CN215035125U - Hydraulic tensioning device for assembling rotor assembly of aero-engine compressor - Google Patents
Hydraulic tensioning device for assembling rotor assembly of aero-engine compressor Download PDFInfo
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- CN215035125U CN215035125U CN202121129020.0U CN202121129020U CN215035125U CN 215035125 U CN215035125 U CN 215035125U CN 202121129020 U CN202121129020 U CN 202121129020U CN 215035125 U CN215035125 U CN 215035125U
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Abstract
The utility model provides a hydraulic tensioning device for assembling an aircraft engine compressor rotor assembly, which comprises a top ring, a tensioning cylinder and a supporting plate; the upper end of the tensioning cylinder is provided with an opening and is provided with internal threads, the side wall of the tensioning cylinder is provided with at least two windows, and the lower end of the tensioning cylinder is sealed; a support plate is inserted into the tensioning cylinder, and the support plate extends out and is clamped in the window; the top ring is sleeved on the side wall of the tensioning cylinder and is fixedly connected with the supporting plate; when the supporting plate is tightly attached to the upper edge of the window, the upper end of the top ring exceeds the upper end plane of the tensioning barrel. The tensioning device is of an integral structure formed by permanent connection of parts, and is convenient to produce, use and maintain.
Description
Technical Field
The utility model relates to a hydraulic pressure straining device of assembly of aeroengine compressor rotor subassembly belongs to the straining device field.
Background
The assembly of the aircraft engine is a later process in the manufacturing process, occupies a very 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 assembler using a special or general purpose tooling fixture. Whether the design of the tool clamp for assembling the aero-engine is scientific and reasonable directly influences the assembly efficiency and the safety of the engine and also concerns the performance, the service life and the working reliability of the engine. Due to the fact that the structures and the overall dimensions of various engines are different, working conditions, technical requirements and manufacturing accuracy of various components, parts and units are different, and the assembling of the engines is often required to be 'customized' tool fixtures.
The process of installing the compressor rotor assembly into the intermediate casing unit body belongs to the key process of assembling the core unit body of the aero-engine, and has the characteristics of large assembling interference magnitude, long matching surface, large rotor size and the like. At present, the installation of a compressor rotor assembly is generally assembled by adopting a temperature difference method, namely, a front journal of a compressor is frozen in liquid nitrogen and kept for a period of time and then quickly falls into a driving bevel gear hub of an intermediary casing unit body, and a load in the opposite direction is applied between the driving bevel gear and the front journal of the compressor by utilizing a screw jack principle and kept for a period of time until the front journal of the compressor recovers to the room temperature.
During the assembly by the temperature difference method, in order to ensure that the rotor assembly of the compressor is installed in place, the load in the opposite direction is applied between the front journal of the compressor and the driving bevel gear in the shortest time possible.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve above-mentioned problem and provide a hydraulic pressure straining device of aeroengine compressor rotor subassembly assembly, its aim at: the tensioning device is of an integral structure formed by permanent connection of parts, and is convenient to produce, use and maintain.
The utility model provides a hydraulic tensioning device assembled by a rotor assembly of an aircraft engine compressor, which comprises a top ring, a tensioning cylinder, a supporting plate and a linear driving device; the upper end of the tensioning cylinder is provided with an opening and is provided with internal threads, the side wall of the tensioning cylinder is provided with at least two windows, and the lower end of the tensioning cylinder is sealed; a support plate is inserted into the tensioning cylinder, and the support plate extends out and is clamped in the window; the top ring is sleeved on the side wall of the tensioning cylinder and is fixedly connected with the supporting plate; when the supporting plate is tightly attached to the upper edge of the window, the upper end of the top ring exceeds the upper end plane of the tensioning barrel; and a linear driving device is arranged between the supporting plate and the lower end surface of the tensioning cylinder.
Further, in order to allow the linear actuator to be placed into the take-up cylinder through the window, the window is sized to allow the linear actuator to be placed into the take-up cylinder.
Further, in order to guide and place the linear driving device through the placement groove, the bottom plane of the tensioning cylinder is provided with a U-shaped placement groove which does not penetrate through the bottom plane of the tensioning cylinder, and the U-shaped opening of the placement groove intersects with one of the windows.
Further, in order to enable the linear driving device to be placed in the window and ensure the strength of the tensioning cylinder, the width of the window is the same as that of the placing groove.
Furthermore, in order to position the hydraulic cylinder, the hydraulic cylinder is arranged in the middle of the tensioning cylinder, the supporting plate and the tensioning cylinder are stressed in a balanced manner, and the circle center of the U-shaped arc part of the placing groove is superposed with the axis of the tensioning cylinder.
Furthermore, in order to enable the supporting plate to be smoothly placed into the window and enable the top ring connected with the supporting plate to be stressed uniformly, two windows are arranged and are arranged at symmetrical positions of the side wall of the tensioning cylinder.
Further, in order to inject the apical ring in an within range, can conveniently put into a tensioning barrel with the pneumatic cylinder, it is provided with the screens boss to encircle on the lateral wall on the upper portion of tensioning barrel, the apical ring sets up on the lateral wall of the tensioning barrel of position on the screens boss.
Furthermore, in order to allow a simple and rapid adjustment of the pressure of the linear drive, the linear drive is a hydraulic cylinder.
The utility model has the advantages that:
1. the tensioning device effectively solves the problems of long preparation period, difficult installation and disassembly, high labor intensity and the like of the traditional process equipment when a certain type of aero-engine compressor rotor assembly is installed in scientific research and production practices, can greatly reduce the labor intensity by using the tensioning device, obviously reduces the operation risk, ensures that the power of the rotor is assembled at one time to be nearly 100 percent, is simple and reliable, has the weight of 15 to 40 percent of that of the traditional process equipment, can averagely shorten the production period by using the tensioning device for assembling at one time for 0.3 day and reduce the work load for about 1 person per day, and is convenient to produce, use and maintain because the device forms an integral structure through the permanent connection of parts.
2. The size of the window is enough to enable the linear driving device to be placed into the tensioning cylinder, and the linear driving device can be placed into the tensioning cylinder through the window.
3. The bottom plane of the tensioning cylinder is provided with a U-shaped placing groove which does not penetrate through the bottom plane of the tensioning cylinder, a U-shaped opening of the placing groove is intersected with one of the windows, and the linear driving device can be guided through the placing groove and placed.
4. The width of the window is the same as that of the placing groove, so that the linear driving device can be placed in the window, and the strength of the tensioning barrel can be guaranteed.
5. The circle center of the U-shaped arc part of the placing groove is superposed with the axis of the tensioning cylinder, and the position of the linear driving device is positioned, so that the linear driving device is arranged in the middle of the tensioning cylinder, and the supporting plate and the tensioning cylinder are stressed in a balanced manner.
6. The window sets up two, and sets up the symmetrical position of the lateral wall of a tensioning barrel makes the backup pad can put into the window smoothly, and makes the apical ring atress that is connected with the backup pad even.
7. The utility model discloses a take-up device, including a tensioning section of thick bamboo, set up the top ring on the lateral wall of the tensioning section of thick bamboo of the upper portion of tensioning section of thick bamboo, set up the clamping boss on the lateral wall of the tensioning section of thick bamboo of position on the clamping boss, inject the top ring in an within range, can conveniently put into the tensioning section of thick bamboo with sharp drive arrangement.
8. The linear driving device is a hydraulic cylinder, and the pressure of the linear driving device can be simply and quickly adjusted.
Drawings
Fig. 1 is a schematic view of the present invention when no linear drive is included.
Fig. 2 is a schematic view of the installation connection when the present invention does not include a linear driving device.
Fig. 3 is a schematic view of the working state of the present invention.
In the figure: 1. a top ring; 2. a tensioning cylinder; 2-1, a window; 2-2, placing a groove; 2-3, a clamping boss; 3. A support plate; 4. a hydraulic cylinder; 5. and a front shaft neck of the compressor.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention will be further explained with reference to the accompanying drawings.
The hydraulic tensioning device for assembling the rotor assembly of the compressor of the aircraft engine shown in the figures 1 to 3 comprises a top ring 1, a tensioning cylinder 2, a supporting plate 3 and a linear driving device;
the upper end of the tensioning cylinder 2 is provided with an opening and is provided with internal threads, the side wall of the tensioning cylinder 2 is at least provided with two windows 2-1, and the lower end of the tensioning cylinder 2 is sealed;
a support plate 3 is inserted into the tensioning cylinder 2, and the support plate 3 extends out and is clamped in the window 2-1;
the top ring 1 is sleeved on the side wall of the tensioning cylinder 2 and is welded with the support plate 3;
when the supporting plate 3 is tightly attached to the upper edge of the window 2-1, the upper end of the top ring 1 exceeds the upper end plane of the tensioning cylinder 2;
a linear driving device is arranged between the supporting plate 3 and the lower end face of the tensioning cylinder 2.
Based on the above embodiment, the size of the window 2-1 is sufficient to allow the linear driving means to be placed in the tensioning tube.
Based on the above embodiment, the bottom plane of the tightening barrel 2 is provided with the U-shaped placing groove 2-2 which does not penetrate through the bottom plane of the tightening barrel 2, and the U-shaped opening of the placing groove 2-2 intersects with one of the windows 2-1.
Based on the above embodiment, the width of the window 2-1 is the same as the width of the placement groove 2-2.
Based on the above embodiment, the center of the circular arc portion of the U shape of the placement groove 2-2 coincides with the axis of the tension tube 2.
Based on the above embodiment, the two windows 2-1 are provided, and are provided at symmetrical positions on the side wall of the tensioning barrel 2.
Based on the above embodiment, the outer side wall of the upper part of the tensioning cylinder 2 is provided with the clamping bosses 2-3 in a surrounding manner; the top ring 1 is arranged on the side wall of the tensioning cylinder 2 above the clamping bosses 2-3.
Based on the above embodiment, the linear driving device is the hydraulic cylinder 4.
The operation of tensioning and maintaining the tensioning force after the tensioning device is adopted to fall into the central driving bevel gear hub of the intermediate casing unit body in a certain type of aero-engine compressor rotor assembly by utilizing the principle of a temperature difference method comprises the following steps:
step 1: the tensioning cylinder 2 of the tensioning device is screwed into the front journal 5 of the compressor by hand.
Step 2: the hydraulic cylinder 4 is pushed in from the bottom U-shaped groove of the tensioning cylinder 2.
And step 3: and operating the hydraulic pump to drive the hydraulic cylinder 4 to act, and observing the indicating value of a pressure gauge on the hydraulic pump at the same time until the tension converted by the indicating value is equal to the preset tension.
And 4, step 4: and keeping the output pressure of the hydraulic pump for 60-180 min according to the environment temperature and the actual working condition.
And 5: and opening the switch valve of the hydraulic pump, discharging the pressure in the hydraulic cylinder 4 and taking out the hydraulic cylinder 4.
Step 6: the tensioning device is screwed out of the compressor front journal 5.
The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. The utility model provides a hydraulic pressure straining device of aeroengine compressor rotor subassembly assembly which characterized in that:
comprises a top ring (1), a tensioning cylinder (2), a supporting plate (3) and a linear driving device;
the upper end of the tensioning cylinder (2) is opened and is provided with internal threads, the side wall of the tensioning cylinder (2) is at least provided with two windows (2-1), and the lower end of the tensioning cylinder (2) is sealed;
a support plate (3) is inserted into the tensioning cylinder (2), and the support plate (3) extends out and is clamped in the window (2-1);
the top ring (1) is sleeved on the side wall of the tensioning cylinder (2) and is fixedly connected with the supporting plate (3);
when the supporting plate (3) is tightly attached to the upper edge of the window (2-1), the upper end of the top ring (1) exceeds the upper end plane of the tensioning cylinder (2);
and a linear driving device is arranged between the support plate (3) and the lower end surface of the tensioning cylinder (2).
2. The hydraulic tensioning device for assembling an aircraft engine compressor rotor assembly according to claim 1, characterized in that: the window (2-1) is of a size sufficient to allow the linear drive to be placed into the tensioning barrel.
3. The hydraulic tensioning device for assembling an aircraft engine compressor rotor assembly according to claim 2, characterized in that: the bottom plane of the tensioning cylinder (2) is provided with a U-shaped placing groove (2-2) which does not penetrate through the bottom plane of the tensioning cylinder (2), and a U-shaped opening of the placing groove (2-2) is intersected with one of the windows (2-1).
4. A hydraulic tensioning device for the assembly of an aircraft engine compressor rotor assembly according to claim 3, characterised in that: the width of the window (2-1) is the same as that of the placing groove (2-2).
5. A hydraulic tensioning device for the assembly of an aircraft engine compressor rotor assembly according to claim 3, characterised in that: the circle center of the U-shaped arc part of the placing groove (2-2) is superposed with the axis of the tensioning cylinder (2).
6. The hydraulic tensioning device for assembling an aircraft engine compressor rotor assembly according to claim 1, characterized in that: the two windows (2-1) are arranged at symmetrical positions on the side wall of the tensioning cylinder (2).
7. The hydraulic tensioning device for assembling an aircraft engine compressor rotor assembly according to claim 1, characterized in that: a clamping boss (2-3) is arranged on the outer side wall of the upper part of the tensioning cylinder (2) in a surrounding manner; the top ring (1) is arranged on the side wall of the tensioning cylinder (2) above the clamping boss (2-3).
8. The hydraulic tensioning device for assembling an aircraft engine compressor rotor assembly according to claim 1, characterized in that: the linear driving device is a hydraulic cylinder (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121129020.0U CN215035125U (en) | 2021-05-25 | 2021-05-25 | Hydraulic tensioning device for assembling rotor assembly of aero-engine compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121129020.0U CN215035125U (en) | 2021-05-25 | 2021-05-25 | Hydraulic tensioning device for assembling rotor assembly of aero-engine compressor |
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| CN215035125U true CN215035125U (en) | 2021-12-07 |
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| CN202121129020.0U Active CN215035125U (en) | 2021-05-25 | 2021-05-25 | Hydraulic tensioning device for assembling rotor assembly of aero-engine compressor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115431013A (en) * | 2022-08-15 | 2022-12-06 | 北京动力机械研究所 | Turbofan engine case press-mounting device |
-
2021
- 2021-05-25 CN CN202121129020.0U patent/CN215035125U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115431013A (en) * | 2022-08-15 | 2022-12-06 | 北京动力机械研究所 | Turbofan engine case press-mounting device |
| CN115431013B (en) * | 2022-08-15 | 2024-04-09 | 北京动力机械研究所 | Turbofan engine casing press-fitting device |
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