CN110654967A - Hoisting device and method for low-pressure turbine rotor of aircraft engine - Google Patents
Hoisting device and method for low-pressure turbine rotor of aircraft engine Download PDFInfo
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- CN110654967A CN110654967A CN201810697198.1A CN201810697198A CN110654967A CN 110654967 A CN110654967 A CN 110654967A CN 201810697198 A CN201810697198 A CN 201810697198A CN 110654967 A CN110654967 A CN 110654967A
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- turbine rotor
- pressure turbine
- rotating shaft
- aircraft engine
- suspender
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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
- B66C1/107—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 for lifting engines
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Load-Engaging Elements For Cranes (AREA)
Abstract
The invention provides a hoisting device and a hoisting method for a low-pressure turbine rotor of an aeroengine, wherein the hoisting device for the low-pressure turbine rotor of the aeroengine comprises: mounting the main body; the rotating shaft penetrates through the mounting main body; one end of each suspender is arranged in the installation main body, the suspender is connected with the rotating shaft through at least two sections of symmetrical transmission thread pairs with opposite rotation directions, the radial distance between the two suspenders is adjusted, and the other end of each suspender is positioned below the installation main body and is connected with the turbine rotor; the hand wheel is arranged at the outer end part of the rotating shaft and is used for driving the rotating shaft to rotate; the rotating motion of the rotating shaft is converted into the linear motion of the suspender through the hand wheel, so that the turbine rotor is hoisted. The invention realizes the stable hoisting of the rotor disc only by using the inner hole and the end surface, protects the comb tooth and the thread structure of the body part to the maximum extent and meets the assembly process requirement of the rotor-stator assembly of the low-pressure turbine.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to a hoisting device and method for a low-pressure turbine rotor of an aircraft engine.
Background
In the field of aero-engines, low-vortex stator assembly is an important link of aero-engine assembly, and the honeycomb and comb tooth structures in unit bodies are more. Meanwhile, the low-pressure turbine generally has a plurality of different size series, so that it is necessary to design an adjustable and universal reliable lifting appliance.
In addition, according to the assembly process, in order to protect the rotor grates and the thread structures at all levels, the following two requirements must be met in the hoisting process:
firstly, the lifting appliance is fixed on the center of the low-pressure turbine disc, the damage to the grate teeth and the thread structures of the rotors at all levels in the lifting process is avoided, and meanwhile, the stability of the rotors and the components thereof in the lifting process needs to be ensured.
And secondly, the hoisting requirements of rotors in different sizes are met.
Fig. 1 is a schematic structural diagram of a conventional rotor hoisting device in the prior art. Fig. 1 shows a typical low-pressure turbine rotor hoisting device, and the device mainly has the following defects:
firstly, a rabbet is required to be arranged on a grate disc on a turbine disc, the turbine disc is fixedly connected to the outer side of the rabbet through two half snap rings, and special requirements are met for the structure of the turbine disc.
And secondly, the telescopic adjusting structure is not arranged, so that the hoisting of different-stage rotors cannot be simultaneously met.
Thirdly, the structure is complicated, and efficiency is lower, need parts such as installation snap ring, support frame, bolt, gasket nut during the use, and efficiency is lower.
In view of the above, a person skilled in the art needs to develop a novel and reliable hoisting tool to realize a more optimized hoisting method.
Disclosure of Invention
The invention aims to overcome the defects that a hoisting device in the prior art is complex in structure, low in efficiency, incapable of meeting hoisting requirements of rotors of different stages and the like, and provides a hoisting device and a hoisting method for a low-pressure turbine rotor of an aircraft engine.
The invention solves the technical problems through the following technical scheme:
the utility model provides an aeroengine low pressure turbine rotor hoist device which characterized in that, aeroengine low pressure turbine rotor hoist device includes:
mounting the main body; the rotating shaft penetrates through the mounting main body;
one end of each suspender is arranged in the mounting main body, the suspender is connected with the rotating shaft through at least two sections of symmetrical transmission thread pairs with opposite rotation directions, the radial distance between the two suspenders is adjusted, and the other end of each suspender is positioned below the mounting plate and is connected with the turbine rotor;
the hand wheel is arranged at the outer end part of the rotating shaft and is used for driving the rotating shaft to rotate;
the rotating motion of the rotating shaft is converted into the linear motion of the suspender through the hand wheel, so that the turbine rotor is hoisted.
According to one embodiment of the invention, the mounting main body comprises a mounting plate and a fixing block, the fixing block is fixed on the lower end face of the mounting plate, and the rotating shaft penetrates through the fixing block.
According to one embodiment of the invention, the fixing block is provided with a guide groove, the rotating shaft is arranged in the guide groove in a penetrating manner, and the end part of the rotating shaft is provided with a limiting structure.
According to one embodiment of the invention, the hand wheel is fixedly connected with the rotating shaft through a key, a pin and a hexagonal nut.
According to one embodiment of the invention, the hoisting device for the low-pressure turbine rotor of the aircraft engine further comprises a bushing and a lifting bolt, the mounting plate is matched with the bushing in an end face and an inner hole, and the lifting bolt is matched with the bushing in an inner thread.
According to one embodiment of the invention, the rotating shaft is provided with an inwards concave installation part, a limiting block is arranged between the installation part and the installation plate, and the bushing is arranged on the limiting block.
According to one embodiment of the invention, the suspender is connected with the turbine rotor through a limit screw to position the turbine rotor in the radial direction;
and the end part of the suspender is provided with a hook foot, and the turbine rotor is positioned in the axial direction through the hook foot.
According to one embodiment of the invention, a plurality of screw plugs are arranged on the upper end surface of the mounting plate.
According to one embodiment of the invention, the suspension rod is in an inverted L shape, the cross rod of the suspension rod is in a hollow shape, the internal thread of the hollow inner cavity of the cross rod is matched with the external thread of the rotating shaft, and the rotating shaft is arranged in the cross rod in a penetrating way.
The invention also discloses a hoisting method of the low-pressure turbine rotor of the aircraft engine, which is characterized in that the hoisting device of the low-pressure turbine rotor of the aircraft engine is adopted, and the hoisting method of the low-pressure turbine rotor of the aircraft engine comprises the following steps:
the hoisting device for the low-pressure turbine rotor of the aircraft engine avoids the comb teeth and threads of the turbine rotor, the positioning and supporting positions are respectively arranged in the inner hole and the end surface of the turbine rotor, the turbine rotor is radially fixed through the suspender and the limiting screw, and the turbine rotor is axially fixed through the hook foot of the suspender; the rotating motion of the rotating shaft is converted into the linear motion of the suspender through the hand wheel, so that the turbine rotor is hoisted.
The positive progress effects of the invention are as follows:
the hoisting device and the hoisting method for the low-pressure turbine rotor of the aero-engine have the following advantages that:
the method realizes the stable hoisting of the rotor disc only by using the inner hole and the end surface, protects the comb teeth and the thread structure of the body part to the maximum extent, and meets the assembly process requirement of the low-pressure turbine rotor-stator component.
And secondly, the hoisting of rotor discs and components thereof in different stages by using the same hoisting tool is realized, and the distance between two hoisting rods can be controlled by using a telescopic device so as to adapt to the inner hole diameters of different rotors.
And thirdly, stable hoisting of the rotor is realized, and the safety is good. Meanwhile, the self-locking characteristic of the transmission thread pair with the rotating shaft and the two sections of the suspension rod which are symmetrical and have opposite rotating directions and the limiting structures at the two ends are utilized, so that the safety and the stability of the rotor disc and the components thereof in the hoisting process are ensured.
Fourthly, the method is high in universality, does not need a special interface, and is suitable for hoisting disc parts.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings in which like reference numerals denote like features throughout the several views, wherein:
fig. 1 is a schematic structural diagram of a conventional rotor hoisting device in the prior art.
Fig. 2 is a schematic structural diagram of the hoisting device for the low-pressure turbine rotor of the aircraft engine.
FIG. 3 is a top view of the device for lifting a low-pressure turbine rotor of an aircraft engine.
Fig. 4 is a schematic diagram of the positioning and supporting positions of the lifting appliance of the low-pressure turbine rotor lifting device of the aircraft engine.
FIG. 5 is a schematic structural diagram of a rotating shaft in the hoisting device for the low-pressure turbine rotor of the aircraft engine.
FIG. 6 is a schematic structural diagram of a suspender in the low-pressure turbine rotor hoisting device of the aeroengine.
Fig. 7 is a schematic structural diagram of a limiting block in the hoisting device for the low-pressure turbine rotor of the aircraft engine.
FIG. 8 is a front view of a fixing block in the low-pressure turbine rotor hoisting device of the aircraft engine.
FIG. 9 is a side view of a fixing block in the hoisting device for the low-pressure turbine rotor of the aircraft engine.
[ reference numerals ]
Bushing 60
Eye screw 70
Mounting part 21
Hook foot 33
Fixed block 11
Limiting structure 112
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts.
Further, although the terms used in the present invention are selected from publicly known and used terms, some of the terms mentioned in the description of the present invention may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein.
Furthermore, it is required that the present invention is understood, not simply by the actual terms used but by the meaning of each term lying within.
Fig. 2 is a schematic structural diagram of the hoisting device for the low-pressure turbine rotor of the aircraft engine. FIG. 3 is a top view of the device for lifting a low-pressure turbine rotor of an aircraft engine. Fig. 4 is a schematic diagram of the positioning and supporting positions of the lifting appliance of the low-pressure turbine rotor lifting device of the aircraft engine.
As shown in fig. 2 to 4, the invention relates to a low-pressure turbine rotor hoisting device for an aircraft engine, which comprises: the installation body, the rotating shaft 20, the two hanging rods 30 and the hand wheel 40 penetrate through the installation body 20. In this embodiment, the mounting main body includes a mounting plate 10 and a fixing block 11, and the fixing block 11 is fixed on the lower end surface of the mounting plate 10. The fixed block 11 is provided with a guide groove 111 and a limit structure 112 at the end.
One end of the suspender 30 is installed in the fixed block 11, and is connected with the rotating shaft 20 through at least two sections of symmetrical transmission thread pairs with opposite rotation directions, the radial distance between the two suspenders 30 is adjusted, and the other end of the suspender 30 is positioned below the fixed block 11 and is connected with the turbine rotor 50. The hand wheel 40 is installed at the outer end of the rotating shaft 20 and is used for driving the rotating shaft 20 to rotate, and the rotating motion of the rotating shaft 20 is converted into the linear motion of the suspender 30 through the hand wheel 40, so that the turbine rotor 50 is hoisted. The hand wheel 40 is fixedly connected with the rotating shaft 20 through a key 41, a pin 42 and a hexagonal nut 43. When the screw pair of the boom 30 and the rotation shaft 20 is driven, the maximum distance between the two booms is guided and limited. Meanwhile, a plurality of screw plugs 12 are further provided on the upper end surface of the mounting plate 10.
Preferably, the aircraft engine low pressure turbine rotor hoisting device further comprises a bushing 60 and a lifting eye screw 70, the mounting plate 10 is matched with the bushing 60 in an end face and an inner hole, and the lifting eye screw 70 is matched with the bushing 60 in an inner thread.
FIG. 5 is a schematic structural diagram of a rotating shaft in the hoisting device for the low-pressure turbine rotor of the aircraft engine. FIG. 6 is a schematic structural diagram of a suspender in the low-pressure turbine rotor hoisting device of the aeroengine. Fig. 7 is a schematic structural diagram of a limiting block in the hoisting device for the low-pressure turbine rotor of the aircraft engine. FIG. 8 is a front view of a fixing block in the low-pressure turbine rotor hoisting device of the aircraft engine. FIG. 9 is a side view of a fixing block in the hoisting device for the low-pressure turbine rotor of the aircraft engine.
As shown in fig. 5 to 9, a recessed mounting portion 21 is provided on the rotating shaft 20, a stopper 22 is provided between the mounting portion 21 and the mounting plate 10, and the bush 50 is provided on the stopper 22. The stop block 22 is attached to the mounting plate 10 by screws to limit the minimum distance between the two hanger rods 30. The limiting block 22 is in an I shape, the middle part extends outwards to form a protruding limiting part 221, the protruding limiting part 221 is provided with an arc concave surface, and the arc concave surface is matched with the mounting part 21. Thus, the mounting plate 10 and the bushing 50 are adopted to match the end face and the inner hole, and the lifting bolt 60 is matched with the inner thread of the bushing 50, so that the rotor and the components thereof can be stably hoisted through the hanger rod 30.
The hanger bar 30 is in an inverted L-shape, and an upper cross bar 31 of the hanger bar 30 is hollow and internally threaded. The internal thread of the hollow cavity of the cross bar 31 is matched with the external thread of the rotating shaft 20, so that the rotating shaft 20 is arranged in the cross bar 31 in a penetrating way. Therefore, the hanger rods 30 can be connected with the rotating shaft 20 through two symmetrical transmission thread pairs with opposite rotation directions, and the radial distance between the hanger rods 30 can be adjusted.
Here, the hanger bar 30 is connected to the turbine rotor 50 by a stopper screw 32, and the turbine rotor 50 is positioned in the radial direction. The end of the boom 30 is provided with a hook 33, and the turbine rotor 50 is positioned in the axial direction by the hook 32.
The invention also discloses a hoisting method of the low-pressure turbine rotor of the aircraft engine, which comprises the following steps: the hoisting device for the low-pressure turbine rotor of the aircraft engine avoids the comb teeth and threads of the turbine rotor, the positioning and supporting positions are respectively arranged in the inner hole and the end surface of the turbine rotor, the turbine rotor is radially fixed through the suspender and the limiting screw, and the turbine rotor is axially fixed through the hook foot of the suspender; the rotating motion of the rotating shaft is converted into the linear motion of the suspender through the hand wheel, so that the turbine rotor is hoisted.
According to the structural description, the hoisting device for the low-pressure turbine rotor of the aircraft engine, disclosed by the invention, is used for protecting the comb tooth structures and threads of the rotor disks at all levels and realizing stable hoisting of the rotor disks and the components thereof, and solves the following technical problems:
firstly, the supporting position of the lifting appliance needs to avoid the grate and the thread of the rotor.
And the lifting appliance has a telescopic structure, so that stable lifting of different-stage rotors and components thereof can be simultaneously met.
Thirdly, the lifting appliance is provided with a locking device, and the adjustment is flexible.
Fourthly, the whole structure of the lifting appliance is stable and compact.
Aiming at the supporting position of the lifting appliance, the aero-engine low-pressure turbine rotor lifting device needs to avoid the comb teeth and the threads of the rotor, and the positioning and supporting positions are respectively arranged in the inner hole and the end face of the rotor according to the process requirements. Utilize jib and stop screw to carry out radial fixed to the rotor, utilize jib hook foot to carry out axial fixity to the rotor terminal surface simultaneously. Aiming at the requirement of adapting to rotors and components thereof with different inner hole sizes of a lifting appliance, a telescopic structure is designed for stable lifting of the rotors and the components thereof with different levels. The radial distance between the two hanging rods is controlled by the rotating shaft and the two sections of symmetrical transmission thread pairs with opposite rotating directions on the hanging rods.
Based on the self structural characteristics of the low-vortex rotor, the body piece is protected to the maximum extent by avoiding the comb teeth and the threads of the rotor, and the positioning and supporting positions are arranged in the inner hole and the end surface of the rotor disc. Based on all inequality at different levels of low vortex rotor size, for making the hoist can be suitable for the rotor of different internal diameter sizes, the hoist has designed extending structure, has satisfied the stable hoist and mount of different levels of rotor and subassembly. The distance between the two hanging rods can be adjusted by utilizing the transmission thread pairs with the rotating shaft and the two sections of the hanging rods which are symmetrical and have opposite rotating directions. Based on the safety of the rotor and the components thereof in the lifting process, the lifting appliance structurally designs a locking device and a limiting structure.
In summary, the device and the method for hoisting the low-pressure turbine rotor of the aero-engine have the following advantages:
the method realizes the stable hoisting of the rotor disc only by using the inner hole and the end surface, protects the comb teeth and the thread structure of the body part to the maximum extent, and meets the assembly process requirement of the low-pressure turbine rotor-stator component.
And secondly, the hoisting of rotor discs and components thereof in different stages by using the same hoisting tool is realized, and the distance between two hoisting rods can be controlled by using a telescopic device so as to adapt to the inner hole diameters of different rotors.
And thirdly, stable hoisting of the rotor is realized, and the safety is good. Meanwhile, the self-locking characteristic of the transmission thread pair with the rotating shaft and the two sections of the suspension rod which are symmetrical and have opposite rotating directions and the limiting structures at the two ends are utilized, so that the safety and the stability of the rotor disc and the components thereof in the hoisting process are ensured.
Fourthly, the method is high in universality, does not need a special interface, and is suitable for hoisting disc parts.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (10)
1. The utility model provides an aeroengine low pressure turbine rotor hoist device which characterized in that, aeroengine low pressure turbine rotor hoist device includes:
mounting the main body; the rotating shaft penetrates through the mounting main body;
one end of each suspender is arranged in the installation main body, the suspender is connected with the rotating shaft through at least two sections of symmetrical transmission thread pairs with opposite rotation directions, the radial distance between the two suspenders is adjusted, and the other end of each suspender is positioned below the installation main body and is connected with the turbine rotor;
the hand wheel is arranged at the outer end part of the rotating shaft and is used for driving the rotating shaft to rotate;
the rotating motion of the rotating shaft is converted into the linear motion of the suspender through the hand wheel, so that the turbine rotor is hoisted.
2. The aircraft engine low pressure turbine rotor lifting device of claim 1, wherein the mounting body comprises a mounting plate and a fixing block, the fixing block is fixed on the lower end face of the mounting plate, and the rotating shaft is arranged in the fixing block in a penetrating manner.
3. The aircraft engine low pressure turbine rotor hoisting device of claim 2, wherein the fixed block is provided with a guide groove, the rotating shaft is arranged in the guide groove in a penetrating way, and a limiting structure is arranged at the end part of the rotating shaft.
4. The aircraft engine low pressure turbine rotor lifting device of claim 1, wherein the hand wheel is fixedly connected with the rotating shaft through a key, a pin and a hexagon nut.
5. The aircraft engine low pressure turbine rotor lifting device of claim 1, further comprising a bushing and a lifting bolt, wherein the mounting plate is engaged with the bushing in an end face and an inner hole, and the lifting bolt is engaged with the bushing in an inner thread.
6. The aircraft engine low pressure turbine rotor lifting device as claimed in claim 3, wherein the rotating shaft is provided with an inward concave mounting portion, a limiting block is arranged between the mounting portion and the mounting plate, and the bushing is arranged on the limiting block.
7. The aircraft engine low pressure turbine rotor lifting device of claim 1, wherein the hanger rod is connected with the turbine rotor through a limit screw to position the turbine rotor in a radial direction;
and the end part of the suspender is provided with a hook foot, and the turbine rotor is positioned in the axial direction through the hook foot.
8. The aircraft engine low pressure turbine rotor lifting device of claim 1, wherein a plurality of screw plugs are arranged on the upper end surface of the mounting plate.
9. The aircraft engine low pressure turbine rotor hoist device of claim 1, characterized in that, the jib is the L type of invering, the horizontal pole of jib is the cavity type, and the internal thread of the cavity inner chamber of horizontal pole with the external screw thread of pivot matches, the pivot is worn to establish in the horizontal pole.
10. A hoisting method of a low-pressure turbine rotor of an aircraft engine is characterized in that the hoisting device of the low-pressure turbine rotor of the aircraft engine as claimed in any one of claims 1 to 9 is adopted, and the hoisting method of the low-pressure turbine rotor of the aircraft engine comprises the following steps:
the hoisting device for the low-pressure turbine rotor of the aircraft engine avoids the comb teeth and threads of the turbine rotor, the positioning and supporting positions are respectively arranged in the inner hole and the end surface of the turbine rotor, the turbine rotor is radially fixed through the suspender and the limiting screw, and the turbine rotor is axially fixed through the hook foot of the suspender; the rotating motion of the rotating shaft is converted into the linear motion of the suspender through the hand wheel, so that the turbine rotor is hoisted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810697198.1A CN110654967A (en) | 2018-06-29 | 2018-06-29 | Hoisting device and method for low-pressure turbine rotor of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810697198.1A CN110654967A (en) | 2018-06-29 | 2018-06-29 | Hoisting device and method for low-pressure turbine rotor of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110654967A true CN110654967A (en) | 2020-01-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810697198.1A Pending CN110654967A (en) | 2018-06-29 | 2018-06-29 | Hoisting device and method for low-pressure turbine rotor of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110654967A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04323192A (en) * | 1991-04-22 | 1992-11-12 | Hitachi Plant Eng & Constr Co Ltd | Lifting device of turbine rotor |
| CN206126664U (en) * | 2016-08-31 | 2017-04-26 | 天津甘泉集团有限公司 | Full through -flow pump rotor core hoist device |
| WO2017136428A1 (en) * | 2016-02-01 | 2017-08-10 | General Electric Company | Lifting device for a wind turbine rotor blade |
| CN206538097U (en) * | 2017-03-17 | 2017-10-03 | 北京天马起重吊索具有限责任公司 | A kind of 20 tons of electronic horizontal roll lifting appliances of single screw |
| CN207375595U (en) * | 2017-10-16 | 2018-05-18 | 山东电力建设第一工程公司 | A kind of steam turbine rotor lifting tool |
-
2018
- 2018-06-29 CN CN201810697198.1A patent/CN110654967A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04323192A (en) * | 1991-04-22 | 1992-11-12 | Hitachi Plant Eng & Constr Co Ltd | Lifting device of turbine rotor |
| WO2017136428A1 (en) * | 2016-02-01 | 2017-08-10 | General Electric Company | Lifting device for a wind turbine rotor blade |
| CN206126664U (en) * | 2016-08-31 | 2017-04-26 | 天津甘泉集团有限公司 | Full through -flow pump rotor core hoist device |
| CN206538097U (en) * | 2017-03-17 | 2017-10-03 | 北京天马起重吊索具有限责任公司 | A kind of 20 tons of electronic horizontal roll lifting appliances of single screw |
| CN207375595U (en) * | 2017-10-16 | 2018-05-18 | 山东电力建设第一工程公司 | A kind of steam turbine rotor lifting tool |
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Application publication date: 20200107 |
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