CN115502839A - Grinding wheel operating device special for turbine blade of aircraft engine - Google Patents

Grinding wheel operating device special for turbine blade of aircraft engine Download PDF

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Publication number
CN115502839A
CN115502839A CN202211227749.0A CN202211227749A CN115502839A CN 115502839 A CN115502839 A CN 115502839A CN 202211227749 A CN202211227749 A CN 202211227749A CN 115502839 A CN115502839 A CN 115502839A
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CN
China
Prior art keywords
blade
turbine blade
driving
driving motor
grinding
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.)
Withdrawn
Application number
CN202211227749.0A
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Chinese (zh)
Inventor
韦球
李笑天
翁朝阳
许涛
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Zhuhai Shawei Technology Co ltd
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Zhuhai Shawei Technology Co ltd
Priority date (The priority date 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 date listed.)
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Publication date
Application filed by Zhuhai Shawei Technology Co ltd filed Critical Zhuhai Shawei Technology Co ltd
Priority to CN202211227749.0A priority Critical patent/CN115502839A/en
Publication of CN115502839A publication Critical patent/CN115502839A/en
Withdrawn legal-status Critical Current

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    • 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
    • B24B47/00—Drives or gearings; Equipment therefor
    • B24B47/10—Drives or gearings; Equipment therefor for rotating or reciprocating working-spindles carrying grinding wheels or workpieces
    • B24B47/12—Drives or gearings; Equipment therefor for rotating or reciprocating working-spindles carrying grinding wheels or workpieces by mechanical gearing or electric power
    • 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
    • B24B51/00—Arrangements for automatic control of a series of individual steps in grinding a workpiece

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)

Abstract

The invention belongs to the technical field of machining of turbine blades of aero-engines, and particularly relates to a special grinding wheel running device for turbine blades of aero-engines. This special emery wheel running device of aeroengine turbine blade, remove fixture and blade grinding mechanism through setting up the blade, when using, remove fixture through controller automatic control and drive turbine blade and do horizontal and longitudinal motion on unable adjustment base's surface, cooperation blade grinding mechanism carries out the curved surface to turbine blade and polishes, thereby the surface of having solved current turbine engine blade is the variable cross section curved surface of distortion, the shape is complicated, ordinary grinding device is difficult to carry out the problem of polishing to the variable cross section curved surface of distortion.

Description

Grinding wheel operating device special for turbine blade of aircraft engine
Technical Field
The invention relates to the technical field of machining of turbine blades of aero-engines, in particular to a special grinding wheel operating device for turbine blades of aero-engines.
Background
The aircraft engine is a highly complex and precise thermal machine, is used as the heart of an aircraft, is not only the power of the aircraft flight, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aircraft engine. After centuries of development, the aero-engine has developed into a mature product with extremely high reliability, and the aero-engine in use includes various types such as a turbojet/turbofan engine, a turboshaft/turboprop engine, a ramjet engine and a piston engine, and not only is the power of military and civil aircrafts, unmanned planes and cruise missiles for various purposes, but also the gas turbine developed by the aero-engine is widely used in the fields such as ground power generation, marine power, mobile power stations, natural gas and petroleum pipeline pump stations and the like.
Turbine blades are important components of the turbine section of a gas turbine engine. The blades rotating at high speed are responsible for drawing high-temperature and high-pressure airflow into the combustor to maintain the operation of the engine. In order to ensure stable and long-term operation in extreme environments of high temperature and high pressure, turbine blades are often forged from high temperature alloys and are cooled in different ways, such as internal air flow cooling, boundary layer cooling, or thermal barrier coatings protecting the blades, to ensure operational reliability. In steam and gas turbine engines, metal fatigue of the blades is the leading cause of engine failure. Strong vibration or resonance can cause metal fatigue. Engineers often employ friction dampers to reduce damage to the blades from these factors.
Turbine engine blades are generally subjected to high operating stresses and high operating temperatures, and the stresses and temperatures are also subject to frequent and severe variations, and moreover have problems of corrosion and wear, which impose very severe requirements on the operating conditions and therefore require high machining precision of the blades. Meanwhile, in order to improve the turbine efficiency, the surface shape of the turbine blade is generally designed to be a twisted variable cross-section curved surface, and the shape is complex.
In the process of producing and processing the turbine engine blade, in order to improve the surface processing precision of the turbine engine blade, the surface of the turbine engine blade needs to be polished, but the surface is a distorted variable cross-section curved surface, the shape is complex, and a common polishing device is difficult to polish the distorted variable cross-section curved surface, so that a special grinding wheel operating device for the turbine blade of the aero-engine is needed.
Disclosure of Invention
The invention provides a special grinding wheel running device for an aircraft engine turbine blade, which is based on the technical problems that the surface of the existing turbine engine blade is a distorted variable cross-section curved surface, the shape is complex, and the distorted variable cross-section curved surface is difficult to polish by a common polishing device.
The invention provides a special grinding wheel operating device for turbine blades of an aircraft engine, which comprises a fixed base, wherein the surface of the fixed base is triangular, a controller is fixedly arranged on the surface of the fixed base, a blade moving clamping mechanism is fixedly connected to the upper surface of the fixed base, a blade polishing mechanism is arranged above the blade moving clamping mechanism, and the blade moving clamping mechanism and the blade polishing mechanism are both electrically connected with the controller through electric wires;
the blade moving and clamping mechanism is used for grinding and clamping the turbine blade of the aero-engine;
the blade grinding mechanism is used for grinding turbine blades of the aircraft engine.
Preferably, the blade moving and clamping mechanism comprises a clamping bottom plate, and the surface of the clamping bottom plate is in sliding connection with the upper surface of the fixed base;
the upper surface of the fixed base is fixedly provided with a first limiting driving groove, the first limiting driving groove is uniformly distributed on the lower surface of the clamping bottom plate, the inner wall of the first limiting driving groove is connected with a first limiting driving block in a sliding mode, and the surface of the first limiting driving block is fixedly connected with the lower surface of the clamping bottom plate.
Preferably, the surface of one of the first limit driving blocks is in threaded connection with a first threaded driving rod, and two ends of the first threaded driving rod are rotatably connected with the inner wall of the first limit driving groove through a bearing seat.
Preferably, a first driving motor is fixedly mounted on the surface of the fixed base, and an output shaft of the first driving motor is fixedly connected with one end of a first threaded driving rod through a coupler;
the upper surface sliding connection of centre gripping bottom plate has turbine blade centre gripping frock, the last fixed surface of centre gripping bottom plate has seted up the spacing driving groove of second, and is three the lower surface evenly distributed of the spacing driving groove of second at turbine blade centre gripping frock, the lower fixed surface of turbine blade centre gripping frock is connected with the spacing drive block of second.
Preferably, the three second limit driving blocks correspond to the three second limit driving grooves, and the surfaces of the second limit driving blocks are in sliding connection with the inner walls of the second limit driving grooves;
the surface of one of the second limit driving blocks is in threaded connection with a second threaded driving rod, and two ends of the second threaded driving rod are rotationally connected with the inner wall of a second limit driving groove through a bearing seat;
and a second driving motor is fixedly mounted on the surface of the clamping bottom plate, and an output shaft of the second driving motor is fixedly connected with one end of the second threaded driving rod through a coupler.
Preferably, the blade polishing mechanism comprises fixed stand columns, the surfaces of the fixed stand columns are fixedly connected with the upper surface of the fixed base, and the six fixed stand columns are symmetrically distributed by taking the axis of the fixed base as the center;
six the top of stationary mast is fixedly connected with first fixed mounting panel, second fixed mounting panel and third fixed mounting panel respectively.
Preferably, the surfaces of the first fixed mounting plate, the second fixed mounting plate and the third fixed mounting plate are respectively and fixedly provided with a third driving motor, a fourth driving motor and a fifth driving motor, and output shafts of the third driving motor, the fourth driving motor and the fifth driving motor are respectively and fixedly connected with a third thread driving rod, a fourth thread driving rod and a fifth thread driving rod through couplers.
Preferably, the one end of third screw thread actuating lever, fourth screw thread actuating lever and fifth screw thread actuating lever all is rotated through bearing and unable adjustment base's surface and is connected, the surface of third screw thread actuating lever, fourth screw thread actuating lever and fifth screw thread actuating lever threaded connection respectively has first articulated seat, the articulated seat of second and third articulated seat, the surface of first articulated seat, the articulated seat of second and third articulated seat all cup joints with the surface slip of stationary mast.
Preferably, the surfaces of the first hinge seat, the second hinge seat and the third hinge seat are respectively hinged with a first adjusting connecting rod, a second adjusting connecting rod and a third adjusting connecting rod, and one ends of the first adjusting connecting rod, the second adjusting connecting rod and the third adjusting connecting rod are hinged with a polishing platform;
the polishing device comprises a polishing platform, and is characterized in that a polishing motor is fixedly mounted on the surface of the polishing platform, an output shaft of the polishing motor is fixedly connected with a polishing shaft through a coupler, one end of the polishing shaft penetrates through and extends to the lower surface of the polishing platform, and one end of the polishing shaft is fixedly connected with a polishing grinding wheel.
Preferably, the first driving motor, the second driving motor, the third driving motor, the fourth driving motor, the fifth driving motor and the polishing motor are all electrically connected with the controller through electric wires.
The beneficial effects of the invention are as follows:
1. through setting up blade removal fixture and blade grinding machanism, when using, remove fixture through controller automatic control and drive turbine blade and do horizontal and longitudinal motion on unable adjustment base's surface, cooperation blade grinding machanism carries out the curved surface to turbine blade and polishes to the surface of having solved current turbine engine blade is the variable cross section curved surface of distortion, and the shape is complicated, and ordinary grinding device is difficult to the problem of polishing to the variable cross section curved surface of distortion.
2. Through setting up blade removal fixture, when using, fix the centre gripping through turbine blade centre gripping frock to the turbine blade that needs burnishing and polishing to drive turbine blade centre gripping frock through first driving motor and second driving motor and carry out horizontal and longitudinal motion burnishing and polishing, thereby reach the effect of better automatic burnishing and polishing.
Drawings
FIG. 1 is a schematic view of a grinding wheel operating device specially used for turbine blades of an aircraft engine, which is provided by the invention;
FIG. 2 is a top view of a fixed base structure of a special grinding wheel operating device for an aircraft engine turbine blade, which is provided by the invention;
FIG. 3 is a perspective view of a blade moving clamping mechanism of a grinding wheel operating device specially used for an aircraft engine turbine blade according to the present invention;
FIG. 4 is a structural section view of a clamping base plate of the grinding wheel running device special for the turbine blade of the aircraft engine, which is provided by the invention;
FIG. 5 is a structural front view of a blade grinding mechanism of the grinding wheel operating device special for the turbine blade of the aircraft engine, which is provided by the invention;
fig. 6 is a perspective view of a blade grinding mechanism structure of a grinding wheel operating device special for an aircraft engine turbine blade according to the present invention.
In the figure: 1. a fixed base; 2. a controller; 3. a blade moving and clamping mechanism; 301. clamping the bottom plate; 302. a first limit driving groove; 303. a first limit driving block; 304. a first threaded drive rod; 305. a first drive motor; 306. clamping a turbine blade; 307. a second limit driving groove; 308. a second limit driving block; 309. a second threaded drive rod; 310. a second drive motor; 4. a blade polishing mechanism; 401. fixing the upright post; 402. a first fixed mounting plate; 403. a second fixed mounting plate; 404. a third fixed mounting plate; 405. a third drive motor; 406. a fourth drive motor; 407. a fifth drive motor; 408. a third threaded drive rod; 409. a fourth threaded drive rod; 410. a fifth threaded drive rod; 411. a first hinge mount; 412. a second hinged seat; 413. a third hinge mount; 414. a first adjusting link; 415. a second adjusting link; 416. a third adjusting link; 417. polishing the platform; 418. polishing the motor; 419. grinding the shaft; 420. and (5) polishing the grinding wheel.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
Referring to fig. 1-6, a special grinding wheel operating device for turbine blades of aero-engines comprises a fixed base 1, wherein the surface of the fixed base 1 is triangular, a controller 2 is fixedly mounted on the surface of the fixed base 1, a blade moving clamping mechanism 3 is fixedly connected to the upper surface of the fixed base 1, a blade polishing mechanism 4 is arranged above the blade moving clamping mechanism 3, and the blade moving clamping mechanism 3 and the blade polishing mechanism 4 are both electrically connected with the controller 2 through electric wires.
Wherein, blade removes fixture 3 and is used for polishing the centre gripping to aeroengine turbine blade.
The blade moving clamping mechanism 3 comprises a clamping bottom plate 301, and the surface of the clamping bottom plate 301 is connected with the upper surface of the fixed base 1 in a sliding mode.
In use, the clamp base plate 301 is used to mount a turbine blade clamp fixture 306.
First spacing drive groove 302 has been seted up to unable adjustment base 1's last fixed surface, and three first spacing drive groove 302 is at the lower surface evenly distributed of centre gripping bottom plate 301, and the inner wall sliding connection in first spacing drive groove 302 has first spacing drive block 303, and the surface of first spacing drive block 303 is connected with the lower fixed surface of centre gripping bottom plate 301.
When the floor clamping device is used, the first limit driving groove 302 is matched with the first limit driving block 303, so that the floor clamping device can be limited in stroke and driven to move on the fixed base 1.
The surface of one of the first limit driving blocks 303 is connected with a first screw thread driving rod 304 through a screw thread, and both ends of the first screw thread driving rod 304 are rotatably connected with the inner wall of the first limit driving groove 302 through a bearing seat.
When the clamping device is used, the first limit driving block 303 is driven to move through the first thread driving rod 304, and the clamping bottom plate 301 is driven to move.
The surface of the fixed base 1 is fixedly provided with a first driving motor 305, and an output shaft of the first driving motor 305 is fixedly connected with one end of a first threaded driving rod 304 through a coupler.
In use, the first drive motor 305 features a drive power source for the first threaded drive rod 304.
The upper surface of the clamping base plate 301 is connected with a turbine blade clamping tool 306 in a sliding mode, the upper surface of the clamping base plate 301 is fixedly provided with a second limiting driving groove 307, the three second limiting driving grooves 307 are uniformly distributed on the lower surface of the turbine blade clamping tool 306, and the lower surface of the turbine blade clamping tool 306 is fixedly connected with a second limiting driving block 308.
Further, in the actual use process, the turbine blade clamping tool 306 may adopt a pneumatic clamping tool, an electric clamping tool or a manual clamping tool according to actual conditions.
The three second limit driving blocks 308 correspond to the three second limit driving grooves 307, and the surfaces of the second limit driving blocks 308 are slidably connected with the inner walls of the second limit driving grooves 307.
A second threaded driving rod 309 is connected to the surface of one of the second limit driving blocks 308 in a threaded manner, and two ends of the second threaded driving rod 309 are rotatably connected to the inner wall of the second limit driving groove 307 through bearing seats.
A second driving motor 310 is fixedly mounted on the surface of the clamping base plate 301, and an output shaft of the second driving motor 310 is fixedly connected with one end of a second threaded driving rod 309 through a coupler.
When the grinding machine is used, an output shaft of the first driving motor 305 drives the first threaded driving rod 304 to rotate through the coupler, so that the first limiting driving block 303 is driven to move, the clamping base plate 301 and the turbine blade clamping tool 306 are driven to transversely move, and therefore the turbine blade is driven to transversely move and grind.
When the grinding machine is used, the output shaft of the second driving motor 310 drives the second threaded driving rod 309 to rotate through the coupler, so as to drive the second limiting driving block 308 to move, and drive the turbine blade clamping tool 306 to longitudinally move on the clamping base plate 301, so that the turbine blade is driven to longitudinally move and grind.
Through setting up blade removal fixture 3, when using, fix the centre gripping through turbine blade centre gripping frock 306 to the turbine blade that needs burnishing and polishing to drive turbine blade centre gripping frock 306 through first driving motor 305 and second driving motor 310 and carry out horizontal and longitudinal motion burnishing and polishing, thereby reach the effect of better automatic burnishing and polishing.
Wherein, blade grinding mechanism 4 is used for polishing aeroengine turbine blade.
Blade grinding machanism 4 includes fixed stand 401, and fixed stand 401's surface and unable adjustment base 1's upper surface fixed connection, six fixed stands 401 use unable adjustment base 1's axis to be the symmetric distribution as the center.
The tops of the six fixed columns 401 are fixedly connected with a first fixed mounting plate 402, a second fixed mounting plate 403 and a third fixed mounting plate 404 respectively.
The surfaces of the first fixed mounting plate 402, the second fixed mounting plate 403 and the third fixed mounting plate 404 are respectively fixedly provided with a third driving motor 405, a fourth driving motor 406 and a fifth driving motor 407, and the output shafts of the third driving motor 405, the fourth driving motor 406 and the fifth driving motor 407 are respectively fixedly connected with a third threaded driving rod 408, a fourth threaded driving rod 409 and a fifth threaded driving rod 410 through couplings.
One end of each of the third threaded driving rod 408, the fourth threaded driving rod 409 and the fifth threaded driving rod 410 is rotatably connected with the surface of the fixed base 1 through a bearing, the surfaces of the third threaded driving rod 408, the fourth threaded driving rod 409 and the fifth threaded driving rod 410 are respectively in threaded connection with a first hinging seat 411, a second hinging seat 412 and a third hinging seat 413, and the surfaces of the first hinging seat 411, the second hinging seat 412 and the third hinging seat 413 are respectively in sliding sleeve connection with the surface of the fixed upright column 401.
In use, the third driving motor 405, the fourth driving motor 406 and the fifth driving motor 407 drive the third threaded driving rod 408, the fourth threaded driving rod 409 and the fifth threaded driving rod 410 to rotate, so as to drive the first hinge seat 411, the second hinge seat 412 and the second hinge seat 412 to move up and down on the surface of the fixed upright 401.
The surfaces of the first, second and third hinged seats 411, 412 and 413 are respectively hinged with a first adjusting link 414, a second adjusting link 415 and a third adjusting link 416, and one ends of the first, second and third adjusting links 414, 415 and 416 are hinged with a grinding platform 417.
The surface of the polishing platform 417 is fixedly provided with a polishing motor 418, an output shaft of the polishing motor 418 is fixedly connected with a polishing shaft 419 through a coupler, one end of the polishing shaft 419 penetrates through and extends to the lower surface of the polishing platform 417, and one end of the polishing shaft 419 is fixedly connected with a polishing grinding wheel 420.
The first driving motor 305, the second driving motor 310, the third driving motor 405, the fourth driving motor 406, the fifth driving motor 407 and the polishing motor 418 are electrically connected to the controller 2 through wires.
Through setting up blade removal fixture 3 and blade grinding machanism 4, when using, remove fixture through 2 automatic control of controller and drive turbine blade and do horizontal and longitudinal motion on unable adjustment base 1's surface, cooperation blade grinding machanism 4 carries out the curved surface to turbine blade and polishes to the surface of having solved current turbine engine blade is the variable cross section curved surface of distortion, and the shape is complicated, and ordinary grinding device is difficult to carry out the problem of polishing to the variable cross section curved surface of distortion.
The working principle is as follows: when the turbine blade clamping tool is used, the controller 2 is programmed in advance according to the turbine blade needing to be ground and polished, and then the turbine blade needing to be ground and polished through the grinding wheel is clamped on the turbine blade clamping tool 306.
After the turbine blade to be ground and polished is clamped on the turbine blade clamping tool 306, the controller 2 automatically controls the first driving motor 305, the second driving motor 310, the third driving motor 405, the fourth driving motor 406, the fifth driving motor 407 and the grinding motor 418 to work, and the surface of the turbine blade is ground and polished.
In the grinding and polishing process, the controller 2 automatically controls the first driving motor 305 to rotate to drive the first driving threaded rod to rotate, the first driving threaded rod drives the first limiting driving block 303 to move to drive the clamping bottom plate 301, the turbine blade clamping tool 306, the second driving motor 310 and the turbine blade to move transversely, and the grinding motor 418 is matched to drive the grinding shaft 419 to rotate to drive the grinding wheel 420 to rotate so as to grind and polish the surface of the turbine blade;
meanwhile, according to the actual size and model of the turbine blade, the controller 2 automatically controls the second driving motor 310 to work, an output shaft of the second driving motor 310 drives the second threaded driving rod 309 to rotate through a coupler, drives the second limiting driving block 308 to move, drives the turbine blade clamping tool 306 to move longitudinally, and drives the grinding shaft 419 to rotate by matching with the grinding motor 418, so as to drive the grinding wheel 420 to rotate, and grind and polish the surface of the turbine blade;
meanwhile, as the surface of the turbine blade has a certain radian, in the grinding process, the controller 2 is programmed in advance according to the radian of the turbine blade, and in the grinding and polishing process, the controller 2 automatically controls one or two of the third driving motor 405, the fourth driving motor 406 and the fifth driving motor 407 to work to drive one or two of the third threaded driving rod 408, the fourth threaded driving rod 409 and the fifth threaded driving rod 410 to rotate, drive one or two of the first hinged seat 411, the second hinged seat 412 and the third hinged seat 413 to move upwards or downwards simultaneously, drive one or two of the first adjusting connecting rod 414, the second adjusting connecting rod 415 and the third adjusting connecting rod 416 to move upwards or downwards simultaneously, drive the grinding platform 417 and the grinding motor 418 to move in an arc shape, and drive the grinding wheel 420 to perform arc-shaped motion to grind and polish the surface of the turbine blade.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered as the technical solutions and the inventive concepts of the present invention within the technical scope of the present invention.

Claims (10)

1. The utility model provides a special emery wheel running device of aeroengine turbine blade, includes unable adjustment base (1), its characterized in that: the surface of the fixed base (1) is triangular, the controller (2) is fixedly mounted on the surface of the fixed base (1), the upper surface of the fixed base (1) is fixedly connected with a blade moving clamping mechanism (3), a blade polishing mechanism (4) is arranged above the blade moving clamping mechanism (3), and the blade moving clamping mechanism (3) and the blade polishing mechanism (4) are both electrically connected with the controller (2) through electric wires;
the blade moving and clamping mechanism (3) is used for grinding and clamping the turbine blade of the aircraft engine;
the blade grinding mechanism (4) is used for grinding turbine blades of the aircraft engine.
2. The aircraft engine turbine blade special grinding wheel operating device according to claim 1, characterized in that: the blade moving clamping mechanism (3) comprises a clamping bottom plate (301), and the surface of the clamping bottom plate (301) is connected with the upper surface of the fixed base (1) in a sliding manner;
first spacing drive groove (302), three have been seted up to the last fixed surface of unable adjustment base (1) first spacing drive groove (302) is at the lower surface evenly distributed of centre gripping bottom plate (301), the inner wall sliding connection in first spacing drive groove (302) has first spacing drive block (303), the surface of first spacing drive block (303) is connected with the lower fixed surface of centre gripping bottom plate (301).
3. The grinding wheel operating device special for the turbine blade of the aircraft engine as claimed in claim 2, characterized in that: the surface of one of the first limit driving block (303) is in threaded connection with a first threaded driving rod (304), and two ends of the first threaded driving rod (304) are rotatably connected with the inner wall of the first limit driving groove (302) through bearing seats.
4. The grinding wheel operating device special for the turbine blade of the aircraft engine as claimed in claim 3, wherein: a first driving motor (305) is fixedly mounted on the surface of the fixed base (1), and an output shaft of the first driving motor (305) is fixedly connected with one end of a first threaded driving rod (304) through a coupler;
the upper surface sliding connection of centre gripping bottom plate (301) has turbine blade centre gripping frock (306), the fixed surface of centre gripping bottom plate (301) has seted up second spacing drive groove (307), and is three second spacing drive groove (307) are at the lower surface evenly distributed of turbine blade centre gripping frock (306), the lower surface fixedly connected with second spacing drive block (308) of turbine blade centre gripping frock (306).
5. The special grinding wheel operating device for the turbine blade of the aircraft engine as claimed in claim 4, characterized in that: the three second limit driving blocks (308) correspond to the three second limit driving grooves (307), and the surfaces of the second limit driving blocks (308) are in sliding connection with the inner walls of the second limit driving grooves (307);
a second threaded driving rod (309) is connected to the surface of one second limiting driving block (308) in a threaded manner, and two ends of the second threaded driving rod (309) are rotatably connected with the inner wall of a second limiting driving groove (307) through a bearing seat;
and a second driving motor (310) is fixedly mounted on the surface of the clamping base plate (301), and an output shaft of the second driving motor (310) is fixedly connected with one end of a second threaded driving rod (309) through a coupler.
6. The grinding wheel operating device special for the turbine blade of the aircraft engine as claimed in claim 5, wherein: the blade grinding mechanism (4) comprises fixed upright columns (401), the surfaces of the fixed upright columns (401) are fixedly connected with the upper surface of the fixed base (1), and the six fixed upright columns (401) are symmetrically distributed by taking the axis of the fixed base (1) as the center;
the tops of the six fixed columns (401) are fixedly connected with a first fixed mounting plate (402), a second fixed mounting plate (403) and a third fixed mounting plate (404) respectively.
7. The grinding wheel operating device special for the turbine blade of the aircraft engine as claimed in claim 6, wherein: the surface of first fixed mounting panel (402), second fixed mounting panel (403) and third fixed mounting panel (404) is fixed mounting respectively has third driving motor (405), fourth driving motor (406) and fifth driving motor (407), the output shaft of third driving motor (405), fourth driving motor (406) and fifth driving motor (407) passes through shaft coupling difference fixedly connected with third screw thread actuating lever (408), fourth screw thread actuating lever (409) and fifth screw thread actuating lever (410).
8. The grinding wheel operating device special for the turbine blade of the aircraft engine as claimed in claim 7, wherein: the one end of third screw thread actuating lever (408), fourth screw thread actuating lever (409) and fifth screw thread actuating lever (410) all rotates through the surface of bearing with unable adjustment base (1) to be connected, the surface difference threaded connection of third screw thread actuating lever (408), fourth screw thread actuating lever (409) and fifth screw thread actuating lever (410) has first articulated seat (411), the articulated seat of second (412) and third articulated seat (413), the surface of first articulated seat (411), the articulated seat of second (412) and third articulated seat (413) all cup joints with the surface sliding of stationary mast (401).
9. The grinding wheel operating device special for the turbine blade of the aircraft engine as claimed in claim 8, wherein: the surfaces of the first hinging seat (411), the second hinging seat (412) and the third hinging seat (413) are respectively hinged with a first adjusting connecting rod (414), a second adjusting connecting rod (415) and a third adjusting connecting rod (416), and one ends of the first adjusting connecting rod (414), the second adjusting connecting rod (415) and the third adjusting connecting rod (416) are hinged with a grinding platform (417);
the utility model discloses a grinding machine, including platform (417) of polishing, the fixed surface of platform (417) of polishing installs motor (418), the output shaft of motor (418) of polishing passes through shaft coupling fixedly connected with polishing axle (419), the lower surface of platform (417) of polishing is run through and is extended to the one end of polishing axle (419), the one end fixedly connected with grinding wheel (420) of polishing axle (419).
10. The grinding wheel operating device special for the turbine blade of the aircraft engine as claimed in claim 9, wherein: the first driving motor (305), the second driving motor (310), the third driving motor (405), the fourth driving motor (406), the fifth driving motor (407) and the grinding motor (418) are all electrically connected with the controller (2) through electric wires.
CN202211227749.0A 2022-10-09 2022-10-09 Grinding wheel operating device special for turbine blade of aircraft engine Withdrawn CN115502839A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211227749.0A CN115502839A (en) 2022-10-09 2022-10-09 Grinding wheel operating device special for turbine blade of aircraft engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211227749.0A CN115502839A (en) 2022-10-09 2022-10-09 Grinding wheel operating device special for turbine blade of aircraft engine

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CN115502839A true CN115502839A (en) 2022-12-23

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CN202211227749.0A Withdrawn CN115502839A (en) 2022-10-09 2022-10-09 Grinding wheel operating device special for turbine blade of aircraft engine

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