CN109600003A - Engine rotor blade disassemblerassembler - Google Patents
Engine rotor blade disassemblerassembler Download PDFInfo
- Publication number
- CN109600003A CN109600003A CN201811550242.2A CN201811550242A CN109600003A CN 109600003 A CN109600003 A CN 109600003A CN 201811550242 A CN201811550242 A CN 201811550242A CN 109600003 A CN109600003 A CN 109600003A
- Authority
- CN
- China
- Prior art keywords
- blade
- central axis
- compression bar
- chassis
- rotor blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K15/00—Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines
- H02K15/02—Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines of stator or rotor bodies
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K15/00—Methods or apparatus specially adapted for manufacturing, assembling, maintaining or repairing of dynamo-electric machines
- H02K15/0006—Disassembling, repairing or modifying dynamo-electric machines
Abstract
This application provides a kind of engine rotor blade disassemblerassemblers, comprising: chassis；Blade support ring is fixedly connected with the chassis；Central axis perpendicular to the chassis and is set at the center on the chassis；Rotor supports disk is movably arranged on the central axis, and can be moved back and forth along the extending direction of the central axis；Blade removable component is set on the central axis, and can be rotated centered on the central axis.
Description
Technical field
This application involves aero-engine technology fields, specifically provide a kind of engine rotor blade disassemblerassembler.
Background technique
In the prior art, blade dismounting is had the following disadvantages using the method for tapping listrium: security risk: dismounting
Blade is using the Impulsive load mode pounded is struck, although using is this flexible material tool of rubber hammer, carries if tapping
Lotus is excessive, still may cause listrium deformation or other damages；Integral shroud side set: when operator taps, blade is by quick
Impact, adjacent blades may move different axial distances, when distance has big difference, integral shroud side set will occur, at this time
It not only may cause integral shroud damage and the required work of packing again also reduce working efficiency；Assembling quality: due to tapping mode
Under vane stress dispersion degree it is big, assembled state is unstable, and inside is easy that there are stress, will affect assembly matter to a certain extent
Amount.
Summary of the invention
In order to solve the above-mentioned technical problem at least one, this application provides a kind of engine rotor blade disassemblerassembler,
It include: chassis；Blade support ring is fixedly connected with the chassis；Central axis perpendicular to the chassis and is set to the chassis
Center at；Rotor supports disk is movably arranged on the central axis, and can along the central axis extending direction it is past
Multiple movement；Blade removable component is set on the central axis, and can be rotated centered on the central axis.
In some embodiments, multiple support rods, the blade support ring and the support rod are provided on the chassis
It is fixedly connected.
In some embodiments, it is arranged with external thread sleeve on the central axis, offers and has on the rotor supports disk
The centre bore of internal screw thread, the rotor supports disk are threadedly coupled with the external thread sleeve, are fixedly connected on the chassis anti-
It ships and resell on another market, the stop pin passes through the rotor supports disk to prevent the rotor supports disk from rotating.
In some embodiments, tommy bar is provided on the external thread sleeve.
In some embodiments, the outer diameter of the rotor supports disk is less than or equal to the internal diameter of the blade support ring.
In some embodiments, blade removable component includes: compression bar support sleeve, is sheathed on the central axis；Compression bar prolongs
Direction is stretched along the radial direction of the compression bar support sleeve, is fixedly connected with the compression bar support sleeve；Wheel assembly is dismounted, slideably
It is set on the compression bar, and can be moved back and forth along the extending direction of the compression bar.
In some embodiments, the end of the compression bar is fixedly connected with push rod.
In some embodiments, it is provided with clamp nut on the central axis, for compressing the compression bar support sleeve.
In some embodiments, dismounting wheel assembly includes: dismounting strut, is connected on the compression bar, and can be along described
The extending direction of compression bar moves back and forth；Dismounting wheel, is connect by shaft with the dismounting strut.
In some embodiments, multiple mounting holes are offered on the rotor supports disk, are arranged in multiple mounting holes
There is positioning pin.
In engine rotor blade disassemblerassembler provided by the embodiments of the present application, replaced in such a way that idler wheel pushes load existing
Some, which is struck, pounds, and avoids the excessive impact force being likely to occur during dress point, and parts safety is obviously improved.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of engine rotor blade disassemblerassembler provided by the embodiments of the present application；
Fig. 2 is the schematic diagram of rotor blade installation provided by the embodiments of the present application；
Fig. 3 is the schematic diagram of rotor blade disassembly provided by the embodiments of the present application.
Wherein:
10, chassis；11, support rod；12, stop pin；20, blade support ring；30, central axis；31, external thread sleeve；32, it pulls
Bar；33, clamp nut；40, rotor supports disk；41, positioning pin；50, blade removable component；51, compression bar support sleeve；52, compression bar；
53, wheel assembly is dismounted；531, strut is dismounted；532, dismounting wheel；54, push rod.
Specific embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining related application, rather than the restriction to this application.It also should be noted that in order to
Convenient for description, part relevant to the application is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
It should be noted that in the description of the present application, term " center ", "upper", "lower", "left", "right", "vertical",
The direction of the instructions such as "horizontal", "inner", "outside" or the term of positional relationship are direction based on the figure or positional relationship, this
It is intended merely to facilitate description, rather than indication or suggestion described device or element must have a particular orientation, with specific
Orientation construction and operation, therefore should not be understood as the limitation to the application.In addition, term " first ", " second " are only used for describing
Purpose is not understood to indicate or imply relative importance.
In addition it is also necessary to explanation, in the description of the present application unless specifically defined or limited otherwise, term " peace
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.To those skilled in the art, it can understand that above-mentioned term exists as the case may be
Concrete meaning in the application.
Fig. 1 is the structural schematic diagram of engine rotor blade disassemblerassembler provided by the embodiments of the present application, as shown in Figure 1,
Engine rotor blade disassemblerassembler includes chassis 10, blade support ring 20, central axis 30, rotor supports disk 40 and blade dismounting
Component 50.
Wherein, blade support ring 20 is fixedly connected with chassis 10.Optionally, multiple support rods are provided on chassis 10
11, blade support ring 20 is fixedly connected with support rod 11, and including but not limited to, multiple support rods 11 can be on chassis 10 along it
Circumferential direction is evenly distributed, and is also possible on chassis 10 can also be and submit on chassis 10 along the even distribution of its circumferential asymmetry
It is distributed wrongly.
Central axis 30, perpendicular to chassis 10 and is set at the center on chassis 10, and rotor supports disk 40 is movably disposed
In on central axis 30, and can be moved back and forth along the extending direction of central axis 30.
Optionally, it is arranged with external thread sleeve 31 on central axis 30, is offered on rotor supports disk 40 in band internal thread
Heart hole, rotor supports disk 40 are threadedly coupled with external thread sleeve 31, and stop pin 12 is fixedly connected on chassis 10, and stop pin 12 is worn
Rotor supports disk 40 is crossed to rotate to prevent the sub- support plate 40 of rotation stop.
In the present embodiment, by rotating external thread sleeve 31, since external thread sleeve 31 is threadedly coupled with rotor supports disk 40,
Since stop pin 12 limits the rotation of rotor supports disk 40, so that rotor supports disk 40 can be reciprocal on external thread sleeve 31
Movement.
, it is understood that for example, rotor supports disk 40 is along straight up when being rotated in the clockwise direction external thread sleeve 31
Direction movement, then, in the counterclockwise direction rotate external thread sleeve 31 when, rotor supports disk 40 can then be transported along vertically downward direction
It is dynamic.
In order to facilitate rotation external thread sleeve 31, be welded with tommy bar 32 on external thread sleeve 31, the quantity of tommy bar 32 include but
It is not limited to two.
Blade removable component 50 is set on central axis 30, and can be rotated centered on central axis 30.Optionally, blade
Removable component 50 includes: that compression bar support sleeve 51, compression bar 52 and dismounting wheel assembly 53, compression bar support sleeve 51 are sheathed on central axis 30
On, the extending direction of compression bar 52 along compression bar support sleeve 51 radial direction and be fixedly connected with compression bar support sleeve 51, dismount wheel group
Part 53 is slidably disposed on compression bar 52, and can be moved back and forth along the extending direction of compression bar 52.
As an alternative embodiment, compression bar support sleeve 51 and 30 clearance fit of central axis, so that pressure
Bar support sleeve 51 can make circumferential rotation on central axis 30.
As another optional embodiment, compression bar support sleeve 51 is threadedly engaged with central axis 30 and connect, and can also make
It obtains compression bar support sleeve 51 and makees circumferential rotation on central axis 30.
As another optional embodiment, compression bar 52 is connected on compression bar support sleeve 51 by fixed pin shaft, compression bar
52 can rotate along fixed pin shaft.
In order to save the active force for pushing compression bar 52, it can be fixedly connected with push rod 54 in the end of compression bar 52, to increase pressure
The length of the arm of force of bar 52, push rod 54 can be adjusted according to actual installation space, or according to the physical strength of operator
To be adjusted.
Optionally, clamp nut 33 is provided on central axis 30, for compressing compression bar support sleeve 51, to prevent compression bar branch
Support set 51 during rotation, falls off from central axis 30.
Dismounting wheel assembly 53 includes dismounting strut 531 and dismounting wheel 532, and dismounting strut 531 is connected on compression bar 52, and energy
Enough extending directions along compression bar 52 move back and forth, and dismounting wheel 532 is connect by shaft with dismounting strut 531.
In some embodiments, the outer diameter of rotor supports disk 40 is less than or equal to the internal diameter of blade support ring 20.
In some embodiments, multiple mounting holes are offered on rotor supports disk 40, and positioning is provided in multiple mounting holes
Pin 41, with the various sizes of rotor of fixation.
Fig. 2 is the schematic diagram of rotor blade installation provided by the embodiments of the present application, as shown in Fig. 2, assembling in rotor blade
When, rotor is placed on rotor supports disk 40, and fixed by positioning pin 41, blade is placed on blade support ring 20,
By rotating tommy bar 32, so that rotor supports disk 40 moves upwards, when rotor is close to the blade tip position of blade, under
Moulded rod 52, so that the blade tip of blade can be pressed on rotor by dismounting wheel 532, and by rotation compression bar 52, thus
Multiple blades on blade support ring 20 can be pressed on rotor.
The blade tip of blade is being pressed on rotor after the distance of one end, is continuing to rotate tommy bar 32, rotor is made to rise one section again
Then distance repeats above-mentioned operation, continue for the blade tip of blade to be pressed on rotor, continues to repeat above-mentioned operation, until
Blade is fully pressed on rotor.
Fig. 3 is the schematic diagram of rotor blade disassembly provided by the embodiments of the present application, as shown in figure 3, in disassembly rotor blade
When, vaned rotor will be assembled fixed on rotor supports disk 40, by rotating tommy bar 32 so that rotor rise one section away from
From by lower moulded rod 52, so that dismounting wheel 532 can extrude the blade tip of blade from rotor, and by rotating pressure
Bar 52, so as to extrude multiple blades on blade support ring 20 from rotor.
After the blade tip of blade is extruded a distance, tommy bar 32 is continued to rotate, so that rotor is risen a distance again, then
Repeat above-mentioned operation, continue to extrude the blade tip of blade from rotor, continue to repeat above-mentioned operation, until blade completely from
It is extruded on rotor.
So far, it has been combined preferred embodiment shown in the drawings and describes the technical solution of the application, still, this field
Technical staff is it is easily understood that the protection scope of the application is expressly not limited to these specific embodiments.Without departing from this
Under the premise of the principle of application, those skilled in the art can make equivalent change or replacement to the relevant technologies feature, these
Technical solution after change or replacement is fallen within the protection scope of the application.
Claims (10)
1. a kind of engine rotor blade disassemblerassembler characterized by comprising
Chassis (10)；
Blade support ring (20) is fixedly connected with the chassis (10)；
Central axis (30) perpendicular to the chassis (10) and is set at the center of the chassis (10)；
Rotor supports disk (40) is movably arranged on the central axis (30), and being capable of prolonging along the central axis (30)
Stretch direction reciprocating motion；
Blade removable component (50) is set on the central axis (30), and can be rotated centered on the central axis (30).
2. engine rotor blade disassemblerassembler according to claim 1, which is characterized in that be arranged on the chassis (10)
Have multiple support rods (11), the blade support ring (20) is fixedly connected with the support rod (11).
3. engine rotor blade disassemblerassembler according to claim 1, which is characterized in that covered on the central axis (30)
Equipped with external thread sleeve (31), band internal thread centre bore, the rotor supports disk are offered on the rotor supports disk (40)
(40) it is threadedly coupled with the external thread sleeve (31), stop pin (12), the anti-rotation is fixedly connected on the chassis (10)
Pin (12) passes through the rotor supports disk (40) to prevent the rotor supports disk (40) from rotating.
4. engine rotor blade disassemblerassembler according to claim 3, which is characterized in that on the external thread sleeve (31)
It is provided with tommy bar (32).
5. engine rotor blade disassemblerassembler according to claim 1, which is characterized in that the rotor supports disk (40)
Outer diameter be less than or equal to the blade support ring (20) internal diameter.
6. engine rotor blade disassemblerassembler according to claim 1, which is characterized in that blade removable component (50) packet
It includes:
Compression bar support sleeve (51) is sheathed on the central axis (30)；
Compression bar (52), extending direction are fixed along the radial direction of the compression bar support sleeve (51) with the compression bar support sleeve (51)
Connection；
It dismounts wheel assembly (53), is slidably disposed on the compression bar (52), and can be along the extending direction of the compression bar (52)
It moves back and forth.
7. engine rotor blade disassemblerassembler according to claim 6, which is characterized in that the end of the compression bar (52)
It is fixedly connected with push rod (54).
8. engine rotor blade disassemblerassembler according to claim 6, which is characterized in that set on the central axis (30)
Clamp nut (33) are equipped with, for compressing the compression bar support sleeve (51).
9. engine rotor blade disassemblerassembler according to claim 6, which is characterized in that dismounting wheel assembly (53) packet
It includes:
It dismounts strut (531), is connected on the compression bar (52), and can back and forth be transported along the extending direction of the compression bar (52)
It is dynamic；
Dismounting wheel (532), is connect by shaft with the dismounting strut (531).
10. engine rotor blade disassemblerassembler according to claim 1, which is characterized in that the rotor supports disk
(40) multiple mounting holes are offered on, and positioning pin (41) are provided in multiple mounting holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811550242.2A CN109600003B (en) | 2018-12-18 | 2018-12-18 | Engine rotor blade dismounting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811550242.2A CN109600003B (en) | 2018-12-18 | 2018-12-18 | Engine rotor blade dismounting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109600003A true CN109600003A (en) | 2019-04-09 |
| CN109600003B CN109600003B (en) | 2020-11-06 |
Family
ID=65962651
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811550242.2A Active CN109600003B (en) | 2018-12-18 | 2018-12-18 | Engine rotor blade dismounting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109600003B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112975335A (en) * | 2019-12-16 | 2021-06-18 | 中国航发商用航空发动机有限责任公司 | Turbine blade mounting system and method |
| CN113021247A (en) * | 2019-12-24 | 2021-06-25 | 中国航发商用航空发动机有限责任公司 | Press-fitting device and installation method of turbine rotor |
| CN114622955A (en) * | 2020-12-14 | 2022-06-14 | 中国航发商用航空发动机有限责任公司 | Mounting device and mounting method for turbine disk blades |
| CN114718658A (en) * | 2021-01-05 | 2022-07-08 | 中国航发商用航空发动机有限责任公司 | Tool and method for controlling width of baffle ring installation groove |
| CN114762926A (en) * | 2021-01-13 | 2022-07-19 | 中国航发商用航空发动机有限责任公司 | Turbine blade removal tool and method |
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| US5918356A (en) * | 1996-05-02 | 1999-07-06 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Tools for mounting a turbo aero engine distributor |
| CN1607319A (en) * | 2003-10-16 | 2005-04-20 | Snecma发动机公司 | Apparatus for mounting blade on turbine rotor plate in turbo machine |
| CN203109894U (en) * | 2013-04-08 | 2013-08-07 | 淮南矿业(集团)有限责任公司 | Special tool for dismantling blades of electric machine |
| US20170291724A1 (en) * | 2016-04-12 | 2017-10-12 | Sikorsky Aircraft Corporation | Systems and methods for separating rotor blade cuffs from rotor blade bodies |
| CN107738223A (en) * | 2017-11-13 | 2018-02-27 | 山东太古飞机工程有限公司 | The dismounting auxiliary mould of aircraft engine first order stator blade radome fairing |
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2018
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| US5918356A (en) * | 1996-05-02 | 1999-07-06 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Tools for mounting a turbo aero engine distributor |
| CN1607319A (en) * | 2003-10-16 | 2005-04-20 | Snecma发动机公司 | Apparatus for mounting blade on turbine rotor plate in turbo machine |
| CN203109894U (en) * | 2013-04-08 | 2013-08-07 | 淮南矿业(集团)有限责任公司 | Special tool for dismantling blades of electric machine |
| US20170291724A1 (en) * | 2016-04-12 | 2017-10-12 | Sikorsky Aircraft Corporation | Systems and methods for separating rotor blade cuffs from rotor blade bodies |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112975335A (en) * | 2019-12-16 | 2021-06-18 | 中国航发商用航空发动机有限责任公司 | Turbine blade mounting system and method |
| CN113021247A (en) * | 2019-12-24 | 2021-06-25 | 中国航发商用航空发动机有限责任公司 | Press-fitting device and installation method of turbine rotor |
| CN113021247B (en) * | 2019-12-24 | 2022-07-19 | 中国航发商用航空发动机有限责任公司 | Press-fitting device and installation method of turbine rotor |
| CN114622955A (en) * | 2020-12-14 | 2022-06-14 | 中国航发商用航空发动机有限责任公司 | Mounting device and mounting method for turbine disk blades |
| CN114718658A (en) * | 2021-01-05 | 2022-07-08 | 中国航发商用航空发动机有限责任公司 | Tool and method for controlling width of baffle ring installation groove |
| CN114762926A (en) * | 2021-01-13 | 2022-07-19 | 中国航发商用航空发动机有限责任公司 | Turbine blade removal tool and method |
| CN114762926B (en) * | 2021-01-13 | 2023-08-04 | 中国航发商用航空发动机有限责任公司 | Turbine blade removal tool and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109600003B (en) | 2020-11-06 |
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