CN207358601U - A kind of aero-engine low-pressure turbine director assembly processing unit (plant) - Google Patents
A kind of aero-engine low-pressure turbine director assembly processing unit (plant) Download PDFInfo
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- CN207358601U CN207358601U CN201721439308.1U CN201721439308U CN207358601U CN 207358601 U CN207358601 U CN 207358601U CN 201721439308 U CN201721439308 U CN 201721439308U CN 207358601 U CN207358601 U CN 207358601U
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- pressure turbine
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Abstract
It the utility model is related to aero-engine and repair manufacturing technology field, and in particular to a kind of aero-engine low-pressure turbine director assembly processing unit (plant).Aero-engine low-pressure turbine director assembly processing unit (plant) provided by the utility model, including fixed seat, fixture and pressing device, the fixture is detachably connected by pressing device and the fixed seat, when two machined surfaces so on the upside of to low-pressure turbine director assembly are processed, fixture is pulled down from fixed seat, using fixture as supporting surface, lathe tool carries out turnery processing to two machined surfaces on the upside of part；When two machined surfaces are processed on the downside of to part, supporting surface is used as using the one end of the fixed seat away from the fixture, and by pressing device by the clamp pressing in the fixed seat, then the machined surface on the downside of part is processed by lathe tool, it can realize that centering benchmark, the precision higher of processing are unified in the processing to aero-engine low-pressure turbine director assembly both direction.
Description
Technical field
It the utility model is related to aero-engine and repair manufacturing technology field, and in particular to a kind of aero-engine low pressure whirlpool
Take turns director assembly processing unit (plant).
Background technology
When repairing the low-pressure turbine director assembly of certain type aero-engine, it is necessary to be carried out in both direction in component
Processing, since assembly housing is thin-walled parts, operating ambient temperature is high, causes component strain serious, influences engine overhaul and add
Working medium amount.New product is to design two sets of frocks to be processed when manufacturing, and there are frock cost height, the part of deformation cannot be carried out
The problems such as precise positioning and fixture datum disunity.
Utility model content
(1) technical problem to be solved in the utility model is：Existing low-pressure turbine director assembly needs during fabrication
Design two sets of frocks to be processed, there are frock cost height, precise positioning and fixture datum cannot be carried out to the part of deformation
Skimble-scamble problem.
(2) technical solution
In order to solve the above-mentioned technical problem, the utility model provides a kind of aero-engine low-pressure turbine director assembly and adds
Frock is put, including fixed seat, fixture and pressing device, and the fixture is detachably connected by pressing device and the fixed seat,
The fixed seat is equipped with location hole and the first mounting hole, by fixed between the low-pressure turbine director assembly and the fixture
Position pin and the cooperation of location hole are positioned, are attached fixation by the cooperation of bolt and the first mounting hole.
The beneficial effects of the utility model：Aero-engine low-pressure turbine director assembly processing provided by the utility model
Device, including fixed seat, fixture and pressing device, the fixture are detachably connected by pressing device and the fixed seat, this
When two machined surfaces of the sample on the upside of to low-pressure turbine director assembly are processed, fixture is pulled down from fixed seat, with folder
Tool is used as supporting surface, is then positioned by location hole and positioning pin, by the cooperation of bolt and the first mounting hole by described in
The installation side of low-pressure turbine director assembly is fixed on the fixture and is clamped, at this time can be by lathe tool on part
Two machined surfaces of side carry out turnery processing；It is remote with the fixed seat when two machined surfaces are processed on the downside of to part
Then the low-pressure turbine director assembly is installed on institute by one end of the fixture as supporting surface by positioning pin and bolt
State on fixture, and by pressing device by the clamp pressing in the fixed seat, then by lathe tool to part on the downside of
Machined surface is processed, since fixture and the fixed seat are to cooperate fixed therefore have a unified positioning therebetween
Benchmark, therefore can realize that centering benchmark is unified in the processing to aero-engine low-pressure turbine director assembly both direction, because
The precision and accuracy higher of this processing.
Further, for the fixture in annular shape, the location hole and first mounting hole are equipped with multiple, Duo Gesuo
State location hole and multiple first mounting holes are arranged alternately and are in that annular shape is distributed on the fixture.
Further, the fixed seat includes the connecting portion in first annular portion, the second ring part and cylindrical shape, the connection
The upper end in portion is connected with the first annular portion, and lower end is connected with second ring part, the fixture by pressing device with
Second ring part is detachably connected.
Further, the axis of the first annular portion, the second ring part and the connecting portion is located on the same line
And internal diameter is identical, first annular portion's outside diameter is less than the outside diameter of second ring part, more than the outside diameter of the connecting portion.
Further, the first annular portion, the second ring part and the connecting portion are an integral structure.
Further, the circumferential direction of the connecting portion is equipped with multiple first through hole.
Further, the pressing device includes pressing plate, fixing bolt, sleeve and spring, and second ring part is outside
The part that side is protruding on the outside of connecting portion is equipped with the second mounting hole, and the sleeve is inserted into second mounting hole, and described second
The upper end of mounting hole is equipped with ream flat hole, and the sleeve is internally formed cavity, and the upside of the sleeve is equipped with fixed part, described solid
Determine portion and be equipped with the threaded hole connected with the cavity, and the upside of the fixed part is equipped with flange, the flange is overlapped on institute
State in ream flat hole；
The pressing plate includes mounting portion and nip portion, and the mounting portion is cylindrical, and the nip portion is vertically connected on institute
On the side wall for stating mounting portion lower end, limiting plate is equipped with the mounting portion, the limiting plate is equipped with the second through hole, the installation
The upper end in portion is inserted into the cavity on the downside of the sleeve, and the screw rod of the fixing bolt passes through second through hole and the screw thread
Hole is threadedly coupled, and the spring pocket is located at the upside of the limiting plate, the fixed spiral shell on the screw rod of the fixing bolt
The nut of bolt is located at the downside of the limiting plate.
Further, the pressing device is equipped with multigroup, circumferential direction of multigroup pressing device in second ring part
On be uniformly distributed.
Further, the backing plate of annular is further included, the inner side of second ring part is equipped with a ring annular groove, the backing plate
It is detachably arranged in the annular groove, the nip portion is by the clamp pressing on the lower face of the backing plate.
Brief description of the drawings
The utility model is above-mentioned and/or the advantages of additional aspect from combining in description of the accompanying drawings below to embodiment and will become
Substantially and it is readily appreciated that, wherein：
Fig. 1 is the sectional view of aero-engine low-pressure turbine director assembly processing unit (plant)；
Fig. 2 is the A portions enlarged drawing of Fig. 1；
Fig. 3 is sleeve sectional view；
Fig. 4 is the broken section structure diagram of the fixture；
Fig. 5 is the sectional view of the backing plate；
Fig. 6 is the structure diagram of the fixing bolt；
Fig. 7 is the sectional view of the pressing plate.
Correspondences of the wherein Fig. 1 into Fig. 7 between reference numeral and component names be：
1st, fixed seat, 11, first annular portion, the 12, second ring part, 13, connecting portion, 14, first through hole, the 15, second peace
Fill hole, 16, ream flat hole, 17, annular groove, 2, fixture, 21, location hole, the 22, first mounting hole, 3, pressing device, 31, pressing plate,
311st, mounting portion, 312, nip portion, 313, limiting plate, the 314, second through hole, 32, fixing bolt, 33, sleeve, 331, fixed part,
332nd, threaded hole, 333, flange, 34, spring, 4, backing plate, 5, low-pressure turbine director assembly.
Embodiment
In order to be more clearly understood that the above-mentioned purpose of the utility model, feature and advantage, below in conjunction with the accompanying drawings and have
The utility model is further described in detail in body embodiment.It should be noted that in the case where there is no conflict, this Shen
The feature in embodiment and embodiment please can be mutually combined.
As shown in Figures 1 to 7, the utility model provides a kind of aero-engine low-pressure turbine director assembly processing dress
Put, including fixed seat 1, fixture 2 and pressing device 3, the fixture 2 are detachably connected by pressing device 3 and the fixed seat 1
Connect, the fixed seat 1 is equipped with 21 and first mounting hole 22 of location hole, the low-pressure turbine director assembly and the fixture 2
Between positioned by the cooperation of positioning pin and location hole 21, be attached by the cooperation of bolt and the first mounting hole 22
It is fixed.
Aero-engine low-pressure turbine director assembly processing unit (plant) provided by the utility model, including fixed seat 1, fixture
2 and pressing device 3, the fixture 2 be detachably connected by pressing device 3 and the fixed seat 1, so led to low-pressure turbine
When two machined surfaces to the upside of device assembly 5 are processed, fixture 2 is pulled down from fixed seat 1, using fixture 2 as supporting surface,
Then positioned by location hole 21 and positioning pin, led the low-pressure turbine by the cooperation of bolt and the first mounting hole 22
Installation side to device assembly 5 is fixed on the fixture 2 and is clamped, at this time can be by lathe tool to two on the upside of part
Machined surface carries out turnery processing；When two machined surfaces are processed on the downside of to part, with the fixed seat 1 away from the fixture
Then the low-pressure turbine director assembly 5 is installed on the fixture by 2 one end as supporting surface by positioning pin and bolt
On 2, and the fixture 2 is pressed in the fixed seat 1 by pressing device 3, then by lathe tool to adding on the downside of part
Work face is processed, since fixture 2 and the fixed seat 1 are to cooperate fixed therefore have a unified positioning therebetween
Benchmark, therefore can realize that centering benchmark is unified in the processing to 5 both direction of aero-engine low-pressure turbine director assembly, because
The precision and accuracy higher of this processing.
As shown in Figure 1 and Figure 4, in annular shape, the location hole 21 and first mounting hole 22 are equipped with the fixture 2
Multiple, multiple location holes 21 and multiple first mounting holes 22 are arranged alternately and are distributed in the fixture 2 in annular shape
On, the fixture 2 is equipped with location hole 21, and the low-pressure turbine director assembly 5 passes through between location hole 21 and the fixture 2
Positioned, first mounting hole 22 is through hole, and bolt is installed through the through hole and the low-pressure turbine director assembly 5
The low-pressure turbine director assembly 5 is fixed on the fixture 2 by the through hole on side, at this time can be by lathe tool to described
The machined surface of the upside of low-pressure turbine director assembly 5 carries out turnery processing, while is installed on by low-pressure turbine director assembly 5
When on the fixture 2, the benchmark center of circle of the fixture 2 is first found accurately, then by the work axle center of lathe tool with the benchmark center of circle of fixture
As benchmark.
As shown in Figure 1, the fixed seat 1 includes the connecting portion 13 in first annular portion 11, the second ring part 12 and cylindrical shape,
The upper end of the connecting portion 13 is connected with the first annular portion 11, and lower end is connected with second ring part 12, the fixture 2
It is detachably connected by pressing device 3 and second ring part 12, the first annular portion 11, the second ring part 12 and described
The axis of connecting portion 13 is located on the same line and internal diameter is identical, and first annular 11 outside diameter of portion is less than the described second annular
The outside diameter in portion 12, more than the outside diameter of the connecting portion 13, due to first annular portion 11, the second ring part 12 and the connecting portion
13 axis is located on the same line, and internal diameter is identical, and the central datum line of the so described whole fixed seat 1 is all phase
Together, it is more prone to be positioned；Preferably, the first annular portion 11, the second ring part 12 and the connecting portion 13 are integrated
Formula structure, the structural strength of the fixed seat 1 of integral structure is more preferable, manufacture is more convenient, while first annular portion 11 and second
The end plane of ring part 12 can ensure parallel and smooth, easily facilitate and find benchmark accurately.
As shown in Figure 1, the circumferential direction of the connecting portion 13 is equipped with multiple first through hole 14, the first through hole 14 can drop
The weight of the low connecting portion 13, and then the weight of whole fixed seat 1 is reduced, one reduces the manufacture cost of fixed seat 1, grasps at the same time
Author can also observe the situation inside the fixed part 331 by the first through hole 14, be conducive to lead low-pressure turbine
Processing and manufacturing to device assembly 5 provides facility.
As shown in Figure 3 and 7, the pressing device 3 includes pressing plate 31, fixing bolt 32, sleeve 33 and spring 34, described
The part that second ring part 12 is protruding to the outside of connecting portion 13 laterally is equipped with the second mounting hole 15, and the sleeve 33 is inserted into described
In second mounting hole 15, the upper end of second mounting hole 15 is equipped with ream flat hole 16, and the sleeve 33 is internally formed cavity, institute
The upside for stating sleeve 33 is equipped with fixed part 331, and the fixed part 331 is equipped with the threaded hole 332 connected with the cavity, and institute
The upside for stating fixed part 331 is equipped with flange 333, and the flange 333 is overlapped in the ream flat hole 16；The pressing plate 31 includes peace
Dress portion 311 and nip portion 312, the mounting portion 311 is cylindrical, and the nip portion 312 is vertically connected on the mounting portion 311
On the side wall of lower end, limiting plate 313 is equipped with the mounting portion 311, the limiting plate 313 is equipped with the second through hole 314, described
The upper end of mounting portion 311 is inserted into the cavity of the downside of sleeve 33, and the screw rod of the fixing bolt 32 is logical through described second
Hole 314 is threadedly coupled with the threaded hole 332, and the spring 34 is sleeved on the screw rod of the fixing bolt 32, and positioned at described
The upside of limiting plate 313, the nut of the fixing bolt 32 are located at the downside of the limiting plate 313.
The fixture 2 can be pressed together on when in use in the fixed seat 1 by nip portion 312, while for described
Spring 34 is equipped with second mounting hole 15, spring 34 can realize that the nip portion 312 is more uniform to the pressure of fixture 2, institute
Stating the mounting portion 311 of pressing plate 31 can rotate in the sleeve 33, therefore in the fixation fixture 2, can be by stirring
The nip portion 312 of pressing plate 31 is stated to compress or unclamp the fixture 2, in addition the restoring force of spring 34 is able to ensure that the pressing plate 31
At will rotate, performance is more preferable.The pressing device 3 be equipped with it is multigroup, multigroup pressing device 3 is in second ring part
It is uniformly distributed in 12 circumferential direction, can so makes pressing plate 31 more uniform to the force of the fixture 2, fixture 2 is fixed on described
More smooth in fixed seat 1, benchmark is more unified, it is possible to increase the accuracy of manufacture of the low-pressure turbine director assembly 5, fixture 2
On have a multiple bolts 22 and 7 positioning pins 22, position and other engine components of 5 matching part of low-pressure turbine director assembly
Unanimously, multiple bolts 22 processing when by nut compress 5,7 positioning pins 22 of low-pressure turbine director assembly processing when pair
Low-pressure turbine director assembly 5 positions and the low-pressure turbine director assembly that will be deformed in high temperature environments is supportted Hui Yuan
Shape, positioning bolt when low-pressure turbine director assembly 5 assembles is simulated in assembling, improves the processing of low-pressure turbine director assembly
When center location precision and deflection when reducing the assembling of low-pressure turbine director assembly, if low-pressure turbine director assembly
Become ovalisation or center location and the deviation of blade center of rotation is too big, then easily knocked when the direction blade of minor axis radius rotates
Encounter the inner wall of low-pressure turbine director assembly, larger gap is left on the direction of major axis radius, engine can be reduced
Work efficiency, and by setting seven groups of positioning pins and pressing device to prevent the change of low-pressure turbine director assembly in the application
Shape, therefore the safety in utilization of equipment can be improved, and improve the work efficiency of engine, the certainly compression in this application
The quantity of device, which may also be, sets other quantity, such as four groups, five groups, six groups, eight groups.
As shown in Figure 1 and Figure 5, the aero-engine low-pressure turbine director assembly processing unit (plant) further includes the pad of annular
Plate 4, the inner side of second ring part 12 are equipped with a ring annular groove 17, and the backing plate 4 is detachably arranged in the annular groove
In 17, the fixture 2 is pressed on the lower face of the backing plate 4 by the nip portion 312, so whole fixture 2 be all the time with
The backing plate 4 contacts fixation, therefore the opposite abrasion produced during the work time is also backing plate 4 and fixture 2, so whole
Device can be worked on by replacing backing plate 4 to realize, it is possible to increase the service life of whole processing unit (plant), is used at the same time
The larger cost of volume of whole fixed seat 1 is higher, and would not produce abrasion to fixed seat 1 by setting backing plate 4, can reduce
Maintenance cost.
Filled below in conjunction with the accompanying drawings to illustrate that aero-engine low-pressure turbine director assembly provided by the utility model is processed
The use principle put.
The aero-engine low-pressure turbine director assembly 5 has three faces to be processed, due to positioned at the to be added of centre
The internal diameter in work face is less than the internal diameter in upper and lower two faces to be processed, therefore these three faces to be processed can not be once complete from a direction
Into processing, it is therefore desirable to processed from two modes；And the processing unit (plant) that the application provides is when in use, led to low-pressure turbine
When two machined surfaces to the upside of device assembly 5 are processed, fixture 2 is pulled down from fixed seat 1, using fixture 2 as supporting surface,
Then the center of circle of fixture 2 described in centering, is positioned by location hole 21 and positioning pin, passes through bolt and the first mounting hole 22
Cooperation the installation side of the low-pressure turbine director assembly 5 be fixed on the fixture 2 be clamped, can lead at this time
Cross lathe tool and turnery processing is carried out to two machined surfaces on the upside of part；
When two machined surfaces are processed on the downside of to part, made with the one end of the fixed seat 1 away from the fixture 2
For supporting surface, then the low-pressure turbine director assembly 5 is installed on the fixture 2 by positioning pin and bolt, then
The fixture 2 is pressed in the fixed seat 1 by and by pressing device 3, at this time that is, low-pressure turbine guider
Component 5 turns around, and the machined surface of downside has been transferred to upside, the machined surface on the downside of part can just be carried out by lathe tool at this time
Processing, since fixture 2 and the fixed seat 1 are to cooperate fixed therefore have a unified positioning datum therebetween, because
It can realize that centering benchmark is unified in the processing to 5 both direction of aero-engine low-pressure turbine director assembly, therefore process
Precision and accuracy higher.
In conclusion aero-engine low-pressure turbine director assembly processing unit (plant) provided by the utility model, including it is solid
Reservation, fixture and pressing device, the fixture are detachably connected by pressing device and the fixed seat, so to low pressure whirlpool
When two machined surfaces on the upside of wheel director assembly are processed, fixture is pulled down from fixed seat, using fixture as supporting surface,
Then positioned by location hole and positioning pin, by the cooperation of bolt and the first mounting hole by the low-pressure turbine guider
The installation side of component is fixed on the fixture and is clamped, at this time can be by lathe tool to two machined surfaces on the upside of part
Carry out turnery processing；When two machined surfaces are processed on the downside of to part, with the one end of the fixed seat away from the fixture
As supporting surface, then the low-pressure turbine director assembly is installed on the fixture by positioning pin and bolt, and leads to
Pressing device is crossed by the clamp pressing in the fixed seat, then the machined surface on the downside of part is added by lathe tool
Work, since fixture and the fixed seat are to cooperate fixed therefore have a unified positioning datum, energy therebetween
Enough realize that centering benchmark, therefore the precision processed are unified in the processing to aero-engine low-pressure turbine director assembly both direction
With accuracy higher.
, it is necessary to explanation in the description of the utility model, term " on ", " under ", "front", "rear", "left", "right",
The orientation or position relationship of the instructions such as " interior ", " outer " are based on orientation shown in the drawings or position relationship, are for only for ease of and retouch
State the utility model and simplify and describe, rather than instruction or imply signified device or element must have specific orientation, with
Specific azimuth configuration and operation, therefore it is not intended that limitation to the utility model.In addition, term " first ", " second "
Description purpose is only used for, and it is not intended that instruction or hint relative importance.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in the description of the utility model
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can mechanically connect or be electrically connected；It can be directly connected, can also be indirectly connected by intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
Concrete meaning of the language in the utility model.In addition, in the description of the utility model, unless otherwise indicated, " multiples' " contains
Justice is two or more.
It is new below in conjunction with this practicality to make the purpose, technical scheme and advantage of the utility model embodiment clearer
Attached drawing in type embodiment, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that is retouched
The embodiment stated is the part of the embodiment of the utility model, instead of all the embodiments.Based on the reality in the utility model
Apply example, those of ordinary skill in the art's all other embodiments obtained on the premise of creative work is not made, all
Belong to the scope of the utility model protection.
The above is only the preferred embodiment of the present invention, is not intended to limit the utility model, all in this practicality
Within new spirit and principle, any modification, equivalent replacement, improvement and so on, should be included in the guarantor of the utility model
Within the scope of shield.
Claims (9)
- A kind of 1. aero-engine low-pressure turbine director assembly processing unit (plant), it is characterised in that：Including fixed seat, fixture and pressure Tight device, the fixture are detachably connected by pressing device and the fixed seat, and the fixed seat is equipped with location hole and the One mounting hole, is determined between the low-pressure turbine director assembly and the fixture by the cooperation of positioning pin and location hole Position, by the cooperation of bolt and the first mounting hole be attached fixation.
- 2. aero-engine low-pressure turbine director assembly processing unit (plant) according to claim 1, it is characterised in that：It is described For fixture in annular shape, the location hole and first mounting hole are equipped with multiple, multiple location holes and multiple described the One mounting hole is arranged alternately and is in that annular shape is distributed on the fixture.
- 3. aero-engine low-pressure turbine director assembly processing unit (plant) according to claim 1, it is characterised in that：It is described Fixed seat includes the connecting portion in first annular portion, the second ring part and cylindrical shape, the upper end of the connecting portion and first ring Shape portion is connected, and lower end is connected with second ring part, and the fixture is detachable by pressing device and second ring part Connection.
- 4. aero-engine low-pressure turbine director assembly processing unit (plant) according to claim 3, it is characterised in that：It is described The axis in first annular portion, the second ring part and the connecting portion is located on the same line and internal diameter is identical, first ring Shape portion outside diameter is less than the outside diameter of second ring part, more than the outside diameter of the connecting portion.
- 5. the aero-engine low-pressure turbine director assembly processing unit (plant) according to claim 3 or 4, it is characterised in that： The first annular portion, the second ring part and the connecting portion are an integral structure.
- 6. aero-engine low-pressure turbine director assembly processing unit (plant) according to claim 5, it is characterised in that：It is described The circumferential direction of connecting portion is equipped with multiple first through hole.
- 7. aero-engine low-pressure turbine director assembly processing unit (plant) according to claim 5, it is characterised in that：It is described Pressing device includes pressing plate, fixing bolt, sleeve and spring, and second ring part is protruding to the portion on the outside of connecting portion laterally The second mounting hole is arranged with, the sleeve is inserted into second mounting hole, and the upper end of second mounting hole is equipped with ream flat hole, The sleeve is internally formed cavity, and the upside of the sleeve is equipped with fixed part, and the fixed part is equipped with to be connected with the cavity Logical threaded hole, and the upside of the fixed part is equipped with flange, the flange is overlapped in the ream flat hole；The pressing plate includes mounting portion and nip portion, and the mounting portion is cylindrical, and the nip portion is vertically connected on the peace On the side wall for filling subordinate end, limiting plate is equipped with the mounting portion, the limiting plate is equipped with the second through hole, the mounting portion Upper end is inserted into the cavity on the downside of the sleeve, and the screw rod of the fixing bolt passes through second through hole and the threaded hole spiral shell Line connects, and the spring pocket is located at the upside of the limiting plate on the screw rod of the fixing bolt, the fixing bolt Nut is located at the downside of the limiting plate.
- 8. aero-engine low-pressure turbine director assembly processing unit (plant) according to claim 7, it is characterised in that：It is described Pressing device be equipped with it is multigroup, multigroup pressing device is uniformly distributed in the circumferential direction of second ring part.
- 9. aero-engine low-pressure turbine director assembly processing unit (plant) according to claim 7, it is characterised in that：Also wrap The backing plate of annular is included, the inner side of second ring part is equipped with a ring annular groove, and the backing plate is detachably arranged in the ring In shape groove, the nip portion is by the clamp pressing on the lower face of the backing plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721439308.1U CN207358601U (en) | 2017-11-01 | 2017-11-01 | A kind of aero-engine low-pressure turbine director assembly processing unit (plant) |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721439308.1U CN207358601U (en) | 2017-11-01 | 2017-11-01 | A kind of aero-engine low-pressure turbine director assembly processing unit (plant) |
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| Publication Number | Publication Date |
|---|---|
| CN207358601U true CN207358601U (en) | 2018-05-15 |
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ID=62344953
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721439308.1U Active CN207358601U (en) | 2017-11-01 | 2017-11-01 | A kind of aero-engine low-pressure turbine director assembly processing unit (plant) |
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| Country | Link |
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| CN (1) | CN207358601U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107825156A (en) * | 2017-11-01 | 2018-03-23 | 贵州凯阳航空发动机有限公司 | A kind of aero-engine low-pressure turbine director assembly processing unit (plant) |
| CN108818089A (en) * | 2018-07-20 | 2018-11-16 | 河南科技大学 | A kind of two sides hole workpiece positioning fixture |
-
2017
- 2017-11-01 CN CN201721439308.1U patent/CN207358601U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107825156A (en) * | 2017-11-01 | 2018-03-23 | 贵州凯阳航空发动机有限公司 | A kind of aero-engine low-pressure turbine director assembly processing unit (plant) |
| CN108818089A (en) * | 2018-07-20 | 2018-11-16 | 河南科技大学 | A kind of two sides hole workpiece positioning fixture |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191210 Address after: 550000 No. 1111 Liyang Road, Baiyun District, Guiyang City, Guizhou Province Co-patentee after: China Natioanl Aero-Technology Import & Export Corporation Patentee after: Chinese Hangfa Guizhou Liyang aero Power Co. Ltd. Address before: 550008 Guizhou Guiyang city Guiyang national high tech Industrial Development Zone Jinyang science and Technology Industrial Park Venture Building 133 room Patentee before: GUIZHOU KAIYANG AERO-ENGINE CO., LTD. |
|
| TR01 | Transfer of patent right |