and a low-pressure turbine are easily damaged due to the fact that a traditional double-nut back-to-back disassembling method or a method that a fan shaft is directly held tightly and then disassembled is adopted are overcome.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine low-pressure turbine rotor disassembly, and in particular to a stopping device and a disassembly method for the aircraft engine low-pressure turbine disassembly. Background Art

[0002] As a key load-bearing structural component of an aircraft engine, the low-pressure turbine rotor of an aircraft engine is composed of precise and expensive parts. During the disassembly process, improper operation can easily cause damage or scrapping of parts, which will directly affect the performance and service life of the aircraft engine and may even cause significant economic losses. Traditionally, for a certain type of three-rotor aircraft engine, its low-pressure turbine and fan shaft are connected using "Special Tr70×3" large spline nuts. During disassembly, the method of disassembly with double nuts facing each other or the method of directly holding the fan shaft and then disassembling have the problem that the disassembly torque is difficult to control and the large nut, low-pressure turbine shaft and low-pressure turbine are easily damaged. Summary of the invention

[0003] The purpose of the present invention is to provide a stopping device and a disassembly method for the low-pressure turbine of an aircraft engine, aiming to solve the problems in the prior art that the low-pressure rotor is easy to rotate, the disassembly torque is difficult to control, and the parts are easy to be damaged when the low-pressure turbine of an aircraft engine is disassembled.

[0004] The present invention is implemented by adopting the following technical scheme: a stopping device for disassembling the low-pressure turbine of an aircraft engine, comprising a mounting plate and a core shaft, the core shaft being arranged at the center of the mounting plate, a spline sleeve being arranged between the mounting plate and the core shaft, the mounting plate, the spline sleeve and the core shaft being fixedly connected by a bolt, the core shaft and the mounting plate being interference-connected by a cylindrical pin to prevent rotation, and the spline sleeve and the core shaft being matched by spline teeth to evenly and reliably transmit torque.

[0005] Furthermore, one end of the core shaft is provided with bolt holes corresponding to the twenty-four bolts on the engine fan shaft, which is used to place the bolt holes of the rotor stopping device core shaft into the twenty-four bolts on the engine fan shaft, and screw in the corresponding twenty-four nuts to achieve a fixed connection between the core shaft and the engine fan shaft.

[0006] Furthermore, the outer edge of the mounting plate is provided with holes corresponding to the six holes on the mounting side of the engine fan casing, and the mounting plate and the engine fan casing are fixedly connected by passing bolt 2 through the holes on the mounting plate and the mounting side of the engine fan casing and screwing in a nut.

[0007] Furthermore, a lifting ring is provided on the mounting plate, and the lifting ring is connected to the mounting plate through a cotter pin. Two lifting rings are provided and are symmetrically arranged relative to the core axis. The lifting ring is a universal rotating lifting ring.

[0008] A method for disassembling a low-pressure turbine of an aircraft engine comprises the following steps: S1. Use a gantry truck to move the rotor stopper to the front of the fan casing of the aircraft engine with the fairing removed; S2. Place the bolt holes of the mandrel of the rotor stopper into the twenty-four bolts of the engine fan shaft, and install the corresponding twenty-four nuts, and tighten them preliminarily; S3. Align the six holes on the outer edge of the mounting plate of the rotor stopper with the six holes on the mounting edge of the engine fan case, connect them with six bolts and nuts, and tighten them preliminarily; S4. Use the cross method to first tighten the twenty-four bolts and nuts connecting the engine fan shaft, and then tighten the six bolts and nuts connecting the fan casing mounting edge; S5. Use other anti-radial movement tools to assist in fixing the fan shaft. Use a special nut disassembly tool and torque amplifier to loosen the connecting nut between the low-pressure turbine and the fan shaft, and disassemble the low-pressure turbine from the fan shaft.

[0009] Furthermore, in step S2, when initially tightening the twenty-four nuts, manual tools are used for initial tightening.

[0010] Furthermore, in step S4, when the cross method is used to tighten the bolts and nuts, it is ensured that each bolt and nut is evenly stressed to achieve a specified tightening torque.

[0011] The stopping device and disassembly method for disassembling a low-pressure turbine of an aircraft engine described in the present invention have the following beneficial effects: The overall device has an exquisite structure and reliable fixation. It adopts inter-tooth coordination to evenly and reliably transmit torque, avoiding the disadvantages of using traditional double-nut back-to-back disassembly method or directly clamping the fan shaft and then disassembling. The disassembly torque is not easy to control and is easy to damage the large nut, low-pressure turbine shaft and low-pressure turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the embodiments of the present invention 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. The drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0013] Figure 1 A side cross-sectional view of a disassembled stopper device of a low-pressure turbine of an aircraft engine; Figure 2 It is a forward schematic diagram of a disassembled stop device of a low-pressure turbine of an aircraft engine; Figure 3is a schematic diagram of the state of the stopper device during the disassembly process; In the figure, 1-mounting plate, 2-spline sleeve, 3-core shaft, 4-bolt one, 5-lifting ring, 6-cotter pin, 7-bolt two, 8-nut, 9-cylindrical pin, 10-stop device, 11-fan casing, 12-fan, 13-low-pressure turbine. DETAILED DESCRIPTION

[0014] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0015] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. 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.

[0016] like Figure 1-3 As shown, a stopping device for disassembling a low-pressure turbine of an aircraft engine comprises a mounting plate 1 and a core shaft 3. The core shaft 3 is arranged at the center of the mounting plate 1. A spline sleeve 2 is arranged between the mounting plate 1 and the core shaft 3. The mounting plate 1, the spline sleeve 2 and the core shaft 3 are fixedly connected by bolts 4. The core shaft 3 and the mounting plate 1 are interference-connected by cylindrical pins 9 to prevent rotation. The spline sleeve 2 and the core shaft 3 are matched by the spline teeth to evenly and reliably transmit torque.

[0017] One end of the core shaft 3 is provided with bolt holes corresponding to the twenty-four bolts on the engine fan shaft. The bolt holes of the core shaft 3 of the rotor stopping device 10 are placed on the twenty-four bolts on the engine fan shaft, and the corresponding twenty-four nuts are screwed in to achieve a fixed connection between the core shaft 3 and the engine fan shaft.

[0018] The outer edge of the mounting plate 1 is provided with holes corresponding to the six holes on the mounting side of the engine fan casing. The mounting plate 1 and the engine fan casing 11 are fixedly connected by passing the bolt 7 through the holes on the mounting side of the mounting plate 1 and the engine fan casing 11 and screwing in the nut 8.

[0019] The mounting plate 1 is also provided with a lifting ring 5, which is connected to the mounting plate 1 via a cotter pin 6. Two lifting rings 5 ​​are provided and are symmetrically arranged relative to the core shaft 3. The lifting ring 5 is a universal rotating lifting ring.

[0020] A stopping device for disassembling a low-pressure turbine of an aircraft engine is used, and the steps of disassembling a low-pressure turbine of an aircraft engine are as follows: S1. After the hook of the gantry truck is connected and fixed with the lifting ring 5, the gantry truck is operated to move slowly to move the rotor stopper 10 to the front of the fan casing 11 of the aircraft engine where the fan 12 leaking out of the fairing cover is disassembled.

[0021] S2. Place the bolt holes of the core shaft 3 of the rotor stopper 10 into the twenty-four bolts of the engine fan shaft, and assemble the corresponding twenty-four nuts, and tighten them preliminarily by hand.

[0022] S3. Align the six holes on the outer edge of the mounting plate 1 of the rotor stopper with the six holes on the mounting side of the engine fan case 11, and use six bolts 7 to pass through the bolt holes on the mounting plate 1 and the mounting side of the fan case 11, connect them with six nuts 8, and tighten them preliminarily by hand.

[0023] S4. Use the cross method to first tighten the twenty-four bolts and nuts connecting the engine fan shaft, and then tighten the six bolts 7 and nuts 8 connecting the installation edge of the fan casing 11.

[0024] S5. Use other anti-radial movement tools to assist in fixing the fan shaft, use a special nut disassembly tool and a torque amplifier, loosen the connecting nut between the low-pressure turbine 13 and the fan shaft, and disassemble the low-pressure turbine 13 from the fan shaft.

[0025] The above embodiments describe the basic principles and main features of the present invention and the advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments, and the above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the changes and modifications made by those skilled in the art shall be within the scope of protection of the appended claims of the present invention without departing from the spirit and scope of the present invention.

Claims

1. A stopping device for decomposing a low-pressure turbine of an aircraft engine, characterized in that: The invention comprises a mounting plate (1) and a mandrel (3), wherein the mandrel (3) is arranged at the center of the mounting plate (1), a spline sleeve (2) is arranged between the mounting plate (1) and the mandrel (3), the mounting plate (1), the spline sleeve (2) and the mandrel (3) are fixedly connected by a bolt (4), the mandrel (3) and the mounting plate (1) are interference-connected by a cylindrical pin (9) to prevent rotation, and the spline sleeve (2) and the mandrel (3) cooperate with each other through the spline teeth to evenly and reliably transmit torque.

2. The stopping device for disassembling a low-pressure turbine of an aircraft engine according to claim 1, characterized in that: One end of the core shaft (3) is provided with bolt holes corresponding to the twenty-four bolts on the engine fan shaft, and is used for inserting the bolt holes of the rotor stopper core shaft (3) into the twenty-four bolts on the engine fan shaft, and screwing in the corresponding twenty-four nuts to achieve a fixed connection between the core shaft (3) and the engine fan shaft.

3. The stopping device for disassembling a low-pressure turbine of an aircraft engine according to claim 1, characterized in that: The outer edge of the mounting plate (1) is provided with holes corresponding to the six holes on the mounting edge of the engine fan casing, and the mounting plate (1) and the engine fan casing are fixedly connected by passing bolt 2 (7) through the holes on the mounting plate (1) and the mounting edge of the engine fan casing and screwing in a nut (8).

4. The stopping device for disassembling a low-pressure turbine of an aircraft engine according to claim 1, characterized in that: The mounting plate (1) is also provided with a lifting ring (5), the lifting ring (5) being connected to the mounting plate (1) via a split pin (6), two lifting rings (5) being provided and symmetrically arranged relative to the core shaft (3), and the lifting ring (5) is a universal rotating lifting ring.

5. A method for disassembling a low-pressure turbine of an aircraft engine, implemented by using a stopping device for disassembling a low-pressure turbine of an aircraft engine as claimed in any one of claims 1 to 4, characterized in that: The following steps are involved: S1. Use a gantry truck to move the rotor stopper to the front of the fan casing of the aircraft engine with the fairing removed; S2. Place the bolt holes of the mandrel (3) of the rotor stopper into the twenty-four bolts of the engine fan shaft, and install the corresponding twenty-four nuts, and tighten them preliminarily; S3. Align the six holes on the outer edge of the mounting plate (1) of the rotor stopper with the six holes on the mounting edge of the engine fan case, connect them with six bolts and nuts, and tighten them preliminarily; S4. Use the cross method to first tighten the twenty-four bolts and nuts connecting the engine fan shaft, and then tighten the six bolts and nuts connecting the fan casing mounting edge; S5. Use other anti-radial movement tools to assist in fixing the fan shaft. Use a special nut disassembly tool and torque amplifier to loosen the connecting nut between the low-pressure turbine and the fan shaft, and disassemble the low-pressure turbine from the fan shaft.

6. The method for disassembling a low-pressure turbine of an aircraft engine according to claim 5, characterized in that: In the step S2, when the twenty-four nuts are initially tightened, a manual tool is used for the initial tightening.

7. The method for disassembling a low-pressure turbine of an aircraft engine according to claim 5, characterized in that: In step S4, when the bolts and nuts are tightened by the cross method, it is ensured that each bolt and nut is evenly stressed to achieve the specified tightening torque.

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