CN111946460A - Guiding device for assembling fan assembly of aircraft engine and assembling method - Google Patents
Guiding device for assembling fan assembly of aircraft engine and assembling method Download PDFInfo
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- CN111946460A CN111946460A CN202010796685.0A CN202010796685A CN111946460A CN 111946460 A CN111946460 A CN 111946460A CN 202010796685 A CN202010796685 A CN 202010796685A CN 111946460 A CN111946460 A CN 111946460A
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- assembly
- guide rod
- guide
- fan assembly
- core machine
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
- B23P19/10—Aligning parts to be fitted together
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C1/00—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles
- B66C1/10—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
Abstract
The invention discloses a guide device and an assembly method for assembling an aircraft engine fan assembly, belongs to the technical field of engine assembly, and can effectively reduce the problem of damage caused by collision of a fulcrum graphite piece in the assembly process of the aircraft engine fan assembly. The guide device comprises a guide rod, a positioning ring and a plurality of connecting pieces, one end of the guide rod is a hoisting end, the other end of the guide rod is a guide end, the positioning ring is coaxially arranged at one end of the hoisting end of the guide rod, the connecting pieces are distributed at intervals along the circumferential direction of the positioning ring, one end of each connecting piece is connected with the positioning ring, and the other end of each connecting piece is connected with the guide rod. The invention can play a role in guiding and installing through the guide part of the guide rod of the fan assembly in the assembling process of the fan assembly, thereby effectively reducing the problem that the fulcrum graphite piece is damaged in the lowering process; meanwhile, the convenience and the efficiency of assembling the fan assembly can be effectively improved, and the consumption of spare parts is reduced.
Description
Technical Field
The invention relates to the technical field of aircraft engine assembly, in particular to a guide device and an assembly method for assembling an aircraft engine fan assembly.
Background
The assembly of aircraft engines is an important part of aircraft engine maintenance. In the process of assembling the fan assembly of the turbofan engine, a rolling rod or a fulcrum runway of a fulcrum bearing assembly on the fan assembly is easy to rub against a fulcrum graphite piece on a core machine, and the structural strength of the fulcrum graphite piece is low, so that the fulcrum graphite piece is easy to be damaged, the contact type sealing device at the fulcrum is caused to lose efficacy, the lubricating oil leakage is increased, and the lubricating oil consumption of the engine is increased. Meanwhile, the damaged fulcrum graphite piece can fall into the lubricating oil system, so that foreign matters appear in the lubricating oil system, and even the fulcrum bearing can be damaged and failed, thereby causing serious consequences. The fulcrum graphite piece damages to cause the rework of the fulcrum supporting component, which not only causes the additional consumption of spare parts, but also wastes human resources, further influences the assembly quality of the engine and restricts the assembly progress of the engine.
Disclosure of Invention
The invention solves the technical problem of providing a guide device for assembling an aircraft engine fan assembly, which can effectively reduce the damage of the fulcrum graphite piece caused by collision in the assembly process of the aircraft engine fan assembly.
The technical scheme adopted by the invention for solving the technical problems is as follows: the correcting device is used for assembling the fan assembly and the core machine, the fan assembly and the core machine are assembled through the matching of a fulcrum graphite piece arranged on the core machine and a fulcrum bearing assembly arranged on the fan assembly, the correcting device comprises a guide rod, a positioning ring and a plurality of connecting pieces, one end of the guide rod is a hoisting end, the other end of the guide rod is a guide end, the positioning ring is coaxially arranged at one end of the hoisting end of the guide rod, the connecting pieces are distributed at intervals along the circumferential direction of the positioning ring, one end of each connecting piece is connected with the positioning ring, and the other end of each connecting piece is connected with the guide rod; a matching ring surface used for being matched with the core machine is formed on one side of the positioning ring facing the guide end, and a plurality of connecting holes used for being connected with the core machine are arranged on the positioning ring at intervals along the circumferential direction of the positioning ring; the guide end of the guide rod can penetrate through the central through hole of the core machine and penetrate out of the end, matched with the fan assembly, of the core machine, and the penetrating part forms a guide part used for being matched with the central hole of the fulcrum bearing assembly on the fan assembly in an inserting mode.
Further, the method comprises the following steps: an annular boss structure matched with the corresponding limiting structure in the core machine is formed in the middle of the guide rod, and the diameter of the annular boss structure is larger than that of other parts of the guide rod.
Further, the method comprises the following steps: the connecting piece is obliquely arranged relative to the axis of the guide rod, and the extending direction of the connecting piece from the end connected with the guide rod to the end connected with the positioning ring is obliquely arranged towards the direction of the guide end of the guide rod.
Further, the method comprises the following steps: all the connecting pieces are distributed at equal angle intervals along the circumferential direction of the positioning ring.
Further, the method comprises the following steps: the connecting piece is provided with six to twelve.
Further, the method comprises the following steps: the connecting piece is provided with ten.
Further, the method comprises the following steps: and a hoisting ring is arranged at the hoisting end.
Further, the method comprises the following steps: the guide portion is detachable.
Further, the method comprises the following steps: the guide part has an adjustment amount of 0-4mm in the axial direction of the guide rod.
In addition, the invention also provides an aircraft engine fan assembly assembling method, and the guide device for assembling the aircraft engine fan assembly, which is provided by the invention, comprises the following steps:
s1, fixedly mounting the assembled and qualified core machine on a turnover assembly vehicle, and enabling one end of the core machine, which is required to be in fit connection with the positioning ring, to be vertically upward through the turnover assembly vehicle;
s2, hoisting and guiding device: hoisting the guide device from the hoisting end by using a lifting appliance, enabling the guide end of the guide rod to penetrate through the central through hole of the core machine from top to bottom and penetrate out of one end, matched with the fan assembly, of the core machine, and then connecting and fixing the positioning ring and the core machine through the connecting hole by using a connecting piece;
s3, turning over the assembly vehicle to enable the guide end of the guide rod to be vertically upward;
s4, hoisting the assembled fan assembly and detecting the qualified fan assembly: hoisting the fan assembly by using a lifting appliance, enabling the fulcrum bearing assembly on the fan assembly to be positioned right above the guide end of the guide rod, and then lowering the fan assembly to enable the central hole of the fulcrum bearing assembly on the fan assembly to be sleeved into the guide part from the guide end of the guide rod until the fulcrum bearing assembly is matched with the fulcrum graphite piece in place;
s5, rotating the fan assembly to align the fan assembly with the anti-error hole arranged on the core machine, and then connecting and installing the fan assembly with the core machine;
s6, turning the assembly vehicle to enable the hoisting end of the guide rod to be vertically upward, then detaching the connecting piece for connecting the positioning ring and the core machine, and finally taking out the guide device.
The invention has the beneficial effects that:
1) the guide device is used for assembly, the guide part of the guide rod can play a role in guiding and mounting in the assembly process of the fan assembly, and the problem that the fulcrum graphite piece is damaged in the lowering process can be effectively solved; meanwhile, the convenience and the efficiency of assembling the fan assembly can be effectively improved, and the consumption of spare parts is reduced.
2) The guide part is arranged to be a detachable structure; and further setting the axial direction of the adjusting device to have an adjusting amount of 0-4 mm; can be more effectively adapted to the dimensions of different engine fan assemblies.
3) Through setting up annular boss structure, can be by the spacing structure cooperation that this annular boss structure corresponds in with the core built-in to play the better radial, axial limiting displacement to the guide bar, and then improve the position accuracy of guide bar installation back in the core built-in, improve the direction assembly precision to the fan sub-assembly.
Drawings
FIG. 1 is a perspective view of a pilot device according to the present invention;
FIG. 2 is a front view of FIG. 1;
FIG. 3 is a top view of FIG. 1;
FIG. 4 is a front view of the present invention polarization device during assembly of the fan assembly with the core engine;
FIG. 5 is a perspective view of FIG. 4 at a first angle;
FIG. 6 is a perspective view of FIG. 4 at a second angle;
labeled as: the fan assembly comprises a fan assembly 1, a core machine 2, a fulcrum graphite piece 3, a fulcrum bearing assembly 4, a central hole 41, a pilot device 5, a guide rod 100, a positioning ring 200, a connecting piece 300, a hoisting end 101, a guide end 102, a guide part 103, an annular boss structure 104, a hanging ring 105, a matching annular surface 201 and a connecting hole 202.
Detailed Description
The invention is further described with reference to the following figures and detailed description. It should be noted that, if directional indications are used in the present invention, such as terms of directions and orientations of up, down, left, right, front and back, the terms are used to facilitate description of relative positional relationship between members, and an absolute position that is not a positional relationship between related members and members is specifically used only to explain a relative positional relationship between members and a motion situation, etc. in a specific posture, if the specific posture is changed, the directional indication is changed accordingly. In addition, when the terms "a", "an", and the like refer to a specific number, two or more specific numbers may be used, and the specific number may be set according to actual needs of those skilled in the art.
The invention relates to a guide device for assembling a fan assembly of an aircraft engine, wherein the guide device 5 is used as an auxiliary tool for assembling the fan assembly 1 and a core machine 2, the fan assembly 1 and the core machine 2 are assembled by matching a fulcrum graphite piece 3 arranged on the core machine 2 with a fulcrum bearing assembly 4 arranged on the fan assembly 1, the guide device 5 comprises a guide rod 100, a positioning ring 200 and a plurality of connecting pieces 300, one end of the guide rod 100 is a hoisting end 101, the other end of the guide rod 100 is a guiding end 102, the positioning ring 200 is coaxially arranged at one end of the hoisting end 101 of the guide rod 100, the connecting pieces 300 are distributed at intervals along the circumferential direction of the positioning ring 200, one end of each connecting piece 300 is connected with the positioning ring 200, and the other end of each connecting piece 300 is connected with the guide rod 100; a matching ring surface 201 for matching with the core machine 2 is formed on one side of the positioning ring 200 facing the guide end 102, and a plurality of connecting holes 202 for connecting with the core machine 2 are arranged on the positioning ring 200 at intervals along the circumferential direction; the guide end 102 of the guide rod 100 is capable of passing through the central through hole of the core machine 2 and out of the end of the core machine 2 that mates with the fan assembly 1, and the portion that passes out forms a guide 103 for mating with the central hole 41 of the fulcrum bearing assembly 4 on the fan assembly 1.
When in use, the guide end 102 of the guide rod 100 penetrates through one end of the central through hole of the core machine 2, penetrates out of the other end and then further extends to form a guide part 103 with a certain length; the guide part 103 is used for being inserted into the central hole 41 of the fulcrum bearing assembly 4 on the fan assembly 1 in the subsequent process of assembling the fan assembly 1, so that the fan assembly 1 is guided and assembled, and the condition that the fulcrum bearing assembly 4 and the fulcrum graphite piece 3 are impacted and damaged due to shaking or misalignment in the installation process of the fan assembly 1 is reduced; thereby improving the installation quality and the installation convenience. Without loss of generality, the corresponding portion of the guide portion 103 should be sized to fit within the central bore 41 of the fulcrum bearing assembly 4 to ensure a cooperative guiding effect with the central bore 41 of the fulcrum bearing assembly 4.
More specifically, the guide portion 103 may be further detachably provided in the present invention. In this way, the size adaptation to different engine fan assemblies 1 can be achieved by replacing the guide members 103. Further, the guide portion 103 may be provided with an adjustment amount of 0 to 4mm in the axial direction of the guide bar 100; specifically, the adjustment can be achieved by a screw connection structure, that is, the guide part 103 is mounted on the guide rod 100 by a screw connection, and the adjustment of the guide part 103 is achieved by controlling the size of the screw connection.
In addition, the guide rod 100 of the present invention needs to pass through the central through hole inside the core machine 2, and in order to improve the positioning accuracy after the guide rod 100 passes through, the diameter of the corresponding portion of the guide rod 100 of the present invention may be set to match the diameter of the corresponding section of the central through hole inside the core machine, and on the premise that the installation can be performed smoothly, the fit clearance between the guide rod 100 and the central through hole is appropriately reduced, thereby improving the positioning accuracy after the guide rod 100 is installed. In the present invention, a ring-shaped boss structure 104 for engaging with a corresponding stopper structure in the core machine 2 may be further formed at the middle of the guide bar 100, and the diameter of the ring-shaped boss structure 104 is larger than that of the rest of the guide bar 100. Namely, the annular boss structure 104 is matched with the limit structure at the corresponding position in the core machine 2 in a more accurate positioning way; the corresponding limiting structure in the core machine 2 refers to a structure which is originally present in the core machine 2 and has higher structural strength and is suitable for limiting the guide rod 100; the skilled person can select a suitable part as the limit structure according to the structure of the corresponding central through hole in the core machine 2; the following configurations within the core machine 2 may be selected but are not limited to: the inner cylindrical surface of the front journal of the core machine and the inner hole surface of a fulcrum bearing used for matching the low-pressure turbine and the high-pressure turbine inside the core machine. In addition, in the case of providing the annular boss structure 104, the axial limit function of the guide rod 100 can also be realized through a step surface formed in the axial direction by the annular boss structure 104 and a corresponding limit structure in a corresponding central through hole in the core machine 2, which plays a role in accurately controlling the insertion depth of the limit rod 100.
The positioning ring 200 of the present invention is used for matching and connecting with the core machine 2, so as to fixedly connect the positioning ring 200 with the core machine 2, and further fix the guide rod 100; specifically, a matching ring surface 201 for matching with the core machine 2 is formed on one side of the positioning ring 200 facing the guiding end 102, and a plurality of connecting holes 202 for connecting with the core machine 2 are arranged on the positioning ring 200 at intervals along the circumferential direction; the retaining ring 200 may be fixedly mounted to the core machine 2 by attachment holes 202, such as by screws or bolts. Of course, the size of the positioning ring 200, without loss of generality, should be consistent with the size of the corresponding mating portion on the core machine 2 to ensure an effective mating connection therebetween; it should also be ensured that the positioning ring 200 is fitted to the core machine 2 with its guide rod 100 just coaxially fitted to the central through hole inside the core machine 2.
More specifically, in order to enable the positioning ring 200 to be coupled with the core machine 2 more properly, the connecting member 200 of the present invention is preferably disposed to be inclined with respect to the axis of the guide rod 100, and the extending direction of the connecting member 300 from the end connected with the guide rod 100 to the end connected with the positioning ring 200 is inclined toward the guide end 102 of the guide rod 100. This reduces interference of the connector 300 during installation of the retaining ring 200.
More specifically, the connecting members 300 of the present invention may be further disposed at equal angular intervals along the circumferential direction of the positioning ring 200. This improves the force distribution of the respective connectors 300. Specifically, the number of the connecting members 300 may be preferably set to six to twelve; specifically, as ten, the angular interval between the respective adjacent two of the connecting members 300 is set to 36 °.
In addition, in order to facilitate the hoisting of the whole guiding device, a hoisting ring 105 can be further arranged at the hoisting end 101 in the invention.
The assembly method of the aircraft engine fan assembly adopts the guide device 5 for the assembly of the aircraft engine fan assembly, and specifically comprises the following steps:
s1, fixedly mounting the assembled and qualified core machine 2 on a turnover assembly vehicle, and enabling one end of the core machine 2, which is required to be in fit connection with the positioning ring 200, to be vertically upward through the turnover assembly vehicle; the overturning assembly vehicle is a common assembly tool with an up-down overturning function; the assembly vehicle can be overturned up and down to realize the transfer of different parts of the assembly workpiece.
S2, hoisting and guiding device 5: lifting the pilot device 5 from the lifting end 101 by using a lifting appliance, enabling the guide end 102 of the guide rod 100 to penetrate through the central through hole of the core machine 2 from top to bottom and penetrate out of the end, matched with the fan assembly 1, of the core machine 2, and then connecting and fixing the positioning ring 200 and the core machine 2 through the connecting hole 202 through a connecting piece; of course, during the process of hoisting the pilot device 5, the guide rod 100 should be slowly inserted, and the collision should be avoided as much as possible; in addition, a connecting member such as a bolt or a screw may be used for connecting and fixing the positioning ring 200 to the core machine 2.
S3, overturning the assembly vehicle to enable the guide end 102 of the guide rod 100 to be vertically upward; the guide portion 103 of the guide rod 100 is extended out of the end of the core machine 2 where the fan assembly 1 is to be assembled, and is raised by a certain length relative to the fulcrum graphite piece 3.
S4, hoisting the fan assembly 1 which is assembled and qualified: lifting the fan assembly 1 by using a lifting appliance, enabling the fulcrum bearing assembly 4 on the fan assembly 1 to be positioned right above the guide end 102 of the guide rod 100, then lowering the fan assembly 1, and enabling the central hole 41 of the fulcrum bearing assembly 4 on the fan assembly 1 to be sleeved into the guide part 103 from the guide end 102 of the guide rod 100 until the fulcrum bearing assembly 4 is matched with the fulcrum graphite piece 3 in place; the fan assembly 1 should be slowly lowered in the process of lowering; in the process, the central hole 41 of the fulcrum bearing assembly 4 is firstly sleeved into the guide part 103 from the guide end 102 of the guide rod 100, the guide part 103 is utilized to guide and limit the fan assembly 1, and the fulcrum bearing assembly 4 on the fan assembly 1 is assembled into the fulcrum graphite piece 3 to realize matching in the process of continuously lowering the fan assembly 1; because by the direction limiting displacement of guide part 103, consequently can reduce the rocking of fulcrum bearing assembly 4 in-process of assembling to fulcrum graphite spare 3 effectively, and then avoid fulcrum bearing assembly 4 and the condition that fulcrum graphite spare 3 bumps to this destruction of avoiding the fulcrum graphite spare 3 that causes.
S5, rotating the fan assembly 1 to align the fan assembly 1 with the anti-error holes arranged on the core machine 2, and then connecting and installing the fan assembly 1 and the core machine 2; specifically, the fan assembly 1 is connected to the core 2 by a plurality of bolts disposed along the circumferential direction.
And S6, turning the assembly vehicle to enable the hoisting end 101 of the guide rod 100 to be vertically upward, then detaching the connecting piece for connecting the positioning ring 200 and the core machine 2, and finally taking out the pilot device 5.
At this point, the assembly of the fan assembly 1 and the core 2 is completed.
Claims (10)
1. A lead positive device for aeroengine fan sub-assembly, lead positive device (5) and be used for assembling fan sub-assembly (1) with core machine (2), the assembly of fan sub-assembly (1) and core machine (2) is realized through fulcrum graphite spare (3) and the fulcrum bearing subassembly (4) cooperation on fan sub-assembly (1) that set up on core machine (2), characterized by that: the guide device (5) comprises a guide rod (100), a positioning ring (200) and a plurality of connecting pieces (300), one end of the guide rod (100) is a hoisting end (101), the other end of the guide rod (100) is a guide end (102), the positioning ring (200) is coaxially arranged at one end of the hoisting end (101) of the guide rod (100), the connecting pieces (300) are distributed at intervals along the circumferential direction of the positioning ring (200), one end of each connecting piece (300) is connected with the positioning ring (200), and the other end of each connecting piece is connected with the guide rod (100); a matching ring surface (201) used for being matched with the core machine (2) is formed on one side of the positioning ring (200) facing to the guide end (102), and a plurality of connecting holes (202) used for being connected with the core machine (2) are formed in the positioning ring (200) at intervals along the circumferential direction; the guide end (102) of the guide rod (100) can penetrate through the central through hole of the core machine (2) and penetrate out from the end, matched with the fan assembly (1), of the core machine (2), and the penetrating part forms a guide part (103) used for being matched with the central hole (41) of the fulcrum bearing assembly (4) on the fan assembly (1) in an inserting mode.
2. The pilot assembly for an aircraft engine fan assembly of claim 1, further comprising: an annular boss structure (104) matched with a corresponding limiting structure in the core machine (2) is formed in the middle of the guide rod (100), and the diameter of the annular boss structure (104) is larger than that of other parts of the guide rod (100).
3. The pilot assembly for an aircraft engine fan assembly of claim 1, further comprising: the connecting piece (300) is obliquely arranged relative to the axis of the guide rod (100), and the extending direction of the connecting piece (300) from the end connected with the guide rod (100) to the end connected with the positioning ring (200) is obliquely arranged towards the guide end (102) of the guide rod (100).
4. The pilot assembly for an aircraft engine fan assembly of claim 1, further comprising: the connecting pieces (300) are distributed along the circumferential direction of the positioning ring (200) at equal angular intervals.
5. The pilot assembly for an aircraft engine fan assembly of claim 1, further comprising: six to twelve connecting pieces (300) are arranged.
6. The pilot assembly for an aircraft engine fan assembly of claim 1, further comprising: ten connectors (300) are provided.
7. The pilot assembly for an aircraft engine fan assembly of claim 1, further comprising: a hanging ring (105) is arranged at the hoisting end (101).
8. The pilot assembly for an aircraft engine fan assembly of any one of claims 1 to 7, wherein: the guide part (103) can be detached.
9. The apparatus of claim 8 for guiding an aircraft engine fan assembly, wherein: the guide section (103) has an adjustment amount of 0-4mm in the axial direction of the guide rod (100).
10. Method for assembling an aircraft engine fan assembly, using a piloting device (5) for the assembly of aircraft engine fan assemblies according to any one of claims 1 to 9, characterized in that: the method comprises the following steps:
s1, fixedly mounting the assembled and qualified core machine (2) on a turnover assembly vehicle, and enabling one end of the core machine (2) which needs to be in fit connection with the positioning ring (200) to be vertically upward through the turnover assembly vehicle;
s2, hoisting and guiding device (5): hoisting the guiding device (5) from the hoisting end (101) by using a lifting appliance, enabling the guiding end (102) of the guiding rod (100) to penetrate through the central through hole of the core machine (2) from top to bottom and penetrate out of one end, matched with the fan assembly (1), of the core machine (2), and then connecting and fixing the positioning ring (200) and the core machine (2) through the connecting hole (202) through a connecting piece;
s3, overturning the assembly vehicle to enable the guide end (102) of the guide rod (100) to be vertically upward;
s4, hoisting the fan assembly (1) which is assembled and qualified: hoisting the fan assembly (1) by using a lifting appliance, enabling the fulcrum bearing assembly (4) on the fan assembly (1) to be positioned right above the guide end (102) of the guide rod (100), then lowering the fan assembly (1) to enable the central hole (41) of the fulcrum bearing assembly (4) on the fan assembly (1) to be sleeved into the guide part (103) from the guide end (102) of the guide rod (100) until the fulcrum bearing assembly (4) is matched with the fulcrum graphite piece (3) in place;
s5, rotating the fan assembly (1), aligning the fan assembly (1) with the error-proof holes arranged on the core machine (2), and then connecting and installing the fan assembly (1) and the core machine (2);
s6, turning the assembly vehicle to enable the hoisting end (101) of the guide rod (100) to be vertically upward, then detaching a connecting piece for connecting the positioning ring (200) and the core machine (2), and finally taking out the pilot device (5).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010796685.0A CN111946460B (en) | 2020-08-10 | 2020-08-10 | Guiding device for assembling fan assembly of aircraft engine and assembling method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010796685.0A CN111946460B (en) | 2020-08-10 | 2020-08-10 | Guiding device for assembling fan assembly of aircraft engine and assembling method |
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| CN111946460B CN111946460B (en) | 2022-08-05 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114510798A (en) * | 2022-01-25 | 2022-05-17 | 中国航发沈阳发动机研究所 | Pneumatic axial force error-proofing analysis method for aircraft engine |
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