CN205237481U - A device for turbine of engine assembly - Google Patents
A device for turbine of engine assembly Download PDFInfo
- Publication number
- CN205237481U CN205237481U CN201521012763.4U CN201521012763U CN205237481U CN 205237481 U CN205237481 U CN 205237481U CN 201521012763 U CN201521012763 U CN 201521012763U CN 205237481 U CN205237481 U CN 205237481U
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- cylindrical shell
- bearing
- supporting pin
- supporting
- turbine
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- 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.)
- Withdrawn - After Issue
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Abstract
The utility model provides a device for turbine of engine assembly, include and install at the epaxial barrel of rotor shaft pivoted relatively of turbine rotor through two vice bearing device, the perpendicular to barrel put admittedly tray deck on being close to turbine rotor one end barrel, with the coaxial internal diameter of putting admittedly on the tray deck of barrel as the holding ring of director installation radical location benchmark with lie in the holding ring outer end and install the basic crown plate of axial positioning with director machine casket butt joint terminal surface as the director, installing the barrel at two epaxial vice bearing device of rotor, wherein being close to the bearing device of bearing device radial fine setting structure for the design has of turbine rotor one end, another bearing device has a bearing device of axial fine setting structure for the design, the tray deck design has the measuring aperture that is used for measuring the blade leading edge distance. Utilize the device can realize the axial of turbine rotor and director, radial position relation's precise adjustment to reach turbine rotor area director assembly and dynamic balance step by step, thereby improve the assembly precision and the reliability of turbine area director.
Description
Technical field
The utility model belongs to aero-engine and manufactures mounting technology field, particularly a kind of fitting device for engine turbine assembling.
Background technology
In aero-engine, there is a kind of large-scale birotary engine, for the assembling of the high and low pressure turbine in such engine assembly cell cube, because guider and rotor are structurally without mutual incidence relation, in cell cube assembling and equilibrium process, cannot directly find assembling benchmark from cell cube itself, be difficult to accurately location, therefore quite difficulty of the engine assembly of the type, adjustment. Engine turbine parts belong to hot junction and stressed member, are the core components of engine, and condition of work is severe, and distortion is large, higher to assembly technical requirement, and its assembly quality and precision have a significant impact engine performance and safety. When prior art assembling, during due to assembling, dimension chain is more, needs controlling element more, and cumulative errors are larger, after having assembled, can not recheck assembling key element, and assembly reliability is lower, and assembly precision is not high.
Summary of the invention
The purpose of this utility model is to overcome the deficiencies in the prior art, provides a kind of device for engine turbine assembling, to improve engine turbine assembly precision and property easy to assembly.
Basic ideas of the present utility model are: a device for large-scale birotary engine turbine assembling peace weighing apparatus is provided, make nozzle ring and rotor produce incidence relation, determine a reference for assembling, then join at the enterprising luggage of this technological datum, adjustment and dynamic balancing. Utilize this device that the assembly parts such as engine zero, assembly, parts are accurately located, clamped, carry out the assembling of engine turbine cell cube and balance.
The device for engine turbine assembling that the utility model provides, comprise by two supplementary bearing devices and be arranged on the cylindrical shell that can rotate relative to armature spindle on turbine rotor shaft, perpendicular to cylindrical shell be installed with the tray deck near on the cylindrical shell of turbine rotor one end, with cylindrical shell be installed with coaxially on tray deck internal diameter as guider install radial location benchmark locating ring, be arranged on the end face that docks with the guider casing locating ring outer end ring flat-plate as guider installation axial location base; Cylindrical shell is arranged on to two supplementary bearing devices on armature spindle, is to be wherein designed with the radially bearing arrangement of fine tuning structure near the bearing arrangement of turbine rotor one end, and another bearing arrangement is the bearing arrangement that is designed with axial fine tuning structure; Described tray deck is designed with the measured hole for measuring blade inlet edge distance.
In technique scheme of the present utility model, the formation of described radially fine tuning structure bearing arrangement comprises: 3 supporting seats that point to cylindrical shell central axis installing hole that are processed with that are circumferentially uniformly distributed setting along cylindrical shell, be arranged in supporting seat installing hole for the supporting pin of support rotor axle with for finely tuning the pad of supporting pin axial location, described supporting pin be designed with supporting seat on the shaft shoulder ring that matches of installing hole end face, described pad is placed between supporting pin shaft shoulder ring and supporting seat installing hole end face, supporting pin, pad and supporting seat are by the installing hole on supporting pin shaft shoulder ring, installing hole on pad, screw hole and set bolt on supporting seat are installed together, the thickness that whole bearing arrangement is adjusted 3 place's pads by replacing makes the axis of locating ring consistent with rotor axis.
In technique scheme of the present utility model, supporting pin preferentially adopts by being arranged on the supports support that can rotate relative to armature spindle cylinder its end in armature spindle; Described support member can be ball, roller, bearing; Preferentially select bearing, be arranged on supporting pin top by mandrel; Further preferred needle bearing, is arranged on supporting pin top by mandrel, makes the external supporting pin end face that exposes of needle bearing split bearing be supported in armature spindle.
In technique scheme of the present utility model, radially fine adjustment shaft bearing apparatus is designed with and keeps the axis location structure parallel with rotor axis of mandrel, described location structure by the locating slot on supporting pin, be arranged on supporting seat upper end and form with the lock-screw that described locating slot matches.
In technique scheme of the present utility model, the formation of described axial fine tuning structure bearing arrangement comprises: be arranged on the bearing between cylindrical shell and armature spindle, be arranged on the threaded adjusting cover in cylindrical shell by screw thread pair, by locking nut and screw thread pair, the adjustment screw on barrel wall be set; Described bearing shaft is to being positioningly arranged on armature spindle, can be arranged on axially slidably in cylindrical shell, make its front end act on bearing outer end by precession threaded adjusting cover cylindrical shell is carried out to axial adjustment, described adjustment screw is the screw that front end rigion is designed with taper seat structure, makes adjustment screw leading portion taper seat act on bearing the inner cylindrical shell is carried out to axial adjustment by precession screw.
In technique scheme of the present utility model, described tray deck decision design is to be designed with and to be strengthened the fan-shaped plate of gusset and form by 3～6 back sides, is generally to be designed with by 4 back sides the fan-shaped plate of strengthening gusset and to form.
In technique scheme of the present utility model, decision design is that tray deck is evenly distributed with 2～8 for measuring the measured hole of blade inlet edge distance on same diameter circumference; Be generally 4 for measuring the measured hole of blade inlet edge distance.
The device that adopts the utility model to provide assembles engine turbine, can realize to turbine rotor and guider axially, the accurate adjustment of radial position relationship, and to the assembling of turbine rotor tape guide device and dynamic balancing step by step, thereby assembly precision and the reliability of raising turbine tape guide device.
The use method of operating that device described in the utility model assembles for engine turbine:
1, the grade of 4 grades of impeller 20 of turbine are packed into after armature spindle 19, then before armature spindle, end-journal is loaded onto bearing, will pack with the turbine rotor of 3rd level impeller the device for engine turbine assembling into;
2, insert in supporting seat forming the radially supporting pin of fine tuning structure bearing arrangement, but unfixing;
3, end face M is installed as benchmark taking locating ring 1, adjusts the axial location of turbine rotor and device, adjust qualified after, threaded adjusting is overlapped to 14 and screws up with a wrench, fix turbine and guider axial location;
4, taking locating ring 1 internal diameter L as benchmark, use dial gauge and magnetic force dial framework, adjust by the pad 8 of selecting different groups, centering turbine rotor axis, after centering inserts supporting pin in supporting seat fixing;
5, the axial benchmark of end face M as guider location and installation is installed, assembling nozzle ring, the concentricity of guarantee guider and turbine rotor to install locating ring 1;
6, after guider rear end face is loaded onto after type frame on balancing machine 3 grades of impellers of dynamic balancing tape guide device;
7, pull down IV guider 27, V stage diverter 26, utilize the pad at front fixed 3 the supporting pin places of balance, the pad of matching by step 4 resets turbine wheel shaft radial position, then loads onto the 4th grade of impeller, is loaded on 3,4 grades of impellers of IV, V stage diverter dynamic balancing tape guide device;
8, complete assembling and the balance of 4,5,6 grades of impellers by above-mentioned 4,5,6,7 method.
Note: when assembling, this device is to be arranged on bracing frame by support plate 10 is installed, and must load onto rear type frame and carry out on balancing machine when balance, and bracing frame, rear type frame and balancing machine do not belong to device category described in the utility model.
9, measure tray deck 2 end faces to turbo blade leading-edge panel apart from S, then the actual value R being marked with according to device, by formula K=R-S, calculates K value and whether meets setting, can overlap 14 by threaded adjusting and adjust to reach requirement while not meeting.
Consider design feature and the general assembly assembly technique of the cell cube of difference, the type turbine tape guide device of the state of the art of each turbine rotor, described device spy is provided with threaded adjusting cover 14 and adjustment screw 17. by swivel nut being screwed into and back-outing and just can carry out the adjustment of the axial location of turbine rotor. the mounting edge of nozzle ring when the effect of described device locating ring installation end face M is equivalent to engine general assembly, for the axial benchmark of guider location and installation, on this mounting edge, can assemble guider, adopt this structure, just by structurally turbine rotor and the guider of onrelevant relation produce incidence relation, can realize location and the adjustment of the axial location of turbine rotor and guider, after axial location adjustment is qualified, again adjustment screw is screwed in ectosome, and adjustment screw is pinned with locking nut 16, by the ball bearing outer steel sleeve locking on turbine rotor, complete axial location.
To install the radial location benchmark that locating ring internal diameter L is turbine rotor shaft to radially adjusting of turbine rotor, adjust by supporting pin 7 and pad 8, when adjustment, by the pad of matching the different groups of 3 place's supporting pin, rotor and guider radial position relationship are adjusted to optimum state, then tighten the set bolt 9 on supporting seat, just completed the adjustment of the radial position of turbine rotor and guider.
Compared with prior art, the utlity model has following very outstanding useful technique effect:
1, utilize device assembling engine turbine described in the utility model, the turbine rotor of onrelevant relation structurally and guider can be connected assemble, adjustment and dynamic balancing, operating process is settled at one go, and there is reset function and recheck function, avoided repeating, make assembling and equilibrium process becomes simply, efficiently.
2, because turbine belongs to hot-end component in airborne vehicle, the assembly precision of turbine rotor and guider, particularly the axial and radial position relationship of turbine rotor and guider is very large to the safety effects of airborne vehicle, utilize the measured hole on the utility model appliance stand dish, in assembling process He after having assembled, all can check the rigging position key element of turbine rotor and guider, as not qualified or do not reach perfect condition, can directly confined state be finely tuned and be revised reach desirable requirement, improve the accuracy and reliability of engine assembly, guarantee assembly quality.
3, assembling process selects pad to be used as the adjustment part of centering turbine rotor, pad has 15 groups, before assembling, record the group of the adjusting pad using respectively in three latches, therefore, utilize the group of the front adjusting pad used of this device test run, after completing, every grade of turbine balance the radial position of destroyed can be quickly recovered to eligible state, after engine test, the confined state of turbine tape guide device can be reverted to the confined state before test run, not only can facilitate measurement and inspection to turbine spare part after test run, the fault simultaneously turbine part in commissioning process being occurred can arrive failure cause by fast finding.
Brief description of the drawings
Fig. 1 is the apparatus structure schematic diagram for engine turbine assembling described in the utility model;
Fig. 2 is the left TV structure schematic diagram of Fig. 1;
Fig. 3 be in Fig. 1 A-A to sectional structure schematic diagram;
Fig. 4 be in Fig. 3 B-B to sectional structure schematic diagram;
Fig. 5 is local I structure for amplifying schematic diagram in Fig. 1;
Fig. 6 is apparatus main body modular construction schematic diagram;
Fig. 7 is the structural representation of supporting pin member.
In above-mentioned figure, each shown by reference numeral mark object is respectively: 1-locating ring, 2-tray deck, 3-supporting seat, 4-cylindrical shell, 5-mandrel, 6-lock-screw, 7-supporting pin, 8-pad, 9-set bolt, 10-installation support plate, 11-needle bearing, 12-lining, 13-end cover, 14-threaded adjusting cover, 15-hold-down screw, 16-locking nut, 17-adjustment screw, 18-ball bearing, 19-turbine rotor shaft, 20-3 grades of impellers, 21-4 grades of impellers, 22-5 grades of impellers, 23-6 grades of impellers, 24-rear type frame, 25-VI stage diverter, 26-V stage diverter, 27-IV stage diverter.
I-axially fine adjustment bearing arrangement; II-radially fine adjustment bearing arrangement; M-locating ring is installed end face, is the axial benchmark of guider location and installation; L-locating ring internal diameter is the axial location benchmark of centering turbine rotor shaft; N-measured hole; R-tray deck end face is to the distance of locating ring end face; The tray deck end face of S-record from measured hole is to the distance of leading-edge panel turbo blade; After K-judgement assembling, the size of turbine rotor and guider axial location relation, can be obtained by formula K=R-S.
Detailed description of the invention
Device for engine turbine assembling described in the utility model is described further by embodiment below in conjunction with accompanying drawing.
Embodiment
In the present embodiment, the structure of the device assembling for engine turbine is as shown in Fig. 1～6, comprise by two supplementary bearing devices and be arranged on the cylindrical shell 4 that can rotate relative to armature spindle on turbine rotor shaft 19, be installed with at the tray deck 2 near on the cylindrical shell of turbine rotor one end, be installed with coaxially internal diameter on tray deck with cylindrical shell the locating ring 1 of radial location benchmark is installed as guider perpendicular to cylindrical shell, and be positioned at locating ring outer end and dock the ring flat-plate of end face as guider installation axial location base with guider casing; Cylindrical shell is arranged on to two supplementary bearing devices on armature spindle, is to be wherein designed with the radially bearing arrangement of fine tuning structure near the bearing arrangement of turbine rotor one end, and another bearing arrangement is the bearing arrangement that is designed with axial fine tuning structure. The fan-shaped plate that described tray deck 2 is designed with reinforcement gusset by 4 back sides forms. Tray deck 2 is evenly distributed with by 4 for measuring the measured hole of blade inlet edge distance on same diameter circumference.
The formation of described radially fine tuning structure bearing arrangement comprises: 3 supporting seats 3 that point to cylindrical shell central axis installing hole that are processed with that are circumferentially uniformly distributed setting along cylindrical shell, be arranged on supporting seat installing hole interior for the supporting pin 7 of support rotor axle with for finely tuning the pad 8 of supporting pin axial location, be also designed with the axis location structure parallel with rotor axis that keeps mandrel. Described supporting pin be designed with supporting seat on the shaft shoulder ring that matches of installing hole end face, top is provided with needle bearing 11 by mandrel 5, needle bearing split bearing body exposes supporting pin end face and is supported in armature spindle. Described pad is placed between supporting pin shaft shoulder ring and supporting seat installing hole end face, supporting pin, pad and supporting seat are installed together by screw hole and set bolt on the installing hole on supporting pin shaft shoulder ring, installing hole, supporting seat on pad, and the thickness that whole bearing arrangement is adjusted 3 place's pads by replacing makes the axis of locating ring 1 consistent with rotor axis. Described location structure by the locating slot on supporting pin, be arranged on the lock-screw 6 that supporting seat upper end matches with institute locating slot and form.
The formation of described axial fine tuning structure bearing arrangement comprises: be arranged on the bearing 18 between cylindrical shell and armature spindle, be arranged on the threaded adjusting cover 14 in cylindrical shell by screw thread pair, by locking nut 16 and screw thread pair, the adjustment screw 17 on barrel wall is set; Described bearing shaft is to being positioningly arranged on armature spindle, can be arranged on axially slidably in cylindrical shell, make its front end act on bearing outer end by precession threaded adjusting cover cylindrical shell is carried out to axial adjustment, described adjustment screw is that front end rigion is the screw of taper seat body, makes the adjustment screw leading portion conical surface act on bearing the inner cylindrical shell is carried out to axial adjustment by precession screw.
Claims (10)
1. for a device for engine turbine assembling, it is characterized in that, comprise by two supplementary bearing devices and installingThe cylindrical shell (4) that can rotate relative to armature spindle on turbine rotor shaft (19), is installed with and is turning near turbine perpendicular to cylindrical shellTray deck (2) on the cylindrical shell of sub-one end, with cylindrical shell be coaxially installed with on tray deck internal diameter install as guider radially fixedThe locating ring (1) of position benchmark and be arranged on locating ring outer end and dock end face as guider installation shaft with guider casingTo the ring flat-plate of location base; Cylindrical shell is arranged on to two supplementary bearing devices on armature spindle, wherein near turbine rotor one endBearing arrangement is to be designed with the radially bearing arrangement of fine tuning structure, and another bearing arrangement is to be designed with axial fine tuning structureBearing arrangement, described tray deck is designed with the measured hole for measuring blade inlet edge distance.
2. the device for engine turbine assembling according to claim 1, is characterized in that, radially describedThe formation of fine tuning structure bearing arrangement, comprises that being circumferentially uniformly distributed being processed with of setting along cylindrical shell points to cylindrical shell central axis3 supporting seats (3) of installing hole, be arranged in supporting seat installing hole for the supporting pin (7) of support rotor axle andFor finely tuning the pad (8) of supporting pin axial location, described supporting pin be designed with supporting seat on installing hole end face mutuallyThe shaft shoulder ring of joining, described pad is placed between supporting pin shaft shoulder ring and supporting seat installing hole end face, supporting pin, padPass through the screw hole on the installing hole on supporting pin shaft shoulder ring, installing hole, the supporting seat on pad and fix with supporting seatBolt is installed together, and the thickness that whole bearing arrangement is adjusted 3 place's pads by replacing makes the axis of locating ring (1)Consistent with rotor axis.
3. the device for engine turbine assembling according to claim 2, is characterized in that, supporting pin is logicalCross and be arranged on the supports support that can rotate relative to armature spindle cylinder its end in armature spindle.
4. the device for engine turbine assembling according to claim 3, is characterized in that described supportPart is bearing (11), is arranged on supporting pin top by mandrel (5).
5. the device for engine turbine assembling according to claim 4, is characterized in that described bearingFor needle bearing, be arranged on supporting pin top by mandrel, make needle bearing split bearing body expose supporting pin end face and prop upSupport in armature spindle.
6. the device for engine turbine assembling according to claim 5, is characterized in that, radially fine settingBearing arrangement is designed with the axis location structure parallel with rotor axis that keeps mandrel, and described location structure is by supporting pinOn locating slot, be arranged on the lock-screw (6) that supporting seat upper end matches with institute locating slot and form.
7. according to the device for engine turbine assembling one of claim 1 to 6 Suo Shu, it is characterized in that,The formation of described axial fine tuning structure bearing arrangement, comprises the bearing (18) being arranged between cylindrical shell and armature spindle, logicalCross screw thread pair and be arranged on the threaded adjusting cover (14) in cylindrical shell, by locking nut (16) and screw thread pair, cylindrical shell is setAdjustment screw (17) on wall; Described bearing shaft, to being positioningly arranged on armature spindle, can be arranged on axially slidablyIn cylindrical shell, make its front end act on bearing outer end by precession threaded adjusting cover and cylindrical shell is carried out to axial adjustment, described tuneJoint screw is the screw that front end rigion is designed with taper seat structure, makes the effect of the adjustment screw front end rigion conical surface by precession screwIn bearing the inner, cylindrical shell is carried out to axial adjustment.
8. according to the device for engine turbine assembling one of claim 1 to 6 Suo Shu, it is characterized in that,The fan-shaped plate that described tray deck (2) is designed with reinforcement gusset by 3～6 back sides forms.
9. the device for engine turbine assembling according to claim 7, is characterized in that described supportThe fan-shaped plate that dish (2) is designed with reinforcement gusset by 3～6 back sides forms.
10. according to the device for engine turbine assembling one of claim 1 to 6 Suo Shu, it is characterized in that,Described tray deck (2) is evenly distributed with by 2～8 for measuring the survey of blade inlet edge distance on same diameter circumferenceMetering-orifice.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521012763.4U CN205237481U (en) | 2015-12-08 | 2015-12-08 | A device for turbine of engine assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521012763.4U CN205237481U (en) | 2015-12-08 | 2015-12-08 | A device for turbine of engine assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205237481U true CN205237481U (en) | 2016-05-18 |
Family
ID=55936560
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521012763.4U Withdrawn - After Issue CN205237481U (en) | 2015-12-08 | 2015-12-08 | A device for turbine of engine assembly |
Country Status (1)
| Country | Link |
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| CN (1) | CN205237481U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105397465A (en) * | 2015-12-08 | 2016-03-16 | 四川成发航空科技股份有限公司 | Assembly device for engine turbine |
| CN108015521A (en) * | 2016-11-04 | 2018-05-11 | 科华控股股份有限公司 | A kind of supercharger volute bushing assembling pressing mechanism that packing ring is replaced using swing gasket |
| CN111761556A (en) * | 2020-07-06 | 2020-10-13 | 中国航发沈阳发动机研究所 | Air inlet casing disassembling tool |
| CN111975337A (en) * | 2020-06-30 | 2020-11-24 | 中国航发南方工业有限公司 | Assembly vehicle for high-speed dynamic balance assembly of power turbine |
| CN112556575A (en) * | 2020-12-04 | 2021-03-26 | 西北工业大学 | Small-size aviation piston engine bent axle butt joint measuring device |
| CN112935788A (en) * | 2019-12-10 | 2021-06-11 | 中国航发商用航空发动机有限责任公司 | Butt joint guiding device of unit body with long shaft and technological method |
| CN114952256A (en) * | 2022-06-07 | 2022-08-30 | 中国航发成都发动机有限公司 | Aero-engine turbine shaft sleeve assembling, positioning and mounting device and positioning and mounting method |
-
2015
- 2015-12-08 CN CN201521012763.4U patent/CN205237481U/en not_active Withdrawn - After Issue
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105397465A (en) * | 2015-12-08 | 2016-03-16 | 四川成发航空科技股份有限公司 | Assembly device for engine turbine |
| CN105397465B (en) * | 2015-12-08 | 2017-05-31 | 四川成发航空科技股份有限公司 | For the device of engine turbine assembling |
| CN108015521A (en) * | 2016-11-04 | 2018-05-11 | 科华控股股份有限公司 | A kind of supercharger volute bushing assembling pressing mechanism that packing ring is replaced using swing gasket |
| CN112935788A (en) * | 2019-12-10 | 2021-06-11 | 中国航发商用航空发动机有限责任公司 | Butt joint guiding device of unit body with long shaft and technological method |
| CN112935788B (en) * | 2019-12-10 | 2022-08-19 | 中国航发商用航空发动机有限责任公司 | Butt joint guiding device of unit body with long shaft and technological method |
| CN111975337A (en) * | 2020-06-30 | 2020-11-24 | 中国航发南方工业有限公司 | Assembly vehicle for high-speed dynamic balance assembly of power turbine |
| CN111761556A (en) * | 2020-07-06 | 2020-10-13 | 中国航发沈阳发动机研究所 | Air inlet casing disassembling tool |
| CN111761556B (en) * | 2020-07-06 | 2022-12-16 | 中国航发沈阳发动机研究所 | Air inlet casing disassembling tool |
| CN112556575A (en) * | 2020-12-04 | 2021-03-26 | 西北工业大学 | Small-size aviation piston engine bent axle butt joint measuring device |
| CN112556575B (en) * | 2020-12-04 | 2022-07-29 | 西北工业大学 | Small-size aviation piston engine bent axle butt joint measuring device |
| CN114952256A (en) * | 2022-06-07 | 2022-08-30 | 中国航发成都发动机有限公司 | Aero-engine turbine shaft sleeve assembling, positioning and mounting device and positioning and mounting method |
| CN114952256B (en) * | 2022-06-07 | 2023-09-15 | 中国航发成都发动机有限公司 | Positioning and mounting device and positioning and mounting method for turbine shaft sleeve of aero-engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160518 Effective date of abandoning: 20170531 |
|
| AV01 | Patent right actively abandoned |