CN104385182A - Aero-engine multistage rotor and stator unit body positioning and hoisting device - Google Patents
Aero-engine multistage rotor and stator unit body positioning and hoisting device Download PDFInfo
- Publication number
- CN104385182A CN104385182A CN201410623939.3A CN201410623939A CN104385182A CN 104385182 A CN104385182 A CN 104385182A CN 201410623939 A CN201410623939 A CN 201410623939A CN 104385182 A CN104385182 A CN 104385182A
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- CN
- China
- Prior art keywords
- bolt
- stator
- fixed head
- aero
- cell cube
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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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C1/00—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles
- B66C1/10—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means
- B66C1/42—Gripping members engaging only the external or internal surfaces of the articles
- B66C1/44—Gripping members engaging only the external or internal surfaces of the articles and applying frictional forces
- B66C1/54—Internally-expanding grippers for handling hollow articles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to an aero-engine multistage rotor and stator unit body positioning and hoisting device, which comprises a process cartridge receiver, a lug shaft, a first screw bolt, a transfer disc, a second screw bolt, a fixing plate, a core expansion ring and a third screw bolt, wherein the process cartridge receiver is connected with the back installing edge of a stator cartridge receiver of a rotor and stator unit body through the first screw bolt, the transfer disc is connected with the process cartridge receiver through the second screw bolt, the fixing plate consists of a plurality of fan-shaped sections, the inner edge of each fan-shaped section is a slope surface, the outer edge of each fan-shaped is provided with a U-shaped groove, the U-shaped groove is matched with a radial plate of the last-stage disc of the rotor and stator unit body, the core expansion ring is provided with a convex edge, the outer part of the convex edge is a circular conical surface, the circular conical surface is matched with the slope surface of the inner edge of the fixing plate, and the transfer disc, the fixing plate and the core expansion ring are connected through the third screw bolt. The device provided by the invention has the advantages that the positioning and the hoisting of the multistage rotor and stator unit body are realized, and the axial and radial collision of a rotor and a stator is avoided.
Description
Technical field
The present invention relates to the device of a kind of spare part location and lifting, be specifically related to the multistage device turning stator cell cube location and lifting of a kind of aero-engine.
Background technology
For many years, it is all that first assembling guider casing refills and joins turbine rotor, not forming unit bodily form formula separately that the turbine of aero-engine turns stator assembling, for the lifting of nozzle box and turbine rotor and assembling all fairly simple.
Along with the thrust-weight ratio of aero-engine and reliability improve further, turbine turns this project organization of stator cell cube and is day by day widely used in modern aeroengine.Turbine turns the assembling Sum decomposition of this special structure form of stator cell cube to turbine and it is also proposed higher requirement, and this structural requirement turbine turns stator and assembles simultaneously, and must take into account the requirement turning relative position between stator and lifting.Turning the assembling Sum decomposition of stator cell cube for realizing turbine, must study and use novel location and hanging apparatus to locate and lifting requirements after the assembling meeting aero-engine.
The compressor of aero-engine is also rotor and each self-assembly of stator usually, and stator casing mostly is opening structure, turns convenient and swift when stator is assembled.But compressor, after rotor assembly balance meets the demands, turns after timing may cause rotor assembly to divide lower blade to load onto stator in transmission and ressembles, affect the counterbalance effect of rotor.And the cell cube of Split Casing structure, after assembling, because rotor-stator is not in the break-in of cell cube state, produce the probability touching mill larger; Also need to study and use novel location and hanging apparatus to locate and lifting requirements after the assembling meeting aero-engine.
Aero-engine is multistage to be turned stator cell cube collaborative assembly on assembling device and is formed and turn stator cell cube, by assembling device, rotor, stator are positioned during assembling, but hang out from assembling device after assembling, hanging apparatus will be leaned on to ensure axis and the radial location of rotor, stator, ensure that rotor, stator relative movement can not occur when slinging.Stator locating surface mounting edge before stator during assembling, locating surface mounting edge before one-level dish of rotor, need with the rear mounting edge of stator and the disc of rotor afterbody dish during lifting, the conversion and the tolerance that relate to size add up, turn stator axial-radial gap all little, require that dimension conversion precision accurately, otherwise must will exist the danger of touching mill.
Summary of the invention
The object of this invention is to provide the multistage device turning stator cell cube location and lifting of a kind of aero-engine, for to aero-engine is multistage turn the assembling of stator cell cube after carry out axis and radial location, and ensure sling turn stator cell cube time multi-stage rotor, can not occur between stator axially and diametrically move.
Technical scheme of the present invention is as follows:
The multistage device turning stator cell cube location and lifting of a kind of aero-engine, comprise technique casing, gudgeon, bolt one, transfer panel, bolt two, fixed head, rise core ring and bolt three, described technique casing is connected by bolt one with mounting edge after the stator casing turning stator cell cube; Described gudgeon is arranged on described technique casing; It is inner that described transfer panel is arranged on described technique casing, and described transfer panel is connected by bolt two with described technique casing; It is inner that described fixed head is arranged on described transfer panel, and described fixed head is made up of polylith fan-shaped section, and the inner edge of described fan-shaped section is domatic, and the outer rim of described fan-shaped section arranges U-type groove, and described U-type groove matches with the disc of the afterbody dish turning stator cell cube; It is inner that the described core ring that rises is arranged on described fixed head, described in the core that rises be equipped with convex edge, the outside of described convex edge is taper seat, and described taper seat matches with the inner edge of described fixed head is domatic; Described transfer panel, fixed head and the core ring that rises are linked together by bolt three.
The multistage device turning stator cell cube location and lifting of described aero-engine, its preferred version is, described fixed head is made up of three pieces of fan-shaped section.
The multistage device turning stator cell cube location and lifting of described aero-engine, its preferred version is, described bolt one quantity is 32 ~ 40, and described bolt two quantity is 8 ~ 12, and described bolt three quantity is 12 ~ 16.
The multistage device turning stator cell cube location and lifting of described aero-engine, its preferred version is, described gudgeon quantity is 2.
When the multistage device turning stator cell cube location and lifting of aero-engine of the present invention works, first technique casing is connected with mounting edge bolt one after stator casing, realizes the multistage stator location turning stator cell cube; Secondly on technique casing, transfer panel is connected with bolt two, then the position of adjusting process casing and transfer panel is come by bolt two, the U-type groove structure of fixed head is made to be installed on the disc of afterbody dish smoothly, fixed head is polylith fan-shaped section, can assemble with the disc of afterbody dish very easily, thus the radial position of fixed rotor; Thereafter with tensioner under the core hoop that rises of the convex edge that is taper seat with outside, the disc of fixed head and afterbody wheel disc radial direction fit tight, accurately locate; Thereafter with bolt three by transfer panel, fixed head and the core ring axial restraint that rises, bolt two on adjustment transfer panel makes technique casing and transfer panel axial distance meet positioning states, guarantee to turn stator cell cube radial-axial firm position, realize rotor by gudgeon, stator lifts simultaneously.
Beneficial effect of the present invention: the arrangement achieves the multistage location and the lifting that turn stator cell cube, avoids causing rotor, stator axial-radial touches mill.This device highly versatile, the scope of application is comparatively wide, is convenient to promote.
Accompanying drawing explanation
Fig. 1 is the multistage device top view turning stator cell cube location and lifting;
Fig. 2 be in Fig. 1 A-A to sectional view;
Fig. 3 is the multistage device working state schematic representation turning stator cell cube location and lifting.
Detailed description of the invention
As shown in Figure 1, 2, 3, the multistage device turning stator cell cube location and lifting of a kind of aero-engine, comprise technique casing 1, gudgeon 8, bolt 1, transfer panel 2, bolt 26, fixed head 3, rise core ring 4 and bolt 37, described technique casing 1 is connected by bolt 1 with mounting edge after the stator casing turning stator cell cube 9; 2 gudgeons 8 are arranged on described technique casing 1; It is inner that described transfer panel 2 is arranged on described technique casing 1, and described transfer panel 2 is connected by bolt 26 with described technique casing 1; It is inner that described fixed head 3 is arranged on described transfer panel, and described fixed head is made up of three pieces of fan-shaped section, and the inner edge of described fan-shaped section is domatic, and the outer rim of described fan-shaped section arranges U-type groove, and described U-type groove coordinates with the disc 10 of the six grades of turbine disks turning stator cell cube; It is inner that the described core ring 4 that rises is arranged on described fixed head, described in the core ring 4 that rises be provided with convex edge, the outside of described convex edge is taper seat, and described taper seat matches with the inner edge of described fixed head 3 is domatic; Described transfer panel 2, fixed head 3 and the core ring 4 that rises are linked together by bolt 37.
As shown in Figure 3, when the multistage device turning stator cell cube location and lifting of aero-engine of the present invention works, first technique casing 1 and mounting edge 9 after stator casing 32 bolts 1 are connected, and realize the multistage stator location turning stator cell cube; Secondly on technique casing 1, transfer panel 2 is connected with 8 bolts 26; Then utilize the U-type groove of fixed head 3 to coordinate with six grades of disc coiled 10, the radial position of fixed rotor, fixed head 3 is three pieces of fan-shaped section, can assemble with six grades of disc coiled 10 very easily; Thereafter with the downward tensioner of the core ring 4 that rises of the convex edge being taper seat with outside, the disc 10 of fixed head 3 and six grades of wheel discs radial direction is fitted closely, accurately locate; Thereafter with 12 bolts 37 by transfer panel 2, fixed head 3 and core ring 4 axial restraint that rises, bolt 26 on adjustment transfer panel 2 makes technique casing 1 and transfer panel 2 axial distance meet positioning states, guarantee to turn stator cell cube radial-axial firm position, realize rotor by gudgeon 8, stator lifts simultaneously.
Claims (4)
1. the multistage device turning stator cell cube location and lifting of aero-engine, it is characterized in that, described device comprises technique casing, gudgeon, bolt one, transfer panel, bolt two, fixed head, rise core ring and bolt three, and described technique casing is connected by bolt one with mounting edge after the stator casing turning stator cell cube; Described gudgeon is arranged on described technique casing; It is inner that described transfer panel is arranged on described technique casing, and described transfer panel is connected by bolt two with described technique casing; It is inner that described fixed head is arranged on described transfer panel, and described fixed head is made up of polylith fan-shaped section, and the inner edge of described fan-shaped section is domatic, and the outer rim of described fan-shaped section arranges U-type groove, and described U-type groove matches with the disc of the afterbody dish turning stator cell cube; It is inner that the described core ring that rises is arranged on described fixed head, described in the core that rises be equipped with convex edge, the outside of described convex edge is taper seat, and described taper seat matches with the inner edge of described fixed head is domatic; Described transfer panel, fixed head and the core ring that rises are linked together by bolt three.
2. the multistage device turning stator cell cube location and lifting of aero-engine according to claim 1, it is characterized in that, described fixed head is made up of three pieces of fan-shaped section.
3. the multistage device turning stator cell cube location and lifting of aero-engine according to claim 1, it is characterized in that, described bolt one quantity is 32 ~ 40, and described bolt two quantity is 8 ~ 12, and described bolt three quantity is 12 ~ 16.
4. the multistage device turning stator cell cube location and lifting of aero-engine according to claim 1, it is characterized in that, described gudgeon quantity is 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410623939.3A CN104385182B (en) | 2014-11-07 | 2014-11-07 | The multistage device turning stator cell cube location and lifting of a kind of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410623939.3A CN104385182B (en) | 2014-11-07 | 2014-11-07 | The multistage device turning stator cell cube location and lifting of a kind of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104385182A true CN104385182A (en) | 2015-03-04 |
| CN104385182B CN104385182B (en) | 2016-04-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410623939.3A Expired - Fee Related CN104385182B (en) | 2014-11-07 | 2014-11-07 | The multistage device turning stator cell cube location and lifting of a kind of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104385182B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106640770A (en) * | 2016-12-23 | 2017-05-10 | 贵州黎阳航空动力有限公司 | Assembly method of low-pressure supercharging device used for bi-rotor gas turbine |
| CN108792916A (en) * | 2018-05-30 | 2018-11-13 | 中国航发商用航空发动机有限责任公司 | Combination workpiece operates tooling |
| CN109514465A (en) * | 2018-11-29 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of long axis class spare part assembly guide clamp and application method |
| CN109516362A (en) * | 2018-11-30 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | The suspender and its application method of a kind of while hoisting rotor and stator component |
| CN110039472A (en) * | 2019-05-29 | 2019-07-23 | 北京深蓝航天科技有限公司 | Turn stator positioning device and its localization method |
| CN111994779A (en) * | 2020-09-14 | 2020-11-27 | 中国航发贵州黎阳航空动力有限公司 | Hoisting method of compressor disk and hoisting tool for machining |
| CN112113480A (en) * | 2020-09-18 | 2020-12-22 | 中国航发沈阳黎明航空发动机有限责任公司 | Auxiliary tool and method for measuring assembly clearance of fan unit body |
| CN113530676A (en) * | 2020-04-22 | 2021-10-22 | 中国航发商用航空发动机有限责任公司 | Rapid fault removing device and process for unit body of gas compressor |
| CN113800385A (en) * | 2020-06-12 | 2021-12-17 | 中国航发商用航空发动机有限责任公司 | Hoisting assembly and hanger switching section thereof |
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| CN203722426U (en) * | 2013-12-31 | 2014-07-16 | 宁波菲仕运动控制技术有限公司 | Assembling tooling for motor stator and rotor |
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2014
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| US6205644B1 (en) * | 1997-12-04 | 2001-03-27 | Emerson Electric Co. | Method of assembling an electric motor |
| KR20090054310A (en) * | 2007-11-26 | 2009-05-29 | 현대자동차주식회사 | Motor installatioin device of hybrid electric vehicle |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106640770A (en) * | 2016-12-23 | 2017-05-10 | 贵州黎阳航空动力有限公司 | Assembly method of low-pressure supercharging device used for bi-rotor gas turbine |
| CN106640770B (en) * | 2016-12-23 | 2019-05-14 | 贵州黎阳航空动力有限公司 | A kind of birotor combustion engine low-pressure supercharging device assembly method |
| CN108792916A (en) * | 2018-05-30 | 2018-11-13 | 中国航发商用航空发动机有限责任公司 | Combination workpiece operates tooling |
| CN108792916B (en) * | 2018-05-30 | 2019-12-27 | 中国航发商用航空发动机有限责任公司 | Combined workpiece operation tool |
| CN109514465A (en) * | 2018-11-29 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of long axis class spare part assembly guide clamp and application method |
| CN109514465B (en) * | 2018-11-29 | 2021-07-16 | 中国航发沈阳黎明航空发动机有限责任公司 | Long-shaft component assembly guiding clamp and using method |
| CN109516362A (en) * | 2018-11-30 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | The suspender and its application method of a kind of while hoisting rotor and stator component |
| CN109516362B (en) * | 2018-11-30 | 2019-10-22 | 中国航发沈阳黎明航空发动机有限责任公司 | The suspender and its application method of a kind of while hoisting rotor and stator component |
| CN110039472B (en) * | 2019-05-29 | 2020-11-20 | 江苏深蓝航天有限公司 | Rotor and stator positioning device and positioning method thereof |
| CN110039472A (en) * | 2019-05-29 | 2019-07-23 | 北京深蓝航天科技有限公司 | Turn stator positioning device and its localization method |
| CN113530676A (en) * | 2020-04-22 | 2021-10-22 | 中国航发商用航空发动机有限责任公司 | Rapid fault removing device and process for unit body of gas compressor |
| CN113530676B (en) * | 2020-04-22 | 2022-06-28 | 中国航发商用航空发动机有限责任公司 | Rapid fault removal device and process for compressor unit body |
| CN113800385A (en) * | 2020-06-12 | 2021-12-17 | 中国航发商用航空发动机有限责任公司 | Hoisting assembly and hanger switching section thereof |
| CN111994779A (en) * | 2020-09-14 | 2020-11-27 | 中国航发贵州黎阳航空动力有限公司 | Hoisting method of compressor disk and hoisting tool for machining |
| CN112113480A (en) * | 2020-09-18 | 2020-12-22 | 中国航发沈阳黎明航空发动机有限责任公司 | Auxiliary tool and method for measuring assembly clearance of fan unit body |
| CN112113480B (en) * | 2020-09-18 | 2021-12-14 | 中国航发沈阳黎明航空发动机有限责任公司 | Auxiliary tool and method for measuring assembly clearance of fan unit body |
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|---|---|
| CN104385182B (en) | 2016-04-13 |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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Granted publication date: 20160413 Termination date: 20201107 |
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