CN107932057B - A kind of aero-engine power turbine torch measuring system assembly method - Google Patents
A kind of aero-engine power turbine torch measuring system assembly method Download PDFInfo
- Publication number
- CN107932057B CN107932057B CN201711126631.8A CN201711126631A CN107932057B CN 107932057 B CN107932057 B CN 107932057B CN 201711126631 A CN201711126631 A CN 201711126631A CN 107932057 B CN107932057 B CN 107932057B
- Authority
- CN
- China
- Prior art keywords
- connecting hole
- core rod
- output shaft
- cylindrical section
- power turbine
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000005259 measurement Methods 0.000 claims description 29
- 238000003825 pressing Methods 0.000 claims description 20
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 8
- 230000006835 compression Effects 0.000 claims description 7
- 238000007906 compression Methods 0.000 claims description 7
- 230000005284 excitation Effects 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 4
- 229910052757 nitrogen Inorganic materials 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 238000012797 qualification Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 210000003734 kidney Anatomy 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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
- B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A kind of aero-engine power turbine torch measuring system assembly method, the aero-engine power turbine torch measuring system is formed by passing through reference axis, output shaft, clamping sleeve, reference rings that two latch successively connect from inside to outside, it includes the following steps: step A, one the first plug is provided and assembles the clamping sleeve, step B provides second plug and assembles the reference rings.A kind of aero-engine power turbine torch measuring system assembly method provided by the present invention can ensure datum tooth and survey and turn round tooth angle degree and disposably assemble qualification, latch once mounting in place, to provide production efficiency significantly.
Description
Technical Field
The invention relates to the technical field of assembly of aero-engines, in particular to an assembly method of a torque measurement system of a power turbine rotor of an aero-engine.
Background
Fig. 1 is a schematic diagram of a partial cross-sectional structural principle of an aeroengine power turbine rotor torque measurement system, fig. 2 is a schematic diagram of an a-a cross-sectional structural principle of fig. 1, fig. 2 mainly illustrates a positional relationship between a torque measurement tooth and a reference tooth, and as shown in fig. 1-2, the aeroengine power turbine rotor torque measurement system is composed of a reference shaft 1, an output shaft 2, a pressing sleeve 3 and a reference ring 4 which are sequentially connected from inside to outside through two stop pins 5, the pressing sleeve 3 is provided with two excitation teeth which are symmetrically distributed at 180 degrees, that is, the torque measurement tooth 31, the reference ring 4 is provided with two reference teeth 41 which are symmetrically distributed at 180 degrees, and the torque measurement tooth 31 and the reference teeth 41 form a typical torque measurement structure.
Fig. 3 is a schematic structural diagram of the output shaft and the reference shaft in an assembled state of fig. 1, and referring to fig. 3, the stop pin 5 is a cylindrical pin, the first connecting hole 11 of the reference shaft 1 for connecting the stop pin 5 is a circular hole, the second connecting hole 21 of the output shaft 2 for connecting the stop pin 5 is a kidney-shaped hole, and a maximum dimension L2 of the second connecting hole 21 in a radial direction of the output shaft 1 is greater than a diameter of the stop pin 5. The shape and the size of a third connecting hole of the pressing sleeve 3 for connecting the stop pin 5 are the same as those of the second connecting hole 21, and the shape and the size of a fourth connecting hole of the reference ring 4 for connecting the stop pin 5 are the same as those of the first connecting hole 11. The stop pin 5 is in interference fit with the reference shaft 2 and the reference ring 4. For example, the diameter D1 of the first connection hole 11 may be 0.01mm larger than the diameter of the stopper pin 5, which means that the diameter of the fourth connection hole is 0.01mm larger than the diameter of the stopper pin 5.
Referring to fig. 2, in an assembly process of the aeroengine power turbine rotor torque measurement system shown in fig. 1, a reference included angle α, which guarantees that the torque measurement tooth 31 and the axis of the reference tooth 41 are assembly key points and difficulties, the reference included angle α may be an included angle between the torque measurement tooth 31 and the reference tooth 41 at the upper left corner of an a-a viewing angle, and the numerical range of the included angle needs to be 90 ° (-20 °), if the included angle α is not qualified, the accuracy of sensor measurement data is directly affected, and a serious safety hazard is caused to an engine.
Disclosure of Invention
The technical problem to be solved by the present invention is to provide an assembly method for a torque measurement system of a power turbine rotor of an aircraft engine, so as to reduce or avoid the aforementioned problems.
In order to solve the technical problem, the invention provides an assembly method of a torque measurement system of a power turbine rotor of an aero-engine, the torque measurement system of the power turbine rotor of the aero-engine consists of a reference shaft, an output shaft, a compression sleeve and a reference ring which are sequentially connected from inside to outside through two stop pins, the compression sleeve is provided with two excitation teeth which are symmetrically distributed at 180 degrees, namely torsion measuring teeth, the reference ring is provided with two reference teeth which are symmetrically distributed at 180 degrees, the stop pins are cylindrical pins, a first connecting hole for connecting the stop pins with the reference shaft is a circular hole, a second connecting hole for connecting the stop pins with the output shaft is a kidney-shaped hole, and the maximum size of the second connecting hole in the radial direction of the output shaft is larger than the diameter of the stop pins. The third connecting hole of the pressing sleeve for connecting the stop pin is the same as the second connecting hole in shape and size, and the fourth connecting hole of the reference ring for connecting the stop pin is the same as the first connecting hole in shape and size. The stop pin respectively with the reference shaft, the reference ring is interference fit, just compress tightly the cover with the output shaft also is interference fit, and it includes following step:
step A, assembling the pressing sleeve, providing a first core rod, wherein the first core rod comprises a first cylindrical section and a kidney-shaped cylindrical section, the diameter of the first cylindrical section is 0.01-0.02mm smaller than that of the first connecting hole of the reference shaft,
a maximum radial dimension of the kidney-shaped column section is ═ the maximum dimension of the second connection hole- [ (pi × (output shaft outer diameter/360) × (90 ° - ∠ a) ],
in the above formula, the value of ∠ A is the numerical range of the reference included angle between the torque measuring teeth and the axis of the reference teeth,
firstly, the output shaft is sleeved on the reference shaft, the first connecting hole corresponds to the second connecting hole, then the compressing sleeve is quickly sleeved on the output shaft after being heated, the first core rod is inserted, the first cylindrical section is inserted into the first connecting hole, then the compressing sleeve is rotated, the torsion measuring tooth moves to the interval of the reference included angle until the compressing sleeve is tightly attached to the kidney-shaped column section, and after the compressing sleeve is cooled, the first core rod is pulled down.
Step B, assembling the reference ring, providing a second core rod, wherein the second core rod comprises a second cylindrical section and a handle means, the diameter of the second cylindrical section is 0.01-0.02mm smaller than the diameter of the circular hole of the reference shaft, the length of the second cylindrical section is larger than or equal to that of the stop pin, the reference ring is sleeved on the compression sleeve installed in the step A, so that the fourth connecting hole corresponds to the third connecting hole, and the two opposite third connecting holes are positioned in the horizontal position, the second core rod is inserted into one fourth connecting hole, the second cylindrical section is inserted into the bottom of the first connecting hole, then the stop pin is assembled in place in the fourth connecting hole at the other end, and then the second core rod is removed, and assembling a second stop pin in place at the corresponding position, so as to complete the assembly of the aeroengine power turbine rotor torque measuring system.
Preferably, in step a, ∠ a has a value in the range of 90 ° (-1 ° -40').
Preferably, in step B, the stop pin is cooled by liquid nitrogen before being assembled.
The assembly method of the aero-engine power turbine rotor torque measurement system provided by the invention can ensure that the angles of the reference tooth and the torque measurement tooth are qualified in one-time assembly, and the stop pin is installed in place in one time, so that the production efficiency is greatly improved.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,
FIG. 1 is a schematic partial cross-sectional structural view of an aircraft engine power turbine rotor torque measurement system;
FIG. 2 is a schematic cross-sectional view A-A of FIG. 1;
FIG. 3 is a schematic view of the output shaft and reference shaft of FIG. 1 in an assembled state;
FIG. 4 is a schematic perspective view of a first mandrel for a method of assembling an aircraft engine power turbine rotor torque measurement system according to an exemplary embodiment of the present invention;
FIG. 5 is a schematic cross-sectional structural view of the kidney column section of FIG. 4;
FIG. 6 is a schematic view of the operation of the first mandrel of FIG. 4;
FIG. 7 is a schematic perspective view of a second mandrel used in conjunction with the first mandrel of FIG. 4;
fig. 8 is a schematic structural view of the second mandrel of fig. 7.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
FIG. 1 is a schematic partial cross-sectional structural view of an aircraft engine power turbine rotor torque measurement system; FIG. 2 is a schematic cross-sectional view A-A of FIG. 1; FIG. 3 is a schematic view of the output shaft and reference shaft of FIG. 1 in an assembled state; FIG. 4 is a schematic perspective view of a first mandrel for a method of assembling an aircraft engine power turbine rotor torque measurement system according to an exemplary embodiment of the present invention; FIG. 5 is a schematic cross-sectional structural view of the kidney column section of FIG. 4; FIG. 6 is a schematic view of the operation of the first mandrel of FIG. 4; FIG. 7 is a schematic perspective view of a second mandrel used in conjunction with the first mandrel of FIG. 4; fig. 8 is a schematic structural view of the second mandrel of fig. 7. Referring to fig. 1-8, the invention provides an assembly method of a torque measurement system of a power turbine rotor of an aero-engine, the torque measurement system of the power turbine rotor of the aero-engine is composed of a reference shaft 1, an output shaft 2, a pressing sleeve 3 and a reference ring 4 which are sequentially connected from inside to outside through two stop pins 5, the pressing sleeve 3 is provided with two excitation teeth which are symmetrically distributed at 180 degrees, namely a torque measurement tooth 31, the reference ring 4 is provided with two reference teeth 41 which are symmetrically distributed at 180 degrees, the stop pins 5 are cylindrical pins, a first connecting hole 11 of the reference shaft 1 for connecting the stop pins 5 is a circular hole, a second connecting hole 21 of the output shaft 2 for connecting the stop pins 5 is a kidney-shaped hole, and the maximum dimension L2 of the second connecting hole 21 in the radial direction of the output shaft 1 is greater than the diameter of the stop pins 5. The shape and the size of a third connecting hole of the pressing sleeve 3 for connecting the stop pin 5 are the same as those of the second connecting hole 21, and the shape and the size of a fourth connecting hole of the reference ring 4 for connecting the stop pin 5 are the same as those of the first connecting hole 11. The stop pin 5 respectively with reference shaft 1, reference ring 4 is interference fit, just compress tightly cover 3 with output shaft 1 also is interference fit, and it includes following step:
step A, assembling the pressing sleeve 3, providing a first core rod 6, wherein the first core rod 6 comprises a first cylindrical section 61 and a kidney-shaped cylindrical section 62, the diameter of the first cylindrical section 61 is 0.01-0.02mm smaller than the diameter D1 of the first connecting hole 11 of the reference shaft 1,
the radial maximum dimension L1 of the kidney-shaped column section 62 is the maximum dimension L2- [ (pi) the output shaft 1 outer diameter D/360 (90 ° - ∠ a) ] of the second connection hole 21,
in the above formula, the value range of ∠ a is the numerical range of the reference included angle α between the torque measuring teeth 31 and the axis of the reference teeth 41,
for example, as described in the background, since the reference angle α has a value range of 90 ° (-20 'to-1 ° 20'), ∠ a may have a value of 89 ° 80 ', 80 °, or 88 ° 80'.
Firstly, the output shaft 2 is sleeved on the reference shaft 1, so that the first connection hole 11 corresponds to the second connection hole 21, then the pressing sleeve 3 is heated and then quickly sleeved on the output shaft 2, the first mandrel 6 is inserted, so that the first cylindrical section 62 is inserted into the first connection hole 11, then the pressing sleeve 3 is rotated, so that the torque measuring teeth 31 move to the interval of the reference included angle α until the pressing sleeve 3 is tightly attached to the kidney-shaped cylindrical section 62, and after the pressing sleeve 3 is cooled, the first mandrel 6 is pulled down.
As described in the background art, the stop pin 5 is in interference fit with the reference shaft 1 and the reference ring 4, and the pressing sleeve 3 is in interference fit with the output shaft 2, so that the positions of the torque measuring teeth 31 and the reference teeth 41 can be ensured as long as the positions of the torque measuring teeth 31 and the reference shaft 1 can be ensured during assembly. The invention enables the pressing sleeve 3 to be assembled in place at one time through the first mandrel 6,
referring to fig. 2 and 6, after the pressing sleeve 3 is rotated, a symmetry plane 300 of the third connecting hole perpendicular to the axis of the reference shaft 1 is displaced, that is, the symmetry plane 300 is separated from the axis 100 of the first core rod 6, that is, the torque measuring teeth 31 forming the reference included angle α are moved toward the section of the reference included angle α, so that the pressing sleeve 3 can be ensured to be installed in place at one time by controlling the maximum radial dimension L1 of the kidney-shaped column section 62.
The value of ∠ a can be further reduced in the range of the reference angle α to account for fit errors, for example, ∠ a can be chosen to be 90 ° (-1 to-40').
Step B, assembling the reference ring 4, providing a second core rod 7, wherein the second core rod 7 comprises a second cylindrical section 71 and a handle section 72, the diameter of the second cylindrical section 71 is 0.01-0.02mm smaller than the diameter D1 of the circular hole 21 of the reference shaft 2, the length L3 of the second cylindrical section 71 is greater than or equal to the length L4 of the stop pin 5, sleeving the reference ring 4 on the pressing sleeve 3 installed in the step A, enabling the fourth connecting hole to correspond to the third connecting hole, enabling two opposite third connecting holes to be located in a horizontal position, inserting the second core rod 7 into one fourth connecting hole, enabling the second cylindrical section 71 to be inserted to the bottom of the first connecting hole 11, then assembling the stop pin 5 in place in the fourth connecting hole at the other end, then removing the second core rod 7, and assembling a second stop pin 5 in place at the corresponding position, and assembling the aeroengine power turbine rotor torque measuring system.
After the assembly of the pressing sleeve 3 in step a is completed, the positional relationship between the torque measuring tooth 31 and the first connecting hole 11 is determined, and the stop pin 5, the first connecting hole 11 and the fourth connecting hole are in interference fit, so that the initial positioning of the reference ring 4 and the reference shaft 1 can be completed by inserting the second cylindrical section 71 into the bottom of the first connecting hole 11, then the stop pin 5 is assembled in place from the fourth connecting hole to the first connecting hole 11 at the other end, the position of the reference tooth 41 can be fixed, then the second core rod 7 is taken out, and the stop pin 5 is assembled in place at one side of the vacated fourth connecting hole, so that the whole assembly process can be completed.
In the process of assembling the stopper pin 5, the stopper pin 5 may be directly driven in by using a tool such as a hammer in a normal temperature state, or the stopper pin 5 may be cooled by liquid nitrogen (for example, by immersing in liquid nitrogen for 5 minutes) and then installed.
The holding means 72 is mainly used for facilitating the holding operation of the second core rod 7, and therefore the holding means 72 may be provided with a flat surface portion as shown in fig. 7 and 8, thereby facilitating the holding with a tool.
The assembly method of the aero-engine power turbine rotor torque measurement system provided by the invention can ensure that the angles of the reference tooth and the torque measurement tooth are qualified in one-time assembly, and the stop pin is installed in place in one time, so that the production efficiency is greatly improved.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (2)
1. An assembly method of a torque measurement system of a power turbine rotor of an aero-engine is characterized in that the torque measurement system of the power turbine rotor of the aero-engine consists of a reference shaft, an output shaft, a compression sleeve and a reference ring which are sequentially connected from inside to outside through two stop pins, the compression sleeve is provided with two excitation teeth which are symmetrically distributed at 180 degrees, namely torque measurement teeth, the reference ring is provided with two reference teeth which are symmetrically distributed at 180 degrees, the stop pins are cylindrical pins, a first connecting hole for connecting the stop pins with the reference shaft is a circular hole, a second connecting hole for connecting the stop pins with the output shaft is a kidney-shaped hole, the maximum size of the second connecting hole in the radial direction of the output shaft is larger than the diameter of the stop pins, a third connecting hole for connecting the stop pins with the compression sleeve is the same as the second connecting hole in shape and size, the fourth connecting hole that the benchmark ring is used for connecting the stop pin with first connecting hole shape, size are the same, the stop pin respectively with the benchmark axle, the benchmark ring is interference fit, just compress tightly the cover with the output shaft also is interference fit, and it includes following step:
step A, assembling the pressing sleeve, providing a first core rod, wherein the first core rod comprises a first cylindrical section and a kidney-shaped cylindrical section, the diameter of the first cylindrical section is 0.01-0.02mm smaller than that of the first connecting hole of the reference shaft,
a maximum radial dimension of the kidney-shaped column section is ═ the maximum dimension of the second connection hole- [ (pi × (output shaft outer diameter/360) × (90 ° - ∠ a) ],
in the above formula, the value range of ∠ A is the numerical range of the reference included angle between the torque measuring teeth and the axis of the reference teeth,
firstly, the output shaft is sleeved on the reference shaft, so that the first connecting hole corresponds to the second connecting hole, then the compressing sleeve is heated and then quickly sleeved on the output shaft, the first core rod is inserted, so that the first cylindrical section is inserted into the first connecting hole, then the compressing sleeve is rotated, so that the torque measuring teeth move to the interval of the reference included angle until the compressing sleeve is tightly attached to the waist-shaped column section, after the compressing sleeve is cooled, the first core rod is pulled down,
step B, assembling the reference ring, providing a second core rod, wherein the second core rod comprises a second cylindrical section and a handle means, the diameter of the second cylindrical section is 0.01-0.02mm smaller than the diameter of the circular hole of the reference shaft, the length of the second cylindrical section is larger than or equal to that of the stop pin, the reference ring is sleeved on the compression sleeve installed in the step A, so that the fourth connecting hole corresponds to the third connecting hole, and the two opposite third connecting holes are positioned in the horizontal position, the second core rod is inserted into one fourth connecting hole, the second cylindrical section is inserted into the bottom of the first connecting hole, then the stop pin is assembled in place in the fourth connecting hole at the other end, and then the second core rod is removed, and assembling a second stop pin in place at the corresponding position, so as to complete the assembly of the aeroengine power turbine rotor torque measuring system.
2. A method according to claim 1, wherein in step B, the retaining pin is cooled with liquid nitrogen prior to being installed during assembly of the retaining pin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711126631.8A CN107932057B (en) | 2017-11-15 | 2017-11-15 | A kind of aero-engine power turbine torch measuring system assembly method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711126631.8A CN107932057B (en) | 2017-11-15 | 2017-11-15 | A kind of aero-engine power turbine torch measuring system assembly method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107932057A CN107932057A (en) | 2018-04-20 |
| CN107932057B true CN107932057B (en) | 2019-05-24 |
Family
ID=61932249
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711126631.8A Active CN107932057B (en) | 2017-11-15 | 2017-11-15 | A kind of aero-engine power turbine torch measuring system assembly method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107932057B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112008351B (en) * | 2020-07-10 | 2021-11-19 | 中国航发南方工业有限公司 | Torsion measuring ring assembling method and clamp |
| CN111982369B (en) * | 2020-07-27 | 2022-05-17 | 中国航发湖南动力机械研究所 | Output shaft torsion measuring method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202582802U (en) * | 2012-05-16 | 2012-12-05 | 郑州机械研究所 | Distortion transmission measurement device used for gear shaft extra large-range torque measurement |
| CN204479221U (en) * | 2015-01-09 | 2015-07-15 | 哈尔滨东安发动机（集团）有限公司 | Engine electricity instrument measuring torsional vibration |
| KR20150089799A (en) * | 2014-01-28 | 2015-08-05 | 주식회사 일진 | Device and method for processing ball joint |
| CN106481680A (en) * | 2016-12-13 | 2017-03-08 | 三汽车制造有限公司 | The mounting assembly of torque sensor |
| CN107246945A (en) * | 2017-05-19 | 2017-10-13 | 哈尔滨工程大学 | A kind of measuring system of dynamic twisting vibration transmission function |
-
2017
- 2017-11-15 CN CN201711126631.8A patent/CN107932057B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202582802U (en) * | 2012-05-16 | 2012-12-05 | 郑州机械研究所 | Distortion transmission measurement device used for gear shaft extra large-range torque measurement |
| KR20150089799A (en) * | 2014-01-28 | 2015-08-05 | 주식회사 일진 | Device and method for processing ball joint |
| CN204479221U (en) * | 2015-01-09 | 2015-07-15 | 哈尔滨东安发动机（集团）有限公司 | Engine electricity instrument measuring torsional vibration |
| CN106481680A (en) * | 2016-12-13 | 2017-03-08 | 三汽车制造有限公司 | The mounting assembly of torque sensor |
| CN107246945A (en) * | 2017-05-19 | 2017-10-13 | 哈尔滨工程大学 | A kind of measuring system of dynamic twisting vibration transmission function |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107932057A (en) | 2018-04-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10414055B2 (en) | Robotic end effector quick change mechanism with switchable magnetic coupler with moment support | |
| CN107932057B (en) | A kind of aero-engine power turbine torch measuring system assembly method | |
| EP2120313B1 (en) | Electrical motor and method for manufacturing the same | |
| CA3026073C (en) | Alignment sub with deformable sleeve | |
| US4519672A (en) | Method for obtaining an accurate concentric fastening of an optical fibre in a connector | |
| US20160319820A1 (en) | Method of assembling a set of impellers through tie rods impeller and turbomachine | |
| CN104967263B (en) | A kind of oscillating motor coil winding arrangement and the method for coiling | |
| EP3315808B1 (en) | Method for manufacturing universal joint | |
| CN105345514A (en) | Clamp | |
| CN111835106A (en) | Stator core fixing structure of double-rotor motor | |
| JP6775579B2 (en) | Ring gear for planetary reducer | |
| CN111015153B (en) | Method and device for assembling multiple shaft parts with angular requirements in deep hole | |
| CN209767350U (en) | Tool for positioning high-low temperature vacuum stepping motor rotor core | |
| CN112405411A (en) | Bearing limit pin assembling tool and using method thereof | |
| CN107246835B (en) | Stator and rotor air gap external drive internal micrometer | |
| CN204947849U (en) | A kind of sectional type armature splicing positioner | |
| CN105136005A (en) | Tool and method for checking hole axis deviations | |
| CN220204453U (en) | Motor shaft for pump | |
| CN205184323U (en) | Clamp | |
| CN109474141A (en) | A kind of permanent magnet motor stator processing tool and its operating method | |
| CN210280522U (en) | Steel wire cap manufacturing tool | |
| CN113927253B (en) | Machining method of porous precision rotating part | |
| JP5996578B2 (en) | Manufacturing method of spark plug | |
| JPS62157731A (en) | Manufacture of rotor for air motor | |
| CN112008351B (en) | Torsion measuring ring assembling method and clamp |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |