CN109676562A - A kind of aero-engine low-pressure turbine guide vane mounting device - Google Patents
A kind of aero-engine low-pressure turbine guide vane mounting device Download PDFInfo
- Publication number
- CN109676562A CN109676562A CN201811556983.1A CN201811556983A CN109676562A CN 109676562 A CN109676562 A CN 109676562A CN 201811556983 A CN201811556983 A CN 201811556983A CN 109676562 A CN109676562 A CN 109676562A
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- CN
- China
- Prior art keywords
- guide vane
- blade
- drive disk
- rod
- angle
- 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.)
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Classifications
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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
-
- 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
Abstract
This application discloses a kind of aero-engine low-pressure turbine guide vane mounting device, by, by guide vane and after the completion of obturage piece pre-assembly, the entirety of guide vane being installed on casing at a certain angle outside casing.It is first sequentially arranged in two blade positions semi-rings by guide vane in order when assembling, finally blade positions semi-ring is attached to form whole grade guide vane, the space constraints for solving last guide vane avoid the erection stress in 1 assembling process of guide vane and tap the impact force generated.
Description
Technical field
The application belongs to aero-engine mounting technology field, in particular to a kind of aero-engine low-pressure turbine directing vane
Piece mounting device.
Background technique
As depicted in figs. 1 and 2, certain type aero-engine low-pressure turbine guide vane 1 is evenly arranged on casing 100 by certain order
On, and the boss 101 of guide vane 1 is placed in the upper lower flange 102,103 of casing 10, guide vane 1 is fan-shaped, and two sides
There is certain inclination angle, is sealed between blade by obturaging piece.To guarantee that guide vane 1 can mount in the upper lower flange of casing 100,
Guide vane 1 need to be assembled with certain inclination angle, and in order to guarantee guider performance, it is desirable that guide vane gap distribution is uniform.
It is radially installed on casing one by one at a certain angle after piece is obturaged in the installation of guide vane unilateral side, last a piece of
It when guide vane is installed, needs to move surrounding vanes certain angle and taps guide vane and assemble, should be oriented in the process
Blade and guide vane are obturaged and there is larger erection stress between piece and casing, and tapping makes blade bear certain impact power,
Influence leaf longevity and assembling quality.In addition, guide vane gap is adjusted by naked eyes merely, it is difficult to guarantee uniformity.
Summary of the invention
The purpose of the application is above-mentioned to solve there is provided a kind of aero-engine low-pressure turbine guide vane mounting device
Any problem.
The technical solution of the application is: a kind of aero-engine low-pressure turbine guide vane mounting device comprising: pedestal
Component, the base assembly include chassis and the mandrel that is vertically set on chassis, and the base assembly is for entire mechanism
Positioning；Blade positions semi-ring, blade positions semi-ring are set to the outer peripheral two sides in chassis, are used to support guide vane；Support group
Part, the support component include the threaded rod being set in outside mandrel and the index dial fixed with threaded rod, the threaded rod and core
Axis in the axial direction on be slidably connected；Angle drive disk, angle drive disk are set in outside threaded rod, and angle fixed disk passes through pin shaft
Fixed with angular adjustment nut, angle drive disk connect with index dial with realize it is axial move synchronously, angularly keep, index dial with
Connecting rod connection, angular adjustment nut are threadedly engaged with threaded rod, are moved up with controlling index dial and connecting rod in the axis direction of mandrel
It is dynamic；Adjustable connecting-rod, the adjustable connecting-rod be fixed on support component upper connecting rod bracket and connect by pin shaft, adjustable connecting-rod is equipped with
Strip hole, so that adjustable connecting-rod can be moved along pin shaft；Blade connecting rod, the blade connecting rod two end respectively with adjustable connecting-rod and connecting rod
Connection, blade connecting rod and blade Boards wall, the blade clamping plate is for accommodating guide vane；Sliding hooks pawl, and the sliding hooks
Pawl setting and radially slidable adjustment on blade clamping plate, and limited by bolt and adjust the radial position for hooking pawl, it is oriented to clamping
Blade.
It in this application, further include height drive disk, height drive disk covers outside threaded rod, for keeping guide vane angle
Spend it is constant in the case where adjust axial position.
It in this application, further include deep groove ball bearing, the deep groove ball bearing is set to the inner cavity of height drive disk, zanjon
The screw thread collective effect of ball bearing and height drive disk, for moving the axial of support component that be converted to of height drive disk
It is dynamic, to drive synchronous axial movement in the state of keeping tilt angle of all guide vanes.
In this application, needle roller thrust bearing and bearing shell are equipped between the index dial and angle drive disk, for realizing
The axial direction of the index dial and angle drive disk moves synchronously, and when the rotation of angular drive disk, index dial is angularly remained unchanged.
It in this application, further include spring retainer component, spring retainer component connects adjustable connecting-rod and connecting rod rack, is used for
Keep the finite-state of guide vane.
It in this application, further include angular adjustment gasket and bearing adjusting gasket, angular adjustment gasket is arranged in threaded rod
On, for ensuring that guide vane has the first state of holding level, bearing adjusting gasket is arranged in angle drive disk and angle
Between adjusting nut, for ensuring that guide vane has the second state of predetermined inclination angle.
In this application, it has circumferentially been uniformly arranged blade card slot in blade positions semi-ring, the angle for stationary guide blades
To position, guarantee the uniformity of circumferential gap between guide vane.
In this application, the blade positions semi-ring is two and structure is identical, for being assembled into all guide vanes
The guide vane of the domain is spliced into after two semi-rings again, is difficult to fill since two sides blade is interfered for solving last a piece of blade
With the problem of.
The device of the application can be realized the unstressed assembly of guide vane, increase blade service life, improve assembly matter
Amount.Area measurement and blade adjustment can be exhausted when blade is pre-assembled, avoid blade from repeating to assemble and disassemble, improve assembly efficiency.
Detailed description of the invention
In order to illustrate more clearly of technical solution provided by the present application, attached drawing will be briefly described below.It is aobvious and easy
Insight, drawings discussed below are only some embodiments of the present application.
Fig. 1 is turborotor and casing connection schematic diagram.
Fig. 2 is turborotor structural schematic diagram.
Fig. 3 is the guide vane mounting device structural schematic diagram of the application.
Fig. 4 is the base assembly structural schematic diagram of the application.
Fig. 5 is the support component structural schematic diagram of the application.
Fig. 6 is the blade positions semi-ring edge enlarged drawing of the application.
Appended drawing reference:
1- guide vane, 2- blade card slot, 3- shadoof, 4- blade positions semi-ring, 5- blade clamping plate, 6- sliding hook pawl, 7-
Blade connecting rod, 8- adjustable connecting-rod, 9- connecting rod rack, 10- support component, 11- connecting rod, 12- angular adjustment gasket, 13- connecting rod are solid
Reservation, 14- index dial, 15- bearing shell, 16- position-limiting drum, 17- deep groove ball bearing, 18- suspension centre, 19- height handle, 20- height are driven
Moving plate, 21- bearing adjusting gasket, 22- angle drive disk, 23- angle handle, 24- pin shaft, 25- needle roller thrust bearing, the angle 26-
Spend adjusting nut, 27- pin shaft, 28- positioning pin, 29- spring retainer component, 30- spring-loaded plunger, 31- gag lever post, 32- pedestal group
Part, 33- pin shaft, 34- screw, the chassis 35-, 36- disc, 37 mandrels, 38- threaded rod, 39- index dial.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.
In order to eliminate the erection stress and impact force, guarantee impeller clearance uniformity in guide vane installation process, realize
Unstressed assembly improves leaf longevity and assembling quality.
The application by outside casing by guide vane and after the completion of obturage piece pre-assembly, by the whole of guide vane 1
Body is installed at a certain angle on casing 100.It is first sequentially arranged at two blade positioning by guide vane 1 in order when assembling
On semi-ring 4, finally blade positions semi-ring 4 is attached to form whole grade guide vane 1, solves the space of last guide vane 1
Restricted problem avoids the erection stress in 1 assembling process of guide vane and taps the impact force generated.
Since the installation of guide vane 1 needs to guarantee that tilt angle, guide vane 1 are circumferentially arranged sequence, guide vane 1 and machine
The opposite angular position of casket 100, the gap uniformity of guide vane 1, guide vane 1 and casing 100 flange matching relationship.Its
In, tilt angle is realized by link mechanism, and 1 distributing order of guide vane is completed when pre-assembled, and angular position passes through casing
Offset hole is fixed, and the gap of guide vane 1 is guaranteed by circumferentially uniformly distributed positioning pin, passes through link mechanism with flange matching relationship
Axial position adjustment structure is cooperated to realize.
The application has generally been broadly divided into link mechanism, guide vane clamping device and axial position adjustment mechanism.Its
In, link mechanism requires that guide vane 1 can be made to reach horizontality, and can actively reach and be maintained at heeling condition.To avoid
Guide vane and the interference of casing flange lead to not install or damage guide vane when installation, it is desirable that every group of 1 angle of guide vane
For individual soft readjustment, during tilting to level, can passive adaptation casing 100 position of guide vane 1 is limited,
Meanwhile angular adjustment needs to limit in view of domain guide vane diameter dimension, avoids generating interference between guide vane 1.It leads
1 gravity of guide vane is overcome to grip to realize by the stiction generated is clamped to blade 1.Axial position relies primarily on
Lifting and screw thread realize that stepless changing is realized.The guide vane mounting device of the application is referring to Fig. 3 to Fig. 6, wherein first state
For horizontality, guide vane clamping plate is in level under the state；Second state is heeling condition, and guide vane clamping plate is in spy
Constant inclination rake angle.
Specifically, the aero-engine low-pressure turbine guide vane mounting device of the application includes: base assembly 32, packet
The mandrel 37 for including chassis 35 and being vertically set on chassis 35, base assembly 32 are used for the positioning of entire mechanism；Blade positioning half
Ring 4 is set to the outer peripheral two sides in chassis 35, is used to support guide vane 1；Support component 10 includes being set in outside mandrel 35
Threaded rod 38 and the index dial 39 fixed with threaded rod 38, threaded rod 38 and mandrel 37 in the axial direction on be slidably connected；Angle
Drive disk 22 is set in outside threaded rod 38, and angle fixed disk 22 is fixed by pin shaft 24 and angular adjustment nut 26, angle driving
Disk 22 connect with index dial 14 with realize it is axial move synchronously, angularly keep, index dial 14 is connect with connecting rod 11, angular adjustment spiral shell
Mother 26 is threadedly engaged with threaded rod 38, is moved on the axis direction of mandrel 37 with controlling index dial 14 and connecting rod 11；Adjustable company
Bar 8 is connect with 10 upper connecting rod bracket 9 of support component is fixed on by pin shaft, and adjustable connecting-rod 8 is equipped with strip hole, so that adjustable company
Bar 8 can be moved along pin shaft；7 both ends of blade connecting rod are connect with adjustable connecting-rod 8 and connecting rod 11 respectively, blade connecting rod 7 and blade clamping plate 5
Fixed, blade clamping plate 5 is for accommodating guide vane 1；Sliding hooks the setting of pawl 6 and radially slidable adjustment on blade clamping plate 5, and logical
It crosses bolt and limits the radial position for adjusting and hooking pawl, to clamp guide vane 1.
Further include height drive disk 20 in the device of the application, 20 sets of height drive disk outside threaded rod 38, for keeping
Axial position is adjusted in the isogonal situation of guide vane.
It further include deep groove ball bearing 17 in the device of the application, deep groove ball bearing 17 is set to the interior of height drive disk 20
Chamber, the screw thread collective effect of deep groove ball bearing 17 and height drive disk 20, for the rotation of height drive disk 20 to be converted to branch
The axial movement of support component 10, to drive synchronous axial movement in the state of keeping tilt angle of all guide vanes 1.
In the device of the application, needle roller thrust bearing 25 and bearing shell 15 are equipped between index dial 14 and angle drive disk 22,
It is moved synchronously for realizing index dial 14 and the axial direction of angle drive disk 22, and when the rotation of angular drive disk 22, index dial 14
Angularly remain unchanged.
It further include spring retainer component 29 in the device of the application, spring retainer component 29 connects adjustable connecting-rod 8 and connecting rod
Bracket 9, for keeping the finite-state of guide vane 1.
It further include angular adjustment gasket 12 and bearing adjusting gasket 21 in the device of the application, angular adjustment gasket 12 is arranged
On threaded rod 38, for ensuring that guide vane 1 has the first state of holding level, bearing adjusting gasket 21 is arranged in angle
Between drive disk 22 and angular adjustment nut 26, for ensuring that guide vane 1 has the second state of predetermined inclination angle.
In the device of the application, it circumferentially is uniformly arranged blade card slot 2 in blade positions semi-ring 4, has been used for fixed guide leaf
The angular position of piece 1 guarantees the uniformity of circumferential gap between guide vane 1.
In the device of the application, blade positions semi-ring 4 is two and structure is identical, for assembling all guide vanes 1
For the guide vane for being spliced into the domain after two semi-rings again.
The guide vane mounting device of the application mainly includes the following steps:
1, guide vane is pre-assembled:
The guide vane 1 for obturaging piece will be installed to be mounted in 4 groove of guide vane positions semi-ring.Among guide vane
Boss is aligned in the groove of guide vane card slot 2, moves up shadoof 3, the automatic fixed mandril axial position of spring-loaded plunger 30, from
And stationary guide blades angular position, guarantee axial being evenly distributed with property.Rotation height handle 19 makes support component 10 and coupled
Link mechanism etc. keeps former posture to synchronize and rises to highest point；Angle handle 23 is rotated, angle drive disk 22 is made to be moved to highest
Place, i.e. horizontality.It will partially lift to guide vane top, slowly fallen in bearing 17 and base assembly 32 in tooling
Mandrel 36 contacts, and confirmation spring retainer component 28 is in state 1, otherwise torsional spring limit assembly 29；Unclamping screw 34 will lead
Pawl 6 is hooked to blade to separate with guide vane clamping plate 5, rotation height handle 10, make whole slowly fall until connecing with guide vane
Touching, tightening screw makes to hook the clamping guide vane of pawl 6.
2, guide vane inclination and handling:
Shadoof 3 is pushed, guide vane card slot 2 is made to bounce back.Slow rotation height handle 19 make all guide vanes 1 slowly on
It rises, while spring retainer component 29 is rotated 90 °；Suspension centre 18 is sling with suspender, while slow rotational angle handle 23 makes and angle
The fixed angular adjustment nut 26 of degree drive disk 22 is displaced downwardly to low level, since adjustable connecting-rod 8 is in vertical shape under the action of the spring
State, and it is in adjustable longest dimension under the effect of gravity, and the relative position of 2 pin shafts 27 is fixed in one group of connecting rod, because
This, connecting rod 11 and guide vane connecting rod 7 are by corresponding sports to its unique special angle.Side length and angle are defined, i.e.,
The requirement of guide vane inclination angle and radial position requirement can be met.Emphasis be determine link mechanism size, both avoided guide vane it
Between interference also need to meet tilt angle requirement.
3, guide vane is installed to casing:
Guide vane is hoisted to right above casing, is slowly fallen, until bearing 17 is contacted with assembly bench, slowly rotation is high
Handle 19 is spent, makes guide vane keep inclination is whole to move down, while positioning pin 28 being aligned with casing hole.When guide vane 1 moves
It moves to casing lower flange Fig. 1, slow rotational angle handle 23 makes guide vane close to casing.Gently guide vane is pulled to make
It is contacted with casing lower flange.Rotation height handle 19 moves down guide vane, while rotational angle handle 23 makes guide vane
Restore horizontal, until guide vane is mounted in casing.
The guide vane mounting device of the application can be realized the unstressed assembly of guide vane, increases guide vane and uses
Service life improves assembling quality.Area measurement and guide vane adjustment can be exhausted when guide vane is pre-assembled, avoid being oriented to
Blade repeats to assemble and disassemble, and improves assembly efficiency.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (8)
1. a kind of aero-engine low-pressure turbine guide vane mounting device, which is characterized in that including
Base assembly (32), the base assembly (32) include chassis (35) and the mandrel that is vertically set on chassis (35)
(37), the base assembly (32) is used for the positioning of entire mechanism；
Blade positions semi-ring (4), blade positions semi-ring (4) are set to chassis (35) outer peripheral two sides, are used to support directing vane
Piece (1)；
Support component (10), the support component (10) include being set in the threaded rod (38) and and threaded rod of mandrel (35) outside
(38) fixed index dial (39), the threaded rod (38) and mandrel (37) in the axial direction on be slidably connected；
Angle drive disk (22), angle drive disk (22) are set in threaded rod (38) outside, and angle fixed disk (22) passes through pin shaft
(24) fixed with angular adjustment nut (26), angle drive disk (22) connect with index dial (14) with realize axial direction move synchronously,
Angular to keep, index dial (14) is connect with connecting rod (11), and angular adjustment nut (26) is threadedly engaged with threaded rod (38), with control
Index dial (14) and connecting rod (11) move on the axis direction of mandrel (37)；
Adjustable connecting-rod (8), the adjustable connecting-rod (8) be fixed on support component (10) upper connecting rod bracket (9) and connect by pin shaft,
Adjustable connecting-rod (8) is equipped with strip hole, so that adjustable connecting-rod (8) can be moved along pin shaft；
Blade connecting rod (7), blade connecting rod (7) both ends are connect with adjustable connecting-rod (8) and connecting rod (11) respectively, blade connecting rod
(7) fixed with blade clamping plate (5), the blade clamping plate (5) is for accommodating guide vane (1)；
Sliding hooks pawl (6), and the sliding hooks pawl (6) setting and radially slidable adjustment on blade clamping plate (5), and passes through bolt limit
Section of setting the tone hooks the radial position of pawl, to clamp guide vane (1).
2. device as described in claim 1, which is characterized in that further include height drive disk (20), height drive disk (20) set
Threaded rod (38) outside, adjust axial position in the isogonal situation of guide vane for keeping.
3. device as claimed in claim 2, which is characterized in that further include deep groove ball bearing (17), the deep groove ball bearing
(17) it is set to the inner cavity of height drive disk (20), the screw thread collective effect of deep groove ball bearing (17) and height drive disk (20),
For the rotation of height drive disk (20) to be converted to the axial movement of support component (10), to drive all guide vanes (1)
Synchronous axial movement in the state of keeping tilt angle.
4. device as claimed in claim 3, which is characterized in that be equipped between the index dial (14) and angle drive disk (22)
Needle roller thrust bearing (25) and bearing shell (15), for realizing the index dial (14) fortune synchronous with the axial direction of angle drive disk (22)
It is dynamic, and when angular drive disk (22) rotation, index dial (14) angularly remains unchanged.
5. device as claimed in claim 4, which is characterized in that further include spring retainer component (29), spring retainer component
(29) adjustable connecting-rod (8) and connecting rod rack (9) are connected, for keeping the finite-state of guide vane (1).
6. device as claimed in claim 5, which is characterized in that further include angular adjustment gasket (12) and bearing adjusting gasket
(21), angular adjustment gasket (12) is arranged on threaded rod (38), keeps horizontal first for ensuring that guide vane (1) has
State, bearing adjusting gasket (21) is arranged between angle drive disk (22) and angular adjustment nut (26), for ensuring to be oriented to
Blade (1) has the second state of predetermined inclination angle.
7. device as claimed in claim 6, which is characterized in that be circumferentially uniformly arranged blade card in blade positions semi-ring (4)
Slot (2) is used for the angular position of stationary guide blades (1), guarantees the uniformity of circumferential gap between guide vane (1).
8. device as claimed in claim 7, which is characterized in that the blade positions semi-ring (4) is two and structure is identical, is used
It is spliced into the guide vane of the domain again after all guide vanes (1) are assembled into two semi-rings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811556983.1A CN109676562A (en) | 2018-12-19 | 2018-12-19 | A kind of aero-engine low-pressure turbine guide vane mounting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811556983.1A CN109676562A (en) | 2018-12-19 | 2018-12-19 | A kind of aero-engine low-pressure turbine guide vane mounting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109676562A true CN109676562A (en) | 2019-04-26 |
Family
ID=66186329
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811556983.1A Withdrawn CN109676562A (en) | 2018-12-19 | 2018-12-19 | A kind of aero-engine low-pressure turbine guide vane mounting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109676562A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110103176A (en) * | 2019-06-19 | 2019-08-09 | 哈尔滨锅炉厂有限责任公司 | A kind of burner blades assembly device |
| CN110216623A (en) * | 2019-05-23 | 2019-09-10 | 中国人民解放军第五七一九工厂 | A kind of engine turbine blade quick decomposing device and method |
| CN112207760A (en) * | 2019-07-09 | 2021-01-12 | 中国航发商用航空发动机有限责任公司 | Vertical low-pressure turbine unit assembling device and assembling method thereof |
| CN113894733A (en) * | 2020-06-22 | 2022-01-07 | 中国航发商用航空发动机有限责任公司 | Integral decomposition method and tool for fan outlet guide vane assembly |
| CN113894732A (en) * | 2020-06-22 | 2022-01-07 | 中国航发商用航空发动机有限责任公司 | Decomposition process of fan stator assembly |
| CN113928721A (en) * | 2021-09-24 | 2022-01-14 | 中国航发沈阳发动机研究所 | Protecting jacket for blades and comb teeth of aero-engine |
| CN115070665A (en) * | 2021-03-15 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | Mounting tool and mounting method for turbine disc baffle ring |
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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 |
| CN105452617A (en) * | 2013-07-15 | 2016-03-30 | 斯奈克玛 | Dismantling device for blades and corresponding dismantling method |
| CN107584273A (en) * | 2017-10-23 | 2018-01-16 | 中国航发成都发动机有限公司 | A kind of engine turbine blade integral installation and provision for disengagement and method |
| 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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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105452617A (en) * | 2013-07-15 | 2016-03-30 | 斯奈克玛 | Dismantling device for blades and corresponding dismantling method |
| CN107584273A (en) * | 2017-10-23 | 2018-01-16 | 中国航发成都发动机有限公司 | A kind of engine turbine blade integral installation and provision for disengagement and method |
| 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 |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110216623A (en) * | 2019-05-23 | 2019-09-10 | 中国人民解放军第五七一九工厂 | A kind of engine turbine blade quick decomposing device and method |
| CN110216623B (en) * | 2019-05-23 | 2024-01-02 | 中国人民解放军第五七一九工厂 | Quick decomposing device and method for turbine blade of engine |
| CN110103176A (en) * | 2019-06-19 | 2019-08-09 | 哈尔滨锅炉厂有限责任公司 | A kind of burner blades assembly device |
| CN112207760A (en) * | 2019-07-09 | 2021-01-12 | 中国航发商用航空发动机有限责任公司 | Vertical low-pressure turbine unit assembling device and assembling method thereof |
| CN112207760B (en) * | 2019-07-09 | 2022-04-26 | 中国航发商用航空发动机有限责任公司 | Vertical low-pressure turbine unit assembling device and assembling method thereof |
| CN113894733A (en) * | 2020-06-22 | 2022-01-07 | 中国航发商用航空发动机有限责任公司 | Integral decomposition method and tool for fan outlet guide vane assembly |
| CN113894732A (en) * | 2020-06-22 | 2022-01-07 | 中国航发商用航空发动机有限责任公司 | Decomposition process of fan stator assembly |
| CN115070665A (en) * | 2021-03-15 | 2022-09-20 | 中国航发商用航空发动机有限责任公司 | Mounting tool and mounting method for turbine disc baffle ring |
| CN115070665B (en) * | 2021-03-15 | 2023-10-31 | 中国航发商用航空发动机有限责任公司 | Mounting tool and mounting method for turbine disk baffle ring |
| CN113928721A (en) * | 2021-09-24 | 2022-01-14 | 中国航发沈阳发动机研究所 | Protecting jacket for blades and comb teeth of aero-engine |
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Application publication date: 20190426 |