CN112936016A - Engine rotor blade tip processingequipment - Google Patents
Engine rotor blade tip processingequipment Download PDFInfo
- Publication number
- CN112936016A CN112936016A CN202110228924.7A CN202110228924A CN112936016A CN 112936016 A CN112936016 A CN 112936016A CN 202110228924 A CN202110228924 A CN 202110228924A CN 112936016 A CN112936016 A CN 112936016A
- Authority
- CN
- China
- Prior art keywords
- oil
- blade
- oil cavity
- elastic sleeve
- positioning
- 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.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
- B24B19/14—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B41/00—Component parts such as frames, beds, carriages, headstocks
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B41/00—Component parts such as frames, beds, carriages, headstocks
- B24B41/06—Work supports, e.g. adjustable steadies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B49/00—Measuring or gauging equipment for controlling the feed movement of the grinding tool or work; Arrangements of indicating or measuring equipment, e.g. for indicating the start of the grinding operation
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the technical field of machining and discloses a machining device for a blade tip of an engine rotor. The freedom degree of a rotor blade of the compressor is completely restrained based on a hydraulic device, the rotor blade is ground under the condition that the blade is rigidly supported, the blade is enabled to move outwards along the radial direction after being assembled through a hydraulic expansion device to reach the maximum outer diameter size of the static state of the blade tip, then the freedom degree of the blade is completely restrained, the rigid support adopted by the blade can ensure that the blade does not move along the radial direction during grinding, and the size of the blade after grinding meets the requirements of parts. Compared with a high-speed grinding scheme for simulating the working state of the blade based on centrifugal force, the device has higher precision consistency and reliability.
Description
Technical Field
The invention belongs to the technical field of machining, and particularly relates to a machining device for a blade tip of an engine rotor.
Background
The gas compressor rotor of the aircraft engine mainly comprises rotor blades and an impeller disc, after the rotor blades are installed on the impeller disc, the radial freedom degree of the rotor blades is not completely limited, the blades can move a small amount along the radial direction of the impeller disc, the grinding precision requirement of the outer diameter of the blade tips of the gas compressor rotor blades is high, and the movement of the blades along the radial direction of the impeller disc during grinding is a main factor for restricting the blade tip grinding quality. The outer diameter of the blade tip of a rotor blade of the compressor is ground by adopting a high-speed grinding processing scheme, the scheme uses a special high-speed grinding machine to drive a wheel disc to rotate at a high speed, the blade on the wheel disc is forced to be pressed on the wheel disc by a high-speed radial centrifugal force, so that the blade tip reaches the maximum size, and the blade tip grinding is carried out by simulating the working state of the blade.
Disclosure of Invention
The invention aims to provide an engine rotor blade tip machining device, which completely restricts the freedom degree of a rotor blade of an air compressor based on a hydraulic device, grinds the rotor blade under the condition that the blade obtains rigid support, enables the blade to move outwards along the radial direction after being assembled through a hydraulic expansion device, achieves the maximum outer diameter size of the static state of the blade tip, and then completely restricts the freedom degree of the blade, and the rigid support adopted by the blade can ensure that the blade does not move along the radial direction during grinding, and ensures that the size of the blade after grinding meets the requirements of parts. Compared with a high-speed grinding scheme for simulating the working state of the blade based on centrifugal force, the device has higher precision consistency and reliability.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
an engine rotor blade tip machining device comprising: the first positioning plate, the second positioning plate, the central shaft, the first oil cavity, the second oil cavity, the first threaded pump and the second threaded pump are arranged on the central shaft;
the impeller disc is fixed between the first positioning disc and the second positioning disc, a first through hole is formed in the center of the first positioning disc, and a second through hole is formed in the center of the second positioning disc;
the central shaft sequentially passes through the first through hole, the impeller disc and the second through hole; the two ends of the central shaft are connected with a machine tool;
the first oil cavity is arranged in the first positioning disc, and the first threaded pump is communicated with the first oil cavity and used for supplying oil to the first oil cavity;
the second oil cavity is arranged in the second positioning plate, and the second thread pump is communicated with the second oil cavity and used for supplying oil to the second oil cavity;
the first oil chamber and the second oil chamber are made of an elastic material;
the outer side of the first oil cavity is connected with a first elastic sleeve, and the outer side of the second oil cavity is connected with a second elastic sleeve;
when the oil cavity expands, the elastic sleeve is pushed to jack the blade.
Further, the apparatus further comprises: a first accumulator and a second accumulator; the first energy accumulator is communicated with the first oil cavity, the second energy accumulator is communicated with the second oil cavity, and the energy accumulator is used for accumulating oil and pressure. When the oil cavity leaks, the energy accumulator can supplement oil and pressure for the oil cavity.
Further, the apparatus further comprises: a set screw; a plurality of positioning holes are symmetrically formed in the first positioning disc and the second positioning disc; the positioning screw penetrates through the positioning hole to position the impeller disc. The positioning screw is also used for tensioning the first positioning plate and the second positioning plate.
Further, the apparatus further comprises: a first pressure gauge and a second pressure gauge;
the first pressure gauge is communicated with the first oil chamber and used for detecting the pressure of the first oil chamber;
the second pressure gauge is communicated with the second oil chamber and used for detecting the pressure of the second oil chamber.
Furthermore, an annular step is arranged in the middle of the central shaft, and the left end face of the annular step is attached to the right end face of the first positioning disc. The annular step is used for limiting the central shaft.
Further, the first through hole and the central shaft of the first positioning disc are in interference fit.
Further, the device further comprises a screw; the screw is used for pressing the first positioning disc and the annular step. The first positioning disc is fixed with the annular step through screws and interference fit.
Furthermore, the second through hole of the second positioning plate is in clearance fit with the central shaft. The second positioning disc is detachable.
Further, the first oil chamber and the second oil chamber are both annular oil chambers;
the first elastic sleeve is annularly arranged and sleeved outside the first oil cavity,
the second elastic sleeve is annularly arranged and sleeved outside the second oil cavity,
a plurality of notches are formed in one sides, close to the impeller disc, of the first elastic sleeve and the second elastic sleeve, and the notches are used for splitting the first elastic sleeve and the second elastic sleeve; the number of the first elastic sleeve and the second elastic sleeve is the same as the number of the blades. The blades are jacked up through the split of the elastic sleeve.
The machining device for the blade tip of the engine rotor has the advantages that the freedom degree of the rotor blade of the compressor is completely restrained based on the hydraulic device, the rotor blade is ground under the condition that the blade obtains rigid support, the blade is enabled to move outwards along the radial direction after being assembled through the hydraulic expansion device, the maximum outer diameter size of the static state of the blade tip is achieved, then the freedom degree of the blade is completely restrained, the rigid support is adopted by the blade, the radial movement of the blade during grinding can be guaranteed, and the size of the blade after grinding can meet the requirements of parts. Compared with a high-speed grinding scheme for simulating the working state of the blade based on centrifugal force, the device has higher precision consistency and reliability.
Drawings
FIG. 1: a schematic structure diagram of an engine rotor blade tip machining device;
1-a first positioning plate, 2-a positioning screw, 3-a central shaft, 4-a first thread pump, 5-a first energy accumulator, 6-a first pressure gauge, 7-a first oil cavity, 8-a first elastic sleeve, 9-a second elastic sleeve and 10-a second positioning plate.
Detailed Description
The technical solution of the present invention is further explained with reference to the drawings and the detailed description.
An engine rotor blade tip machining device, as shown in fig. 1, includes: the hydraulic positioning device comprises a first positioning plate 1, a screw 2, a central shaft 3, a first threaded pump 4, a first energy accumulator 5, a first pressure gauge 6, a first oil cavity 7, a first elastic sleeve 8, a second elastic sleeve 9 and a second positioning plate 10. When the blade tip is machined, the blade is installed in the impeller disc and can move along the radial direction within a certain scale, and when the blade tip is finely machined, the blade needs to be ground when the diameter of the blade tip enveloping circle is the largest, so that the machining quality is ensured. The device completely restrains the freedom degree of the rotor blade of the compressor based on the hydraulic device, grinds the blade under the condition that the blade is supported, and has more advantages compared with centrifugal force support from the angle analysis and comparison of the output reliability of the supporting force; the first positioning plate 1, the second positioning plate 10 and the screws 2 are used for realizing the positioning and clamping functions of the equipment, and the first positioning plate can completely restrain the impeller plate on the technical equipment; the hydraulic control module of the device consists of a thread pump 4, an energy accumulator 5 and a pressure gauge 6 and is used for realizing quantitative output of supporting force; the first oil cavity 7, the first elastic sleeve 8 and the second elastic sleeve 9 are radial force mechanical output modules of the device, the petal-shaped elastic sleeves have good elastic deformation capacity, and sealing glue is filled among the expansion petals to prevent the oil cavity from being extruded out of the expansion petals. When the hydraulic oil pressurizing device works, hydraulic oil in the first oil cavity 1 and the second oil cavity 2 is pressurized through the threaded pump, so that the oil cavity 7 deforms, the expansion valve of the first elastic sleeve 8 and the expansion valve of the second elastic sleeve 9 deform, the top end of the expansion valve is in contact with the blade, the blade is located at a proper processing position, and support is provided. The tooling and the part to be processed are assembled to form a process system, and a mechanical interface connected with a machine tool is provided for the process system by the central shaft 3.
Before the device is used, a first positioning plate 1, a screw 2, a central shaft 3, a thread pump 4, an energy accumulator 5, a pressure gauge 6, a first oil cavity 7 and a first elastic sleeve 8 are assembled; the screw 2, the threaded pump 4, the energy accumulator 5, the pressure gauge 6, the first oil chamber 7, the second elastic sleeve 9 and the second positioning plate 10 are assembled. After the impeller disc and the rotor blades are assembled, the whole rotor is arranged on the first positioning disc 1 through the positioning inner hole of the impeller disc, then the second positioning disc 10 is arranged on the positioning hole on the other side of the impeller disc through the central shaft 3, and the screws 2 on the two sides are screwed to complete the positioning and the compressing of the rotor. The oil cavity 1 and the oil cavity 2 are pressurized through the threaded pumps 4 on the two sides respectively, the system pressure is read in real time through the pressure gauge 6, the first oil cavity 7 is deformed by hydraulic oil in the oil cavity 1 and the oil cavity 2, the expansion valve of the first elastic sleeve 8 and the expansion valve of the second elastic sleeve 9 are deformed, the top end of the expansion valve is in contact with the blade, the expansion valve is located at a proper machining position, and support is provided.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The utility model provides an engine rotor apex processingequipment which characterized in that: the device comprises: the first positioning plate, the second positioning plate, the central shaft, the first oil cavity, the second oil cavity, the first threaded pump and the second threaded pump are arranged on the central shaft;
the impeller disc is fixed between the first positioning disc and the second positioning disc, a first through hole is formed in the center of the first positioning disc, and a second through hole is formed in the center of the second positioning disc;
the central shaft sequentially passes through the first through hole, the impeller disc and the second through hole; the two ends of the central shaft are connected with a machine tool;
the first oil cavity is arranged in the first positioning disc, and the first threaded pump is communicated with the first oil cavity and used for supplying oil to the first oil cavity;
the second oil cavity is arranged in the second positioning plate, and the second thread pump is communicated with the second oil cavity and used for supplying oil to the second oil cavity;
the first oil chamber and the second oil chamber are made of an elastic material;
the outer side of the first oil cavity is connected with a first elastic sleeve, and the outer side of the second oil cavity is connected with a second elastic sleeve;
when the oil cavity expands, the elastic sleeve is pushed to jack the blade.
2. The engine rotor blade tip machining device according to claim 1, characterized in that: the device further comprises: a first accumulator and a second accumulator; the first energy accumulator is communicated with the first oil cavity, the second energy accumulator is communicated with the second oil cavity, and the energy accumulator is used for accumulating oil and pressure.
3. The engine rotor blade tip machining device according to claim 1, characterized in that: the device further comprises: a set screw; a plurality of positioning holes are symmetrically formed in the first positioning disc and the second positioning disc; the positioning screw penetrates through the positioning hole to position the impeller disc.
4. The engine rotor blade tip machining device according to claim 1, characterized in that: the device further comprises: a first pressure gauge and a second pressure gauge;
the first pressure gauge is communicated with the first oil chamber and used for monitoring the pressure of the first oil chamber;
the second pressure gauge is communicated with the second oil chamber and used for monitoring the pressure of the second oil chamber.
5. The engine rotor blade tip machining device according to claim 1, characterized in that:
the middle part of the central shaft is provided with an annular step, and the left end face of the annular step is attached to the right end face of the first positioning disc.
6. The engine rotor blade tip machining device according to claim 5, characterized in that:
the first through hole and the central shaft of the first positioning disc are in interference fit.
7. The engine rotor blade tip machining device according to claim 5, characterized in that:
the device further comprises a screw; the screw is used for pressing the first positioning disc and the annular step.
8. The engine rotor blade tip machining device according to claim 6, characterized in that:
and the second through hole of the second positioning plate is in clearance fit with the central shaft.
9. The engine rotor blade tip machining device according to claim 4, wherein:
the first oil chamber and the second oil chamber are both annular oil chambers;
the first elastic sleeve is annularly arranged and sleeved outside the first oil cavity,
the second elastic sleeve is annularly arranged and sleeved outside the second oil cavity,
a plurality of notches are formed in one sides, close to the impeller disc, of the first elastic sleeve and the second elastic sleeve, and the notches are used for splitting the first elastic sleeve and the second elastic sleeve; the number of the first elastic sleeve and the second elastic sleeve is the same as the number of the blades.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2021203555407 | 2021-02-09 | ||
| CN202120355540 | 2021-02-09 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112936016A true CN112936016A (en) | 2021-06-11 |
Family
ID=76247080
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110228924.7A Pending CN112936016A (en) | 2021-02-09 | 2021-03-02 | Engine rotor blade tip processingequipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112936016A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115122193A (en) * | 2022-08-05 | 2022-09-30 | 上海电气电站设备有限公司 | Auxiliary device for grinding wheel disc blade top |
Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070084053A1 (en) * | 2005-10-17 | 2007-04-19 | Pratt & Whitney Canada Corp. | Blade tip grinding tooling |
| CN101239497A (en) * | 2008-03-25 | 2008-08-13 | 哈尔滨东安发动机（集团）有限公司 | Protection method and mold for elastic valve-swelling type locating sleeve |
| CN101508077A (en) * | 2009-03-30 | 2009-08-19 | 北京北内设备工具有限公司 | High precision inner-pore positioning system using elastic expansion-sleeve |
| CN202527733U (en) * | 2012-03-21 | 2012-11-14 | 四川新达泵业有限责任公司 | Boring bar device of machining single-stage double-suction axially split pump |
| CN103158045A (en) * | 2011-12-19 | 2013-06-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Universal composite swelling device for blade grind |
| CN203146319U (en) * | 2012-11-23 | 2013-08-21 | 浙江台州先顶液压有限公司 | Vehicle hydraulic vane pump motor and switching control hydraulic system thereof |
| CN103267503A (en) * | 2013-04-24 | 2013-08-28 | 中国航空工业集团公司北京长城航空测控技术研究所 | Dynamic calibration test table of engine blade tip gap measurement sensor |
| CN104889706A (en) * | 2015-05-28 | 2015-09-09 | 北京航空航天大学 | Weak rigidity workpiece reverse segmental machining method and device |
| CN105171565A (en) * | 2015-10-20 | 2015-12-23 | 南京宁庆数控机床制造有限公司 | Portable airplane engine blade grinding machine |
| CN205309957U (en) * | 2015-12-05 | 2016-06-15 | 重庆市永川区益锐机械有限责任公司 | Vane pump rotor burring equipment |
| CN205799150U (en) * | 2016-06-22 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of positioner for grinding blade tip |
| CN106737011A (en) * | 2016-11-25 | 2017-05-31 | 沈阳黎明航空发动机(集团)有限责任公司 | The crown processing unit (plant) and method of a kind of low-pressure turbine blade |
| CN106737012A (en) * | 2016-12-21 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Turbine rotor grinder fixture |
| CN106737172A (en) * | 2016-12-21 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Grinding attachment |
| CN207058344U (en) * | 2017-07-28 | 2018-03-02 | 沈阳黎明法拉航空动力技术工程有限公司 | A kind of rotor disk blade tip grinding fixture |
| CN108115564A (en) * | 2017-12-18 | 2018-06-05 | 中国航发南方工业有限公司 | Reaction wheel blade tip grinding and clamping frock |
| CN108581520A (en) * | 2018-04-12 | 2018-09-28 | 宁波海天精工股份有限公司 | A kind of hydraulic pump end cap processing self-centering hydraulic pressure fixture |
| CN109209641A (en) * | 2018-10-31 | 2019-01-15 | 中国科学院工程热物理研究所 | A kind of connection structure of engine rotor assemblies |
| CN208395275U (en) * | 2018-05-24 | 2019-01-18 | 成都青石激光科技有限公司 | A kind of cooling device for being gripped in compressor blade laser repair process |
| CN111335966A (en) * | 2020-03-25 | 2020-06-26 | 中国航发哈尔滨东安发动机有限公司 | Variable blade tip size control mounting structure of high-speed engine compressor |
-
2021
- 2021-03-02 CN CN202110228924.7A patent/CN112936016A/en active Pending
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070084053A1 (en) * | 2005-10-17 | 2007-04-19 | Pratt & Whitney Canada Corp. | Blade tip grinding tooling |
| CN101239497A (en) * | 2008-03-25 | 2008-08-13 | 哈尔滨东安发动机（集团）有限公司 | Protection method and mold for elastic valve-swelling type locating sleeve |
| CN101508077A (en) * | 2009-03-30 | 2009-08-19 | 北京北内设备工具有限公司 | High precision inner-pore positioning system using elastic expansion-sleeve |
| CN103158045A (en) * | 2011-12-19 | 2013-06-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Universal composite swelling device for blade grind |
| CN202527733U (en) * | 2012-03-21 | 2012-11-14 | 四川新达泵业有限责任公司 | Boring bar device of machining single-stage double-suction axially split pump |
| CN203146319U (en) * | 2012-11-23 | 2013-08-21 | 浙江台州先顶液压有限公司 | Vehicle hydraulic vane pump motor and switching control hydraulic system thereof |
| CN103267503A (en) * | 2013-04-24 | 2013-08-28 | 中国航空工业集团公司北京长城航空测控技术研究所 | Dynamic calibration test table of engine blade tip gap measurement sensor |
| CN104889706A (en) * | 2015-05-28 | 2015-09-09 | 北京航空航天大学 | Weak rigidity workpiece reverse segmental machining method and device |
| CN105171565A (en) * | 2015-10-20 | 2015-12-23 | 南京宁庆数控机床制造有限公司 | Portable airplane engine blade grinding machine |
| CN205309957U (en) * | 2015-12-05 | 2016-06-15 | 重庆市永川区益锐机械有限责任公司 | Vane pump rotor burring equipment |
| CN205799150U (en) * | 2016-06-22 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of positioner for grinding blade tip |
| CN106737011A (en) * | 2016-11-25 | 2017-05-31 | 沈阳黎明航空发动机(集团)有限责任公司 | The crown processing unit (plant) and method of a kind of low-pressure turbine blade |
| CN106737012A (en) * | 2016-12-21 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Turbine rotor grinder fixture |
| CN106737172A (en) * | 2016-12-21 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Grinding attachment |
| CN207058344U (en) * | 2017-07-28 | 2018-03-02 | 沈阳黎明法拉航空动力技术工程有限公司 | A kind of rotor disk blade tip grinding fixture |
| CN108115564A (en) * | 2017-12-18 | 2018-06-05 | 中国航发南方工业有限公司 | Reaction wheel blade tip grinding and clamping frock |
| CN108581520A (en) * | 2018-04-12 | 2018-09-28 | 宁波海天精工股份有限公司 | A kind of hydraulic pump end cap processing self-centering hydraulic pressure fixture |
| CN208395275U (en) * | 2018-05-24 | 2019-01-18 | 成都青石激光科技有限公司 | A kind of cooling device for being gripped in compressor blade laser repair process |
| CN109209641A (en) * | 2018-10-31 | 2019-01-15 | 中国科学院工程热物理研究所 | A kind of connection structure of engine rotor assemblies |
| CN111335966A (en) * | 2020-03-25 | 2020-06-26 | 中国航发哈尔滨东安发动机有限公司 | Variable blade tip size control mounting structure of high-speed engine compressor |
Non-Patent Citations (2)
| Title |
|---|
| 刘海涛等: "定桨距风机叶尖扰流器的故障分析", 《黑龙江科技信息》, no. 30, 25 October 2014 (2014-10-25), pages 81 * |
| 胡运林: "《机械制造工艺与实施》", 30 July 2011, 冶金工业出版社, pages: 113 - 114 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115122193A (en) * | 2022-08-05 | 2022-09-30 | 上海电气电站设备有限公司 | Auxiliary device for grinding wheel disc blade top |
| CN115122193B (en) * | 2022-08-05 | 2024-03-19 | 上海电气电站设备有限公司 | Wheel disc blade top grinding auxiliary device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107131234B (en) | Brake built-in rotary table and its brake control method | |
| CN112936016A (en) | Engine rotor blade tip processingequipment | |
| CN108214040B (en) | Clamp for improving balance accuracy of wheel | |
| CN103884504A (en) | Axial force bearing test structure of elastic foil dynamic pressure gas thrust bearings | |
| CN103100970B (en) | Rotating sealing device capable of polishing with air | |
| CN107790804A (en) | A kind of lithium battery electrode plate cutting device and its assembly technology | |
| CN101701588A (en) | Method for assembling impeller and high speed rotating shaft, and special tool thereof | |
| CN103111946A (en) | Fixture for abrasive flow polishing of blisk | |
| CN104209860A (en) | Special flat floating fixture for precision honing machine | |
| CN208262533U (en) | A kind of super-huge numerical control vertical grinding machine | |
| CN104100637B (en) | Protection mechanism and lathe with the supporting dynamic and hydrostatic bearing of machine tool chief axis | |
| CN113118799B (en) | Workpiece clamping device and machine tool | |
| CN216051159U (en) | Axial loading test equipment | |
| CN112483650A (en) | Radial support and oil cavity seal of gas compressor | |
| CN207494664U (en) | A kind of lithium battery electrode plate cutting device | |
| CN206839620U (en) | Processing jig | |
| CN112355813B (en) | Vertical grinding device for turbine rotor blade tips | |
| CN103397913B (en) | A kind of low-pressure turbine band stator counterbalanced procedure | |
| CN210849435U (en) | Dividing head holding device | |
| CN114161273A (en) | Clamp for grinding and clamping workpiece at tip of gas turbine rotor | |
| CN112483456A (en) | Axial stop support and oil cavity seal of gas compressor | |
| CN113829131B (en) | Turbine disc blade grinding device | |
| CN106984992B (en) | Spindle nose holding system and numerical control machining center | |
| CN220680139U (en) | Five revolving stages of oil formula of stopping | |
| CN221109517U (en) | Tool for preparing expansion joint on stator shielding sleeve |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210611 |