CN114029901A - Tool and method for assembling rotor of gas generator of aircraft engine - Google Patents
Tool and method for assembling rotor of gas generator of aircraft engine Download PDFInfo
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- CN114029901A CN114029901A CN202111326202.1A CN202111326202A CN114029901A CN 114029901 A CN114029901 A CN 114029901A CN 202111326202 A CN202111326202 A CN 202111326202A CN 114029901 A CN114029901 A CN 114029901A
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- 210000004907 gland Anatomy 0.000 claims abstract description 53
- 238000009434 installation Methods 0.000 claims abstract description 23
- 230000006835 compression Effects 0.000 claims description 35
- 238000007906 compression Methods 0.000 claims description 35
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000003825 pressing Methods 0.000 abstract description 8
- 230000008569 process Effects 0.000 abstract description 8
- 238000002485 combustion reaction Methods 0.000 description 5
- 239000000446 fuel Substances 0.000 description 5
- 210000003781 tooth socket Anatomy 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
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- 229910052802 copper Inorganic materials 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/14—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/02—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same
- B25B27/026—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same fluid driven
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Abstract
The invention discloses an aircraft engine gas generator rotor assembling tool.A nut mounting assembly firstly connects a fixing piece with a gas turbine secondary disc and then connects a mounting plate connected with the fixing piece with an engine casing so as to indirectly connect the gas turbine secondary disc with the engine casing, realize the rotation stopping of a gas turbine rotor and prevent the rotor from deflecting and the rotating piece from slipping in the process of pressing a nut by a bearing after the rotating piece is screwed down; the rear bearing lock ring is arranged on the rear bearing gland nut through the arrangement positioning rod, the pressure head and the hydraulic device, so that the reliability of the rear bearing gland nut arranged on the rear bearing is ensured. This scheme passes through nut installation subassembly installation rear bearing gland nut to solve the difficult not only rotation of rotor in the rear bearing gland nut assembling process, the difficult centering of rotor and skid the scheduling problem when screwing up, and then stability when improving the assembly and the reliability after the assembly, rethread lock collar installation subassembly is installed the rear bearing lock collar in rear bearing gland nut, improves the reliability after the installation.
Description
Technical Field
The invention relates to the technical field of assembly of parts of an aircraft engine, in particular to an assembly tool for a rotor of a gas generator of the aircraft engine. In addition, the invention also relates to an aircraft engine gas generator rotor assembling method adopting the aircraft engine gas generator rotor assembling tool.
Background
The rotor of the aircraft engine gas generator generally comprises a three-stage axial flow, a one-stage centrifugal compressor and a two-stage gas turbine rotor, wherein the centrifugal compressor is connected with the gas turbine rotor through a central pull rod, the centrifugal compressor and the gas turbine rotor are respectively installed on the central pull rod through compression nuts, and then a lock ring safety is installed; the combustion rotor adopts a 1-0-1 supporting mode, the rear fulcrum of the combustion rotor is positioned at the rear shaft neck of the gas turbine secondary disc, a rear bearing is arranged on the shaft neck, a compression nut is required to compress and a locking ring safety is required to be arranged, during assembly, the gas compressor rotor and the gas turbine rotor are separately arranged, namely the compression nut and the locking ring of the turbine rotor are required to be assembled.
The existing assembly method of the aeroengine gas generator rotor generally comprises the steps of firstly installing the rear bearing and the gland nut and the lock ring thereof, then installing the turbine rotor, and then installing the gland nut and the lock ring of the turbine rotor during final assembly, but the installation method has the following defects (as shown in figure 1): 1. the back bearing gland nut surrounds the turbine rotor gland nut, the radial gap between the two nuts is very small, and the distance between the turbine rotor gland nut and the mounting opening of the casing is large, so that the processing difficulty of an assembling tool for the turbine rotor gland nut is large, the strength cannot be ensured, the assembling tool is easy to stress and break in the assembling process, broken fragments are difficult to take out, and the whole aeroengine gas generator rotor cannot be assembled smoothly; 2. in the final assembly state, the rotor of the aeroengine gas generator is only supported by the front bearing, and then the lock ring is knocked by the copper bar and the hammer to ensure that the rotor bearing is impacted, and the rotor is easy to deflect and lose collision.
If the assembly method is improved, the turbine rotor compression nut and the lock ring are firstly installed, and then the rear bearing compression nut and the lock ring are installed, the following problems can also occur: 1. the rotor rotation stopping problem: when the bearing gland nut is assembled, after the assembly, the weight of the fuel combustion rotor is too large, the fuel combustion rotor cannot be manually stopped rotating, the fuel combustion rotor is in a rotatable state, and the rear bearing gland nut needs to be screwed down according to a specified torque, so that the rotor needs to be stopped firstly, and meanwhile, the rotor is positioned in an engine, and the rotor is difficult to find out the thrust point of the rotor when the rotor is stopped rotating; 2. rotor centering problem: because the outer ring of the rear bearing of the fuel rotor is not installed temporarily, the rear bearing box is lost, the whole fuel rotor is in a cantilever structure, and the rotor is easy to deflect when a nut on the rotor is screwed down by a large force, so that the rotor and the stator are likely to be rubbed and abraded, and potential safety hazards are caused; 3. the problem of tightening slip: because of the big influence of outside quick-witted casket size, lead to erecting tool to need longer sleeve, it is more difficult with fixed to screw up in-process spanner centering, and erecting tool easily skids from the nut assembly groove to influence the assembly smoothness nature, and have certain potential safety hazard, easily cause the part damage.
Disclosure of Invention
The invention provides an aircraft engine gas generator rotor assembling tool and an aircraft engine gas generator rotor assembling method, which are used for solving the technical problems that a turbine rotor is difficult to assemble in the existing aircraft engine gas generator rotor assembling process, the rotor cannot stop rotating and is difficult to center and easy to slip when a rear bearing gland nut and a lock ring are assembled.
According to one aspect of the invention, an aircraft engine gas generator rotor assembly tool is provided, comprising a nut mounting assembly for mounting a rear bearing gland nut and a lock collar mounting assembly for mounting a rear bearing lock collar on the rear bearing gland nut; the nut mounting assembly comprises a fixing piece, a mounting plate, a positioning ring and a rotating piece, wherein the fixing piece is used for being connected with the gas turbine secondary disc and coaxially arranged with the gas turbine secondary disc, the mounting plate is connected with the fixing piece and is used for being connected with the engine casing, the positioning ring is connected with the fixing piece and coaxially arranged with the fixing piece, and the rotating piece penetrates through the positioning ring and is coaxially arranged with the positioning ring and is used for screwing the rear bearing compression nut; the locking ring installation component comprises a positioning rod connected with the central pull rod, a pressure head sleeved on the positioning rod and used for abutting against the rear bearing locking ring, and a hydraulic device sleeved on the positioning rod and used for applying force to abut against the pressure head.
Furthermore, the fixing piece is provided with a first connecting end used for being connected with the gas turbine secondary disc and a second connecting end simultaneously connected with the mounting plate and the positioning ring, the first connecting end is provided with clamping blocks used for clamping and matching with clamping grooves of the gas turbine secondary disc, and the clamping blocks and the clamping grooves are arranged in a one-to-one correspondence mode.
Further, the second link is equipped with the first installation limit that radially outwards extends the formation, and the holding ring is equipped with the second installation limit that radially outwards extends the formation, and the both ends face on the axial direction on first installation limit is laminated with mounting panel and second installation limit respectively, and nut installation component still includes the connecting hole that runs through second installation limit, first installation limit and mounting panel and the first connecting bolt of being connected with the connecting hole along the axial, and a plurality of connecting holes are arranged along nut installation component circumference interval.
Furthermore, the mounting plate is provided with mounting holes which are used for being arranged corresponding to bolt holes in the engine casing, the mounting holes are arranged corresponding to the bolt holes one to one, and the nut mounting assembly further comprises second connecting bolts used for connecting the bolt holes and the mounting holes.
Furthermore, the rotating part is provided with a rotating connecting end which penetrates through the positioning ring and is connected with the rear bearing compression nut and a handheld force application end which is used for rotating to apply force to tighten the rear bearing compression nut, the rotating connecting end is provided with a clamping tooth which is used for clamping the matched clamping tooth with the tooth socket of the rear bearing compression nut, and the clamping tooth and the tooth socket are arranged in a one-to-one correspondence mode.
Further, the hand-held force application end includes a rotating handle arranged in a radial direction.
Furthermore, the positioning ring is in clearance fit with the rotating part, and the distance between the positioning ring and the rotating part ranges from 0.01mm to 0.08 mm.
Furthermore, the pressure head is of a cylindrical structure, the opening end of the pressure head is provided with a pressing platform which is used for being arranged corresponding to the safety groove of the rear bearing compression nut, and the pressing platform and the safety groove are arranged in a one-to-one correspondence mode.
Furthermore, the outer side wall of the positioning rod is provided with an external thread structure which is in threaded connection with the internal thread structure of the inner side wall of the central pull rod.
According to another aspect of the present invention, there is also provided an aircraft engine gas generator rotor assembly method, using the aircraft engine gas generator rotor assembly tool described above, including the steps of: installing a compressor rotor assembly into an engine casing; installing a gas turbine primary rotor assembly into an engine case; mounting the rear bearing inner ring on a rear shaft neck of a secondary rotor of the gas turbine; mounting a gas turbine secondary rotor into an engine case; mounting a rotor compression nut on a gas turbine secondary rotor, and mounting a rotor locking ring on the rotor compression nut; the rear bearing compression nut is installed on the rear bearing through the nut installation assembly, and the rear bearing locking ring is installed on the rear bearing compression nut through the locking ring installation assembly.
The invention has the following beneficial effects:
according to the aircraft engine gas generator rotor assembling tool, the nut mounting assembly firstly connects the fixing piece with the gas turbine secondary disc, and then connects the mounting plate connected with the fixing piece with the engine casing, so that the gas turbine secondary disc is indirectly connected with the inside of the engine casing, and the rotation stopping of a gas turbine rotor is realized; meanwhile, after the turbine secondary disc is fixed, the centering problem of the gas turbine rotor can be solved, then the positioning ring is connected with the fixed part, the rotating part penetrates through the positioning ring to tighten the rear bearing compression nut, and the positioning ring and the fixed part are coaxially arranged, and the positioning ring and the gas turbine secondary disc are coaxially arranged, namely the rotating part and the gas turbine secondary disc are coaxially arranged, so that the centering problem of the rotor is further solved, and the rotor is prevented from deflecting and slipping in the process of tightening the rear bearing compression nut by the rotating part; the lock ring mounting assembly is used for mounting the rear bearing lock ring on the rear bearing gland nut through the mounting positioning rod, the pressure head and the hydraulic device so as to ensure the reliability of the rear bearing gland nut on the rear bearing. The aircraft engine gas generator rotor assembling tool is provided with the rear bearing gland nut through the nut mounting assembly, so that the problems that a rotor is difficult to stop rotating, the rotor is difficult to center, the rotor slips when being screwed and the like in the assembling process of the rear bearing gland nut are solved, the stability during assembling and the reliability after assembling are improved, and the rear bearing lock ring is mounted on the rear bearing gland nut through the lock ring mounting assembly, so that the reliability after assembling is improved.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a diagram of a rear bearing gland nut and a turbine rotor gland nut of the prior art;
FIG. 2 is a schematic structural view of a nut mounting assembly in an aircraft engine gas generator rotor assembly tool in accordance with a preferred embodiment of the present invention;
FIG. 3 is a schematic structural view of a nut mounting assembly mounting nut in an aircraft engine gas generator rotor assembly tool in accordance with a preferred embodiment of the present invention;
FIG. 4 is a schematic illustration of the lock ring mounting assembly of the aircraft engine gas generator rotor assembly tool in accordance with the preferred embodiment of the present invention in its lock ring installation configuration;
fig. 5 is a schematic perspective view of a ram in an aircraft engine gas generator rotor assembly tool in accordance with a preferred embodiment of the invention.
Illustration of the drawings:
100. a nut mounting assembly; 110. a fixing member; 111. a first connection end; 112. a second connection end; 113. a first mounting edge; 114. a clamping block; 120. mounting a plate; 130. a positioning ring; 131. a second mounting edge; 140. a rotating member; 141. rotating the connecting end; 142. a hand-held force application end; 143. rotating the handle; 144. clamping teeth; 150. a first connecting bolt; 160. a second connecting bolt; 200. a lock ring mounting assembly; 210. positioning a rod; 220. a pressure head; 221. pressing the table; 230. and a hydraulic device.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
FIG. 1 is a diagram of a rear bearing gland nut and a turbine rotor gland nut of the prior art; FIG. 2 is a schematic structural view of a nut mounting assembly in an aircraft engine gas generator rotor assembly tool in accordance with a preferred embodiment of the present invention; FIG. 3 is a schematic structural view of a nut mounting assembly mounting nut in an aircraft engine gas generator rotor assembly tool in accordance with a preferred embodiment of the present invention; FIG. 4 is a schematic illustration of the lock ring mounting assembly of the aircraft engine gas generator rotor assembly tool in accordance with the preferred embodiment of the present invention in its lock ring installation configuration; fig. 5 is a schematic perspective view of a ram in an aircraft engine gas generator rotor assembly tool in accordance with a preferred embodiment of the invention.
As shown in fig. 2-5, the aircraft engine gas generator rotor assembly tool of the present embodiment includes a nut mounting assembly 100 for mounting a rear bearing gland nut and a lock collar mounting assembly 200 for mounting a rear bearing lock collar to the rear bearing gland nut; the nut mounting assembly 100 comprises a fixed member 110 which is used for being connected with a gas turbine secondary disk and is coaxially arranged with the gas turbine secondary disk, a mounting plate 120 which is connected with the fixed member 110 and is used for being connected with an engine casing, a positioning ring 130 which is connected with the fixed member 110 and is coaxially arranged with the fixed member 110, and a rotating member 140 which penetrates through the positioning ring 130 and is coaxially arranged with the positioning ring 130 and is used for screwing a rear bearing compression nut; the locking ring mounting assembly 200 includes a positioning rod 210 connected to the center rod, a pressing head 220 sleeved on the positioning rod 210 for pressing the rear bearing locking ring, and a hydraulic device 230 sleeved on the positioning rod 210 for applying force to press the pressing head 220. Specifically, the aircraft engine gas generator at least comprises an engine casing, a central pull rod, a compressor rotor, a gas turbine primary disc, a gas turbine secondary disc and a rear bearing arranged at the rear journal of the gas turbine secondary disc, wherein the central pull rod, the compressor rotor, the gas turbine primary disc and the gas turbine secondary disc are all arranged in the engine casing, and the compressor rotor, the gas turbine primary disc and the gas turbine secondary disc are all arranged on the central pull rod. Specifically, according to the aircraft engine gas generator rotor assembling tool, the nut mounting assembly 100 firstly connects the fixing piece 110 with the gas turbine secondary disc, and then connects the mounting plate 120 connected with the fixing piece 110 with the engine casing, so that the gas turbine secondary disc is indirectly connected with the inside of the engine casing, and the rotation stopping of the gas turbine rotor is realized; meanwhile, after the turbine secondary disc is fixed, the centering problem of the gas turbine rotor can be solved, then the positioning ring 130 is connected with the fixed part 110, the rotating part 140 penetrates through the positioning ring 130 to tighten the rear bearing gland nut, and the rotating part 140 and the positioning ring 130 are coaxially arranged, the positioning ring 130 and the fixed part 110 are coaxially arranged, the positioning ring 130 and the gas turbine secondary disc are coaxially arranged, namely the rotating part 140 and the gas turbine secondary disc are coaxially arranged, so that the centering problem of the rotor is further solved, and the rotor deflection and the rotating part 140 slippage are prevented in the process that the rotating part 140 tightens the rear bearing gland nut; the lock ring mounting assembly 200 further mounts the rear bearing lock ring on the rear bearing gland nut through the mounting positioning rod 210, the pressure head 220 and the hydraulic device 230, so as to ensure the reliability of the mounting of the rear bearing gland nut on the rear bearing. The aircraft engine gas generator rotor assembling tool is used for installing the rear bearing gland nut through the nut installation component 100, so that the problems that the rotor is difficult to stop rotating, the rotor is difficult to center and the rotor slips when being screwed in the rear bearing gland nut assembling process are solved, the stability during assembling and the reliability after assembling are further improved, and the rear bearing lock ring is installed on the rear bearing gland nut through the lock ring installation component 200, so that the reliability after assembling is improved.
As shown in fig. 2 and 3, in the embodiment, the fixing member 110 is provided with a first connecting end 111 for connecting with the gas turbine secondary disk and a second connecting end 112 for connecting with the mounting plate 120 and the positioning ring 130, the first connecting end 111 is provided with a fixture block 114 for clamping and matching with a fixture groove of the gas turbine secondary disk, and the fixture block 114 and the fixture groove are arranged in a one-to-one correspondence. Specifically, the gas turbine secondary disk is provided with an even number of clamping grooves, the even number of clamping grooves are divided into two groups which are symmetrically arranged at 180 degrees, the first connecting end 111 is provided with clamping blocks 114 with the same number as the clamping grooves, the clamping blocks 114 and the clamping grooves are arranged in a one-to-one correspondence manner, and the clamping blocks 114 are clamped in the clamping grooves, so that the fixing member 110 and the gas turbine secondary disk are ensured to be stably connected.
As shown in fig. 2 and 3, in this embodiment, the second connecting end 112 is provided with a first mounting edge 113 formed by extending radially outward, the positioning ring 130 is provided with a second mounting edge 131 formed by extending radially outward, two end faces of the first mounting edge 113 in the axial direction are respectively attached to the mounting plate 120 and the second mounting edge 131, the nut mounting assembly 100 further includes a connecting hole axially penetrating through the second mounting edge 131, the first mounting edge 113 and the mounting plate 120, and a first connecting bolt 150 connected to the connecting hole, and the plurality of connecting holes are circumferentially arranged at intervals along the nut mounting assembly 100. Specifically, the second connecting end 112 extends radially outward to form a first mounting edge 113, the positioning ring 130 extends radially outward to form a second mounting edge 131, two end faces of the first mounting edge 113 in the axial direction are respectively attached to the mounting plate 120 and the second mounting edge 131, and a connecting hole penetrates through the second mounting edge 131, the first mounting edge 113 and the mounting plate 120 and is connected with the first connecting bolt 150 to connect the second mounting edge 131, the first mounting edge 113 and the mounting plate 120 together. Meanwhile, the plurality of connecting holes are arranged at intervals along the circumferential direction of the nut mounting assembly 100, so that the second mounting edge 131, the first mounting edge 113 and the mounting plate 120 are ensured to be connected stably.
As shown in fig. 2 and 3, in the present embodiment, the mounting plate 120 is provided with mounting holes for corresponding arrangement with bolt holes on the engine case, the mounting holes are arranged in one-to-one correspondence with the bolt holes, and the nut mounting assembly 100 further includes second connecting bolts 160 for connecting the bolt holes and the mounting holes. Specifically, the mounting plate 120 is coupled to the bolt hole of the engine case through mounting holes at both ends thereof and a second coupling bolt 160. It should be understood that the fixing member 110 and the gas turbine secondary disk are connected through the clamping block 114 and the clamping groove, the fixing member 110 and the mounting plate 120 are connected through the connecting hole and the first connecting bolt 150, the mounting plate 120 and the engine casing are connected through the mounting hole and the bolt hole, and then the engine casing is connected with the gas turbine secondary disk, so that the rotation stopping of the gas turbine rotor is realized, and the gas turbine rotor is ensured to be incapable of rotating, so that the bearing gland nut is convenient to assemble.
As shown in fig. 2 and 3, in the present embodiment, the rotating member 140 is provided with a rotating connection end 141 penetrating the positioning ring 130 and used for connecting with the rear bearing gland nut, and a hand-held force application end 142 for applying force in rotation to tighten the rear bearing gland nut, the rotating connection end 141 is provided with a latch 144 for latching and cooperating with the tooth socket of the rear bearing gland nut, and the latch 144 and the tooth socket are arranged in one-to-one correspondence. Specifically, the rear bearing compression nut has a plurality of tooth grooves, the rotation connecting end 141 is provided with the latch 144 arranged in one-to-one correspondence with the tooth grooves, and the rotation member 140 and the rear bearing compression nut are connected with the tooth grooves through the latch 144, so that the rotation member 140 applies force to tighten the rear bearing compression nut. It should be appreciated that the stationary member 110 is coaxially disposed with the gas turbine secondary disk, the positioning ring 130 is coaxially disposed with the stationary member 110, and the rotating member 140 is coaxially disposed with the positioning ring 130, and thus the rotating member 140 is coaxially disposed with the gas turbine secondary disk to effectively prevent the rotating member 140 from slipping and rotor deflection during tightening of the rear bearing gland nut.
As shown in fig. 2 and 3, in this embodiment, the hand-held force application end 142 includes a rotating handle 143 disposed in a radial direction. Specifically, tightening of the rear bearing compression nut by turning the handle 143 facilitates application of force to ensure that the rear bearing compression nut is tightened to the desired torque.
In the embodiment shown in fig. 2 and 3, the positioning ring 130 is in clearance fit with the rotating member 140, and the distance between the positioning ring 130 and the rotating member 140 is in the range of 0.01mm to 0.08 mm. Specifically, when the distance between the positioning ring 130 and the rotating member 140 is in the range of 0.01mm-0.08mm, the assembly precision is proper, the manufacturing process difficulty is low, the rotating member 140 and the gas turbine rotor are relatively concentric, and the rotating member 140 is prevented from slipping; when the distance between the positioning ring 130 and the rotating member 140 is less than 0.01mm, the assembly precision is high, the manufacturing process is difficult, and the assembly is difficult; when the distance between the positioning ring 130 and the rotating member 140 is greater than 0.08mm, the rotating member 140 cannot be ensured to be concentric with the gas turbine rotor, which results in slippage when the rotating member 140 is screwed down on the rear bearing gland nut and the gas turbine rotor is deflected. Alternatively, the spacing between the retaining ring 130 and the rotating member 140 may range from 0.01mm to 0.03mm, further improving the reliability of the rotating member 140 when tightening the rear bearing compression nut.
As shown in fig. 5, in the present embodiment, the pressure head 220 has a cylindrical structure, the opening end of the pressure head 220 is provided with a pressure table 221 arranged corresponding to the safety groove of the rear bearing compression nut, and the pressure tables 221 and the safety groove are arranged in one-to-one correspondence. Specifically, the rear bearing gland nut is provided with a plurality of safety slots arranged at intervals in the circumferential direction, the pressure head 220 is provided with pressure tables 221 arranged in one-to-one correspondence with the safety slots, and the pressure head 220 extrudes the rear bearing lock ring through the pressure tables 221 so as to press the outer circle of the rear bearing lock ring into the safety slots of the rear bearing gland nut, thereby ensuring that the rear bearing gland nut and the rear bearing lock ring are reliably assembled.
As shown in fig. 4, in the present embodiment, the outer side wall of the positioning rod 210 is provided with an external thread structure for being in threaded connection with the internal thread structure of the inner side wall of the center rod. Specifically, the positioning rod 210 is connected with the central rod through an external thread structure and an internal thread structure, so that the connection is reliable and the disassembly and assembly are convenient.
As shown in fig. 4, the hydraulic device 230 further includes a hydraulic cylinder for generating pressure and a hydraulic jack connected to the hydraulic cylinder for applying pressure to the ram 220. Specifically, pressure is transmitted into the hydraulic jack through the hydraulic cylinder, the hydraulic jack transmits the pressure to the pressure head 220, and the pressure head 220 extrudes the rear bearing locking ring, so that the rear bearing locking ring is connected with the rear bearing compression nut.
The aircraft engine gas generator rotor assembling method of the embodiment adopts the aircraft engine gas generator rotor assembling tool, and comprises the following steps: installing a compressor rotor assembly into an engine casing; installing a gas turbine primary rotor assembly into an engine case; mounting the rear bearing inner ring on a rear shaft neck of a secondary rotor of the gas turbine; mounting a gas turbine secondary rotor into an engine case; mounting a rotor compression nut on a gas turbine secondary rotor, and mounting a rotor locking ring on the rotor compression nut; the rear bearing gland nut is mounted to the rear bearing by the nut mounting assembly 100 and the rear bearing lock collar is mounted to the rear bearing gland nut by the lock collar mounting assembly 200.
The rear bearing compression nut is mounted on the rear bearing through the nut mounting assembly 100, and specifically comprises the following steps:
clamping and matching the clamping block 114 at the first connecting end 111 of the fixing member 110 with a clamping groove on a gas turbine secondary disc, then enabling the mounting hole of the mounting plate 120 to correspond to the bolt hole of the engine case, connecting the fixing member 110 with the mounting plate 120 through a first connecting bolt 150, and connecting the mounting plate 120 with the engine case through a second connecting bolt 160;
the positioning ring 130 is connected to the fixed member 110 by the first connecting bolt 150, the rotating member 140 passes through the positioning ring 130 and is connected to the rear bearing compression nut, and then the rear bearing compression nut is tightened by the rotating member 140, and after the tightening torque reaches the required torque, the nut mounting assembly 100 is removed.
The rear bearing lock ring is then mounted to the rear bearing gland nut by the lock ring mounting assembly 200. The method specifically comprises the following steps:
connecting the positioning rod 210 with the central pull rod;
mounting the ram 220 to the rear bearing collar;
mounting the jack to ram 220, connecting the hydraulic cylinders;
pressure is generated through the hydraulic cylinder, the hydraulic jack transmits the pressure to the pressure head 220, the boss on the pressure head 220 presses the excircle of the rear bearing lock ring at the corresponding position to the safety groove of the rear bearing gland nut, the safety of the lock ring is realized, and then the lock ring installation component 200 is disassembled.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An aircraft engine gas generator rotor assembly tool comprising a nut mounting assembly (100) for mounting a rear bearing gland nut and a lock collar mounting assembly (200) for mounting a rear bearing lock collar to the rear bearing gland nut;
the nut mounting assembly (100) comprises a fixing piece (110) which is used for being connected with the gas turbine secondary disk and coaxially arranged with the gas turbine secondary disk, a mounting plate (120) which is connected with the fixing piece (110) and is used for being connected with an engine casing, a positioning ring (130) which is connected with the fixing piece (110) and coaxially arranged with the fixing piece (110), and a rotating piece (140) which penetrates through the positioning ring (130) and is coaxially arranged with the positioning ring (130) and is used for screwing a rear bearing compression nut;
the locking ring mounting assembly (200) comprises a positioning rod (210) connected with the central pull rod, a pressure head (220) sleeved on the positioning rod (210) and used for abutting against the rear bearing locking ring, and a hydraulic device (230) sleeved on the positioning rod (210) and used for applying force to abut against the pressure head (220).
2. The aircraft engine gas generator rotor assembly tool according to claim 1, wherein the fixing member (110) is provided with a first connecting end (111) for connecting with the gas turbine secondary disk and a second connecting end (112) for connecting with the mounting plate (120) and the positioning ring (130) at the same time, the first connecting end (111) is provided with a fixture block (114) for clamping and matching with a clamping groove of the gas turbine secondary disk, and the fixture block (114) is arranged in one-to-one correspondence with the clamping groove.
3. The aircraft engine gas generator rotor assembly tool as claimed in claim 2, wherein the second connection end (112) is provided with a first mounting edge (113) extending radially outward, the positioning ring (130) is provided with a second mounting edge (131) extending radially outward, two end faces of the first mounting edge (113) in the axial direction are respectively attached to the mounting plate (120) and the second mounting edge (131), the nut mounting assembly (100) further comprises connection holes axially penetrating through the second mounting edge (131), the first mounting edge (113) and the mounting plate (120), and first connection bolts (150) connected with the connection holes, and the plurality of connection holes are circumferentially spaced along the nut mounting assembly (100).
4. The aircraft engine gas generator rotor assembly tool of claim 1, wherein the mounting plate (120) is provided with mounting holes for corresponding arrangement with bolt holes on the engine case, the mounting holes being arranged in one-to-one correspondence with the bolt holes, the nut mounting assembly (100) further comprising second attachment bolts (160) for attaching the bolt holes and the mounting holes.
5. The aircraft engine gas generator rotor assembly tool of claim 1, wherein the rotary member (140) is provided with a rotary attachment end (141) for connection with the rear bearing gland nut through the retaining ring (130) and a hand-held force application end (142) for applying a force in rotation to tighten the rear bearing gland nut, the rotary attachment end (141) being provided with a latch (144) for snap fit engagement with a tooth slot of the rear bearing gland nut, the latch (144) being arranged in one-to-one correspondence with the tooth slot.
6. The aircraft engine gas generator rotor assembly tool of claim 5, wherein the hand-held force application end (142) includes a turning handle (143) disposed in a radial direction.
7. The aircraft engine gas generator rotor assembly tool of claim 1, wherein the positioning ring (130) is a clearance fit with the rotor (140), and wherein the positioning ring (130) is spaced from the rotor (140) by a distance in the range of 0.01mm to 0.08 mm.
8. The aircraft engine gas generator rotor assembly tool according to any one of claims 1 to 7, wherein the pressure head (220) is of a cylindrical structure, the open end of the pressure head (220) is provided with a pressure table (221) for corresponding arrangement with a safety groove of the rear bearing gland nut, and the pressure tables (221) are arranged in one-to-one correspondence with the safety groove.
9. The aircraft engine gas generator rotor assembly tool of any one of claims 1 to 7, wherein an outer side wall of the positioning rod (210) is provided with an external thread structure for threaded connection with an internal thread structure of an inner side wall of the center stay.
10. A method for assembling an aircraft engine gas generator rotor, characterized in that use is made of an aircraft engine gas generator rotor assembly tool according to any one of claims 1 to 9, comprising the following steps:
installing a compressor rotor assembly into an engine casing;
installing a gas turbine primary rotor assembly into an engine case;
mounting the rear bearing inner ring on a rear shaft neck of a secondary rotor of the gas turbine;
mounting a gas turbine secondary rotor into an engine case;
mounting a rotor compression nut on a gas turbine secondary rotor, and mounting a rotor locking ring on the rotor compression nut;
the rear bearing compression nut is installed on the rear bearing through the nut installation component (100), and the rear bearing locking ring is installed on the rear bearing compression nut through the locking ring installation component (200).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111326202.1A CN114029901A (en) | 2021-11-10 | 2021-11-10 | Tool and method for assembling rotor of gas generator of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111326202.1A CN114029901A (en) | 2021-11-10 | 2021-11-10 | Tool and method for assembling rotor of gas generator of aircraft engine |
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| Publication Number | Publication Date |
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| CN114029901A true CN114029901A (en) | 2022-02-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111326202.1A Pending CN114029901A (en) | 2021-11-10 | 2021-11-10 | Tool and method for assembling rotor of gas generator of aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114535982A (en) * | 2022-04-02 | 2022-05-27 | 中国航发沈阳发动机研究所 | Aeroengine doublestage high whirlpool stator unit body assembly fixture |
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Application publication date: 20220211 |