CN105458647A - Assembling method for power turbine without adjustment of axial gap between rotor and stator - Google Patents
Assembling method for power turbine without adjustment of axial gap between rotor and stator Download PDFInfo
- Publication number
- CN105458647A CN105458647A CN201510812741.4A CN201510812741A CN105458647A CN 105458647 A CN105458647 A CN 105458647A CN 201510812741 A CN201510812741 A CN 201510812741A CN 105458647 A CN105458647 A CN 105458647A
- Authority
- CN
- China
- Prior art keywords
- rotor
- stator
- assembly
- power turbine
- split casing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
Abstract
The invention relates to an assembling method for a power turbine, in particular to an assembling method for a power turbine without adjustment of an axial gap between a rotor and a stator. According to the technical scheme, the assembling method for the power turbine without adjustment of the axial gap between the rotor and the stator comprises the following steps that firstly, the axial distance between the rotor and the stator is calculated; secondly, tool installing is carried out; thirdly, a transition section assembly is installed; fourthly, the rotor is installed; fifthly, a split casing assembly is installed; sixthly, a rear bearing casing is installed; seventhly, a thrust bearing and other rear bearing related assemblies are installed; and eighthly, assembling is carried out. By means of the assembling method for the power turbine without adjustment of the axial gap between the rotor and the stator, assembling of the power turbine is achieved, and it is effectively guaranteed that the axial gap between the rotor and the stator meets the requirement.
Description
Technical field
The present invention relates to a kind of assembly method of power turbine, be specifically related to a kind of rotor and the stator axial gap assembly method without the power turbine adjusted.
Background technology
As shown in Figure 1, a kind of power turbine comprises rotor and stator, and stator comprises changeover portion assembly, Split Casing assembly and rear support case, and Split Casing assembly is to opening structure, and changeover portion assembly and rear support case are domain structure.Be provided with thrust bearing between its rotor and stator, the inner ring installed surface between rotor and thrust bearing inner ring and all non-design modifying pad of the outer shroud installed surface between stator and shaft washer, cause rotor and stator axial gap to adjust.During assembling, the inner ring installed surface of thrust bearing and outer shroud installed surface must be consistent, therefore cannot realize level assembling, and vertically assemble and be difficult to guarantee and turn the requirement of stator axial gap, need to be realized by frock.
Summary of the invention
The invention provides a kind of rotor and the stator axial gap assembly method without the power turbine adjusted, realize the assembling of power turbine and effectively ensure that rotor and stator axial gap meet the demands.
Technical scheme of the present invention is as follows:
Rotor and stator axial gap, without an assembly method for the power turbine adjusted, comprise the steps:
One, rotor and stator axial spacing is calculated: measure the length Y of rotor front end face to the inner ring installed surface between rotor and thrust bearing inner ring, measure the length X of changeover portion assembly front end face to the outer shroud installed surface between stator and shaft washer, calculated difference Z=X-Y, Z are rotor and stator axial spacing;
Two, the installation of frock: turning assembling base is placed on vertical state, is arranged on described base center by locating shaft and adjustment axle, and locating shaft is fixed together with adjustment axle, adjusts axle with described base to be threaded; Adjusting pad is fixedly mounted on locating shaft; Mounting platform is fixedly mounted on base upper surface, mounting platform is arranged seam and hole, described hole coordinates with locating shaft installs; By rotating the height of adjustment axial adjustment locating shaft, the upper surface of adjusting pad and the difference in height of mounting platform upper surface is made to be Z value;
Three, changeover portion assembly is installed: be arranged on mounting platform by changeover portion assembly, located by seam, utilize screw to be fixed on mounting platform;
Four, rotor is installed: be arranged on by suspender on rotor, under vertical state, rotor be installed, rotor front end face and adjusting pad are fitted, point lower suspender;
Five, Split Casing assembly is installed: by support installing on mounting platform, described support is divided into left and right two halves, backing plate being linked together by adjustment bolt and support, by rotating adjustment bolt, the rear end face height of backing plate upper surface and changeover portion assembly being consistent; Split Casing assembly is to opening structure, by Split Casing assembly, first winches on support, Split Casing assembly ecto-entad is pushed to installation site, Split Casing assembly first and changeover portion assembly are fixed together by connecting bolt one, same mode installs Split Casing assembly, and second is also fixing, installs Split Casing assembly and splits mounting edge connecting bolt two;
Six, support case after installing: rear support case is arranged on Split Casing assembly, and with connecting bolt three, rear support case and Split Casing assembly is fixed together; Under this state, the inner ring installed surface between rotor and thrust bearing inner ring and the outer shroud installed surface height between stator and shaft washer are consistent, and ensure that the installation site of thrust bearing;
Seven, thrust bearing and other rear bearing associated component are installed: install successively internal ring of thrust bearing leading portion, thrust bearing outer shroud, internal ring of thrust bearing back segment, distance collar, bearing inner ring, outer race, clamp nut, sealing teeth, clamp nut, after to obturage ring, speed measuring device;
Eight, assemble: the power turbine assembled divided to descend and turn to level, being arranged on power turbine base, protecgulum is installed.
Described rotor and stator axial gap are without the assembly method of the power turbine adjusted, and its preferred version is, roller installed by described backing plate.
Beneficial effect of the present invention is: the present invention can realize the assembling of power turbine, and effectively ensure that and turn the requirement of stator axial gap.
Accompanying drawing explanation
Fig. 1 is power turbine structural representation;
Fig. 2 is tool structure schematic diagram;
Fig. 3 is changeover portion assembly installation diagram;
Fig. 4 is rotor installation diagram;
Fig. 5 is support installing figure;
Fig. 6 is A direction view in Fig. 5;
Fig. 7 is B place partial enlarged drawing in Fig. 5;
Fig. 8 is Split Casing assembly installation diagram;
Fig. 9 is rear support case installation diagram;
Figure 10 is C place partial enlarged drawing in Fig. 9.
Detailed description of the invention
As shown in Fig. 1 ~ 10, a kind of rotor and stator axial gap, without the assembly method of the power turbine adjusted, comprise the steps:
One, rotor 1 and stator axial spacing is calculated: measure the length Y of rotor 1 front end face to the inner ring installed surface 7 between rotor 1 and thrust bearing 5 inner ring, measure the length X of changeover portion assembly 2 front end face to the outer shroud installed surface 8 between stator and thrust bearing 5 outer ring, calculated difference Z=X-Y, Z are rotor 1 and stator axial spacing;
Two, the installation of frock: turning assembling base 11 is placed on vertical state, is arranged on described base 11 center by locating shaft 13 and adjustment axle 12, and locating shaft 13 is fixed together with adjustment axle 12, adjusts axle 12 with described base 11 to be threaded; Adjusting pad 14 is fixedly mounted on locating shaft 13; Mounting platform 15 is fixedly mounted on base 11 upper surface, mounting platform 15 is arranged seam and hole, described hole coordinates with locating shaft 13 installs; Adjusting the height of locating shaft 13 by rotating adjustment axle 12, making the difference in height of the upper surface of adjusting pad 14 and mounting platform 15 upper surface be Z value;
Three, changeover portion assembly 2 is installed: be arranged on mounting platform 15 by changeover portion assembly 2, located by seam, utilize screw to be fixed on mounting platform 15;
Four, rotor 1 is installed: be arranged on by suspender 16 on rotor 1, rotor 1 is installed under vertical state, rotor 1 front end face and adjusting pad 14 are fitted, point lower suspender 16;
Five, Split Casing assembly 3 is installed: be arranged on by support 17 on mounting platform 15, described support 17 is divided into left and right two halves, backing plate 18 is linked together with support 17 by adjustment bolt 20, roller 19 installed by described backing plate 18; By rotating adjustment bolt 20, the rear end face height of backing plate 18 upper surface and changeover portion assembly 2 is consistent; Split Casing assembly 3 is to opening structure, by Split Casing assembly 3, first winches on support, Split Casing assembly 3 ecto-entad is pushed to installation site, Split Casing assembly 3 first and changeover portion assembly 2 are fixed together by connecting bolt one, same mode installs Split Casing assembly 3, and second is also fixing, installs Split Casing assembly 3 and splits mounting edge connecting bolt two;
Six, support case 4 after installing: rear support case 4 is arranged on Split Casing assembly 3, and with connecting bolt three, rear support case 4 is fixed together with Split Casing assembly 3; Under this state, the inner ring installed surface 7 between rotor 1 and thrust bearing 5 inner ring and the outer shroud installed surface 8 between stator and thrust bearing 5 outer ring are highly consistent, and ensure that the installation site of thrust bearing 5;
Seven, thrust bearing 5 and other rear bearing associated component are installed: install successively internal ring of thrust bearing leading portion, thrust bearing outer shroud, internal ring of thrust bearing back segment, distance collar, bearing inner ring, outer race, clamp nut, sealing teeth, clamp nut, after to obturage ring, speed measuring device;
Eight, assemble: the power turbine assembled divided to descend and turn to level, being arranged on power turbine base, protecgulum 6 is installed.
Claims (2)
1. rotor and stator axial gap are without the assembly method of the power turbine adjusted, and it is characterized in that, comprise the steps:
One, rotor and stator axial spacing is calculated: measure the length Y of rotor front end face to the inner ring installed surface between rotor and thrust bearing inner ring, measure the length X of changeover portion assembly front end face to the outer shroud installed surface between stator and shaft washer, calculated difference Z=X-Y, Z are rotor and stator axial spacing;
Two, the installation of frock: turning assembling base is placed on vertical state, is arranged on described base center by locating shaft and adjustment axle, and locating shaft is fixed together with adjustment axle, adjusts axle with described base to be threaded; Adjusting pad is fixedly mounted on locating shaft; Mounting platform is fixedly mounted on base upper surface, mounting platform is arranged seam and hole, described hole coordinates with locating shaft installs; By rotating the height of adjustment axial adjustment locating shaft, the upper surface of adjusting pad and the difference in height of mounting platform upper surface is made to be Z value;
Three, changeover portion assembly is installed: be arranged on mounting platform by changeover portion assembly, located by seam, utilize screw to be fixed on mounting platform;
Four, rotor is installed: be arranged on by suspender on rotor, under vertical state, rotor be installed, rotor front end face and adjusting pad are fitted, point lower suspender;
Five, Split Casing assembly is installed: by support installing on mounting platform, described support is divided into left and right two halves, backing plate being linked together by adjustment bolt and support, by rotating adjustment bolt, the rear end face height of backing plate upper surface and changeover portion assembly being consistent; Split Casing assembly is to opening structure, by Split Casing assembly, first winches on support, Split Casing assembly ecto-entad is pushed to installation site, Split Casing assembly first and changeover portion assembly are fixed together by connecting bolt one, same mode installs Split Casing assembly, and second is also fixing, installs Split Casing assembly and splits mounting edge connecting bolt two;
Six, support case after installing: rear support case is arranged on Split Casing assembly, and with connecting bolt three, rear support case and Split Casing assembly is fixed together; Under this state, the inner ring installed surface between rotor and thrust bearing inner ring and the outer shroud installed surface height between stator and shaft washer are consistent, and ensure that the installation site of thrust bearing;
Seven, thrust bearing and other rear bearing associated component are installed: install successively internal ring of thrust bearing leading portion, thrust bearing outer shroud, internal ring of thrust bearing back segment, distance collar, bearing inner ring, outer race, clamp nut, sealing teeth, clamp nut, after to obturage ring, speed measuring device;
Eight, assemble: the power turbine assembled divided to descend and turn to level, being arranged on power turbine base, protecgulum is installed.
2. rotor according to claim 1 and stator axial gap are without the assembly method of the power turbine adjusted, and it is characterized in that, roller installed by described backing plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510812741.4A CN105458647B (en) | 2015-11-20 | 2015-11-20 | Rotor and assembly method of the stator axial gap without the power turbine for adjusting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510812741.4A CN105458647B (en) | 2015-11-20 | 2015-11-20 | Rotor and assembly method of the stator axial gap without the power turbine for adjusting |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105458647A true CN105458647A (en) | 2016-04-06 |
| CN105458647B CN105458647B (en) | 2017-06-30 |
Family
ID=55597038
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510812741.4A Active CN105458647B (en) | 2015-11-20 | 2015-11-20 | Rotor and assembly method of the stator axial gap without the power turbine for adjusting |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105458647B (en) |
Cited By (12)
| 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 |
| CN109238104A (en) * | 2018-11-21 | 2019-01-18 | 安徽江淮汽车集团股份有限公司 | A kind of double clutch axial clearance detection device and detection method |
| CN109339869A (en) * | 2018-11-30 | 2019-02-15 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine High Pressure Turbine Rotor centring means and its application method |
| CN109357595A (en) * | 2018-12-07 | 2019-02-19 | 中国航发南方工业有限公司 | The measurement method of axial gap between centrifugal impeller and impeller outer cover |
| 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 |
| CN111663970A (en) * | 2019-03-06 | 2020-09-15 | 中国航发商用航空发动机有限责任公司 | Aircraft engine assembling method |
| CN112112692A (en) * | 2019-06-19 | 2020-12-22 | 中国航发商用航空发动机有限责任公司 | Turbine assembling method and lifting appliance |
| CN114535982A (en) * | 2022-04-02 | 2022-05-27 | 中国航发沈阳发动机研究所 | Aeroengine doublestage high whirlpool stator unit body assembly fixture |
| CN114688100A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Assembly method of gas compressor of gas turbine engine |
| CN114918871A (en) * | 2022-06-29 | 2022-08-19 | 中国航发动力股份有限公司 | Rotor assembly frame and use method thereof |
| CN115319456A (en) * | 2022-07-06 | 2022-11-11 | 中国船舶重工集团公司第七0三研究所 | Method for assembling compressor casing of cylindrical gas turbine |
| CN115431013A (en) * | 2022-08-15 | 2022-12-06 | 北京动力机械研究所 | Turbofan engine case press-mounting device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4118847A (en) * | 1975-08-19 | 1978-10-10 | Stal-Laval Turbin Ab | Method of assembling a turbo-machine, apparatus for use in the method, and turbo machine constructed according to said method |
| FR2515734A1 (en) * | 1981-11-05 | 1983-05-06 | Snecma | SYSTEM FOR ADJUSTING THE CENTERING OF A TURBOMACHINE WHEEL AND TURBOMACHINE PROVIDED WITH MEANS FOR APPLYING SAID SYSTEM |
| US20090288291A1 (en) * | 2005-10-28 | 2009-11-26 | Man Turbo Ag | Device for the Lateral Fitting and Removal of a Compressor Barrel |
| CN102330605A (en) * | 2011-09-05 | 2012-01-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Heavy combustion engine assembling method for assembling rotor and front and rear supports in combining manner |
| CN103056653A (en) * | 2013-01-11 | 2013-04-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Bracket type core machine assembly method |
| CN103586827A (en) * | 2013-11-11 | 2014-02-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Axial-flow compressor unit body component assembling device and method |
-
2015
- 2015-11-20 CN CN201510812741.4A patent/CN105458647B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4118847A (en) * | 1975-08-19 | 1978-10-10 | Stal-Laval Turbin Ab | Method of assembling a turbo-machine, apparatus for use in the method, and turbo machine constructed according to said method |
| FR2515734A1 (en) * | 1981-11-05 | 1983-05-06 | Snecma | SYSTEM FOR ADJUSTING THE CENTERING OF A TURBOMACHINE WHEEL AND TURBOMACHINE PROVIDED WITH MEANS FOR APPLYING SAID SYSTEM |
| US20090288291A1 (en) * | 2005-10-28 | 2009-11-26 | Man Turbo Ag | Device for the Lateral Fitting and Removal of a Compressor Barrel |
| CN102330605A (en) * | 2011-09-05 | 2012-01-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Heavy combustion engine assembling method for assembling rotor and front and rear supports in combining manner |
| CN103056653A (en) * | 2013-01-11 | 2013-04-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Bracket type core machine assembly method |
| CN103586827A (en) * | 2013-11-11 | 2014-02-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Axial-flow compressor unit body component assembling device and method |
Cited By (18)
| 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 |
| CN109238104A (en) * | 2018-11-21 | 2019-01-18 | 安徽江淮汽车集团股份有限公司 | A kind of double clutch axial clearance detection device and detection method |
| CN109238104B (en) * | 2018-11-21 | 2020-05-05 | 安徽江淮汽车集团股份有限公司 | Double-clutch axial clearance detection device and detection method |
| CN109339869A (en) * | 2018-11-30 | 2019-02-15 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine High Pressure Turbine Rotor centring means and its 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 |
| 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 |
| CN109357595A (en) * | 2018-12-07 | 2019-02-19 | 中国航发南方工业有限公司 | The measurement method of axial gap between centrifugal impeller and impeller outer cover |
| CN111663970A (en) * | 2019-03-06 | 2020-09-15 | 中国航发商用航空发动机有限责任公司 | Aircraft engine assembling method |
| CN112112692A (en) * | 2019-06-19 | 2020-12-22 | 中国航发商用航空发动机有限责任公司 | Turbine assembling method and lifting appliance |
| CN114535982A (en) * | 2022-04-02 | 2022-05-27 | 中国航发沈阳发动机研究所 | Aeroengine doublestage high whirlpool stator unit body assembly fixture |
| CN114688100A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Assembly method of gas compressor of gas turbine engine |
| CN114918871A (en) * | 2022-06-29 | 2022-08-19 | 中国航发动力股份有限公司 | Rotor assembly frame and use method thereof |
| CN114918871B (en) * | 2022-06-29 | 2023-09-22 | 中国航发动力股份有限公司 | Rotor assembly frame and application method thereof |
| CN115319456A (en) * | 2022-07-06 | 2022-11-11 | 中国船舶重工集团公司第七0三研究所 | Method for assembling compressor casing of cylindrical gas turbine |
| CN115319456B (en) * | 2022-07-06 | 2023-12-05 | 中国船舶重工集团公司第七0三研究所 | Assembling method for cylindrical gas turbine compressor casing |
| CN115431013A (en) * | 2022-08-15 | 2022-12-06 | 北京动力机械研究所 | Turbofan engine case press-mounting device |
| CN115431013B (en) * | 2022-08-15 | 2024-04-09 | 北京动力机械研究所 | Turbofan engine casing press-fitting device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105458647B (en) | 2017-06-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105458647A (en) | Assembling method for power turbine without adjustment of axial gap between rotor and stator | |
| US8858155B2 (en) | Method and system for aligning a wind turbine component | |
| CN204195185U (en) | A kind of aero-engine low-pressure turbine assembling detection device | |
| CN105921996A (en) | Large unit coupling centering device and method | |
| KR101799354B1 (en) | Wind power generator and wind power generater system | |
| EP3428449B1 (en) | Drivetrain for a wind turbine and method for positioning a main bearing of said drivetrain | |
| CN203608039U (en) | Guiding tool for combining stator and rotor of permanent-magnet motor | |
| CN208548815U (en) | Horizontal permanent-magnetic synchronizes submersible motor kludge production platform | |
| CN204992958U (en) | Large -scale permanent -magnet machine decides, rotor attaches together device | |
| CN104265673A (en) | Fixing support for axial flow fan motor | |
| CN104052204A (en) | Assembling and positioning device for generator | |
| CN205101174U (en) | Wind -driven generator and wind -driven generator set | |
| CN204349739U (en) | A kind of three grades of concentric radial devices of motor | |
| CN208289377U (en) | Center adjusts tool when hydrogenerator upper spider is installed | |
| CN205130671U (en) | Electronic word machine that rolls of brake disc | |
| CN104079127A (en) | Processing method of bearing mounting holes in rotor covers of gyro machine, and fixture | |
| CN102734390A (en) | Gap-adjustable slewing drive device | |
| CN102624179B (en) | Support installation structure of coder for slip ring motor | |
| CN202428379U (en) | Device for assisting in assembling yaw system of wind generating set | |
| CN101915668B (en) | Dedicated base of fault simulation comprehensive experiment table for machine driven system | |
| CN204061276U (en) | A kind of fixed support for Axial-flow fan motor | |
| CN104088818A (en) | Aligning method of static blade fan for power plant | |
| CN204396635U (en) | A kind of punch process mould of constant velocity cardan joint | |
| CN219444936U (en) | Be applied to helium compressor shafting and casing installation device | |
| CN214560231U (en) | General processing frock in fan elbow cabin |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
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 |