CN110961722A - Manufacturing method of mortise of turbine disc of aero-engine - Google Patents
Manufacturing method of mortise of turbine disc of aero-engine Download PDFInfo
- Publication number
- CN110961722A CN110961722A CN201911148005.8A CN201911148005A CN110961722A CN 110961722 A CN110961722 A CN 110961722A CN 201911148005 A CN201911148005 A CN 201911148005A CN 110961722 A CN110961722 A CN 110961722A
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- CN
- China
- Prior art keywords
- broaching
- cutter
- disc
- relieving device
- mortise
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23D—PLANING; SLOTTING; SHEARING; BROACHING; SAWING; FILING; SCRAPING; LIKE OPERATIONS FOR WORKING METAL BY REMOVING MATERIAL, NOT OTHERWISE PROVIDED FOR
- B23D41/00—Broaching machines or broaching devices characterised only by constructional features of particular parts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/155—Arrangements for automatic insertion or removal of tools, e.g. combined with manual handling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Jigs For Machine Tools (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a manufacturing method of a mortise of a turbine disc of an aero-engine, which specifically comprises the following steps: (1) disassembling the front end of the inner hole broaching machine, and removing the inner hole broaching device; (2) placing the knife box supporting plate in the hole of the bed head and fixing the knife box supporting plate by using a bolt; (3) installing a cutter relieving device on the front surface of the front panel of the machine tool at the upper part of the cutter box supporting plate, installing an upper limit and a lower limit, and placing the cutter box on the cutter box supporting plate for sliding connection; (4) installing a hydraulic cylinder body and a hydraulic station; (5) mounting the turbine disc clamp on a cutter relieving device; (6) the cutter relieving device is put down, and the broaching feed turbine disc is broached; and lifting the cutter relieving device, recovering the broaching feed to the initial position, repositioning and clamping the broaching part of the turbine disc after the turbine disc is indexed, putting down the cutter relieving device for broaching, and repeating the steps until all broaching is finished. The invention can improve the working efficiency and reduce the working strength of workers.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to a manufacturing method of a mortise of a turbine disc of an aero-engine.
Background
At present, aeroengine turbine disc tongue-and-groove manufacture equipment is single-tool manual tool changing, a broaching turbine disc process is completed by 4 times of continuous operation of workers, the manual tool changing is high in working strength and low in efficiency, and the side-lying broaching machine is high in purchasing cost compared with an inner hole broaching machine. Therefore, a need exists for a method of manufacturing a mortise for a turbine disk of an aircraft engine to solve the above problems.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the manufacturing method of the turbine disc mortise of the aero-engine, which can improve the working efficiency and reduce the working strength of workers by modifying an inner hole broaching machine.
A manufacturing method of a mortise of a turbine disc of an aircraft engine specifically comprises the following steps:
the method comprises the following steps: disassembling the front end of the inner hole broaching machine, and removing the inner hole broaching device;
step two: placing the knife box supporting plate in the hole of the bed head and fixing the knife box supporting plate by using a bolt;
step three: installing a cutter relieving device on the front surface of the front panel of the machine tool at the upper part of the cutter box supporting plate, installing an upper limit and a lower limit, and placing the cutter box on the cutter box supporting plate for sliding connection;
step four: installing a hydraulic cylinder body and a hydraulic station, and installing the hydraulic cylinder body on the upper part of a front panel of a machine tool;
step five: mounting the turbine disc clamp on a cutter relieving device;
step six: and (3) putting down the cutter relieving device and positioning the cutter relieving device at a lower limit position, broaching the broaching cutter feeding turbine disc, lifting the cutter relieving device after the broaches completely leave the disc body, retracting the broaches to recover to an initial position, repositioning and clamping the broaching part of the turbine disc after the turbine disc is indexed, putting down the cutter relieving device to the lower limit position for broaching, and repeating the steps until all broaching is finished.
The knife box supporting plate comprises a base and an upper cover, the base is connected with the upper cover through screws and pins, a rectangular groove track is formed in the base, a lower base plate is arranged on the bottom surface inside the groove, a base plate is arranged on the inner wall surface of the groove, and a left pressing plate and a right pressing plate are arranged on the base.
The hydraulic cylinder body is arranged on the upper portion of a front panel of the machine tool through a cylinder support and connected with the cutter relieving device, and the cylinder support is used for positioning and supporting the hydraulic cylinder body and providing downward pressure, so that stability in the broaching process is guaranteed.
The cutter box comprises a body seat and a handle seat, one end of the body seat is connected with the handle seat through a pin, the body seat is provided with a square groove, and a cutter is arranged in the square groove and is pressed tightly by a pressing block; the side surface of the other end of the body seat is connected with a stop iron, and the top end of the body seat is connected with a hanging ring.
The cutter relieving device comprises a base plate and a sliding plate, the base plate is arranged on the front face of a front panel of the machine tool, a sliding groove is formed in the base plate, the sliding plate is driven by a hydraulic cylinder to slide up and down in the sliding groove of the base plate, and a wedge iron is arranged between the base plate and the sliding plate and used for adjusting a gap.
The turbine disc clamp comprises a clamp body seat, a disc and a positioning ring, the clamp body seat is connected with the cutter relieving device, the mandrel penetrates through the disc to be connected to the front end face of the clamp body seat, the disc can rotate around the mandrel, the positioning ring is connected to the surface of the disc through a screw, and the turbine disc is installed on the surface of the positioning ring and fixed through a pressing plate.
The outer circle of the disc is uniformly provided with positioning holes along the circumferential direction, and is provided with a handle and a positioning pin for indexing positioning.
The lower limit is a positioning block on the front surface of the front panel of the machine tool, and the upper limit is a hydraulic cylinder body.
The invention has the beneficial effects that: the invention can use a simple equipment inner hole broaching machine, and is provided with the corresponding cutter relieving device and the corresponding cutter box, so that the side-lying broaching machine has the processing capacity of the side-lying broaching machine, the original inner hole broaching machine is directly transformed, the equipment investment cost is low, the cost investment is controlled, meanwhile, the hydraulic cylinder body is arranged, the hydraulic cylinder body can be driven by the hydraulic station to realize the lifting and descending of the cutter relieving device, the manual cutter feeding is replaced, the processing efficiency is improved, the working intensity of workers is reduced, and the whole process is safe and efficient. The invention can process complex turbine disc mortises, has high precision and good durability, and can be widely applied to the processing of small turbine disc mortises.
Drawings
FIG. 1 is a schematic view of a blade case pallet of the present invention;
FIG. 2 is a view taken along line B-B of FIG. 1;
FIG. 3 is a view taken along line A-A of FIG. 1;
FIG. 4 is a schematic view of a knife cassette of the present invention;
FIG. 5 is a top view of FIG. 4;
FIG. 6 is a view from the B-B direction of FIG. 4;
FIG. 7 is a view taken along line A-A of FIG. 4;
FIG. 8 is a schematic view of a back-off device according to the present invention;
FIG. 9 is a top view of FIG. 8;
FIG. 10 is a schematic view of a turbine disk clamp of the present invention;
FIG. 11 is a view from the A-A direction of FIG. 10;
FIG. 12 is a view taken along line K of FIG. 10;
FIG. 13 is a view from the C-C direction of FIG. 12;
FIG. 14 is a schematic view of a locating block of the present invention;
FIG. 15 is a schematic view of the connection of the blade cartridge carrier, the blade cartridge, the back-off device, and the turbine disk clamp of the present invention;
FIG. 16 is a top view of FIG. 15;
wherein the content of the first and second substances,
the device comprises a base 1, an upper cover 2, a backing plate 3, a lower backing plate 4, a left pressing plate 5, a right pressing plate 6, a screw 7, a pin 8, a handle seat 9, a body seat 10, a lifting ring 11, a pressing block 12, a stop iron 13, a base plate 14, a sliding plate 15, a round pin 16, a cylindrical pin 17, a wedge iron 18, a diamond pin 19, a clamp body seat 20, a disc 21, a bush 22, a bolt 23, a pressing plate 24, a positioning ring 25, a handle 26, a spring 27, a cushion block 28, a guide sleeve 29, a positioning pin 30, a positioning pin bush 31, a mandrel 32, a base block 33 and a cylinder support 34.
Detailed Description
For better understanding of the present invention, the technical solutions and effects of the present invention will be described in detail by the following embodiments with reference to the accompanying drawings.
A manufacturing method of a mortise of a turbine disc of an aircraft engine specifically comprises the following steps:
the method comprises the following steps: disassembling the front end of the inner hole broaching machine, and removing the inner hole broaching device;
step two: placing the knife box supporting plate in the hole of the bed head and fixing the knife box supporting plate by using a bolt; as shown in fig. 1-3, the knife box supporting plate comprises a base 1 and an upper cover 2, the base 1 is connected with the upper cover 2 through a screw 7 and a pin 8, a rectangular groove track is formed on the base 1, a lower backing plate 4 is arranged on the bottom surface inside the groove, a backing plate 3 is arranged on the inner wall surface of the groove, and a left pressing plate 5 and a right pressing plate 6 are arranged on the base 1.
Step three: the cutter relieving device is arranged on the front surface of the front panel of the machine tool on the upper part of the supporting plate of the cutter box, and the upper limit and the lower limit are arranged, as shown in figures 8-9, the cutter relieving device comprises a base plate 14 and a sliding plate 15, the base plate 14 is arranged on the front surface of the front panel of the machine tool through a round pin 16 and a diamond pin 19, a sliding groove is formed in the base plate 14, the sliding plate 15 is connected with a hydraulic cylinder body, the hydraulic cylinder body drives the sliding plate 15 to slide up and down in the sliding groove of the base plate 14, and a wedge 18 is arranged between the. The lower limit is a positioning block on the front surface of the front panel of the machine tool, and as shown in fig. 14, the lower limit comprises a base block 33 which is connected to the front surface of the front panel of the machine tool by a bolt 23, and the two positioning blocks are arranged at two ends of the front panel of the machine tool, are used for limiting the limit position of the downward movement of the hydraulic cylinder and are used as the broaching position, so that the cutter relieving device can be broached to form a mortise when being positioned at the lower limit;
placing a knife box on a knife box supporting plate to be in sliding connection, wherein the knife box comprises a body seat 10 and a handle seat 9, one end of the body seat 10 is connected with the handle seat 9 through a pin 8, the body seat 10 is provided with a square groove, a knife is arranged in the square groove and is pressed by a pressing block 12, and the pressing block 12 is connected with the body seat 10 through a screw 7; the other end side of the body seat 10 is connected with a stop iron 13 through a screw 7, and the top end of the body seat 10 is connected with a hanging ring 11.
Step four: installing a hydraulic cylinder body and a hydraulic station (not shown in the figure), and installing the hydraulic cylinder body on the upper part of the front panel of the machine tool, wherein the hydraulic cylinder is an upper limit; the hydraulic cylinder body is arranged on the upper portion of a front panel of the machine tool through a cylinder support 34 and connected with a cutter relieving device, and the cylinder support 34 positions and supports the hydraulic cylinder body and provides downward pressure to guarantee stability in the broaching process.
Step five: mounting the turbine disc clamp on a cutter relieving device; as shown in fig. 10-13, the turbine disc clamp comprises a clamp body seat 20, a disc 21 and a positioning ring 25, wherein a through hole is formed in the clamp body seat 20 and connected with a cutter relieving device through a cylindrical pin 17, a bushing 22 is arranged in the through hole, a mandrel 32 penetrates through the disc 21 and is connected to the front end face of the clamp body seat 20, the disc 21 can rotate around the mandrel 32, the positioning ring 25 is connected to the surface of the disc 21 through a screw 7, the turbine disc is installed on the surface of the positioning ring 25 and is fixed through a pressing plate 24, a through hole is formed in the pressing plate 24, a bolt 23 penetrates through the through hole and is connected to the disc 21 and is locked through a. Positioning holes are uniformly distributed on the outer circle of the disc 21 along the circumferential direction, a handle 26 is arranged for indexing positioning, a positioning pin 30 is connected to the lower end of the handle 26, a cushion block 28 is connected to the outer circle of the clamp body seat 20 through a screw 7, a guide sleeve 29 is connected to the shaft shoulder of the cushion block 28, a spring 27 is arranged in the guide sleeve 29, the positioning pin 30 penetrates through the spring 27 and is inserted into the positioning hole of the disc 21 to index and position the turbine disc, and a positioning pin bushing 31 is arranged in the positioning hole of the. The knife box supporting plate, the knife box, the cutter relieving device and the turbine disc clamp are connected as shown in figures 15-16.
Step six: and (3) putting down the cutter relieving device and positioning the cutter relieving device at a lower limit position, broaching the broaching cutter feeding turbine disc, lifting the cutter relieving device after the broaches completely leave the disc body, retracting the broaches to recover to an initial position, repositioning and clamping the broaching part of the turbine disc after the turbine disc is indexed, putting down the cutter relieving device to the lower limit position for broaching, and repeating the steps until all broaching is finished.
Claims (8)
1. A manufacturing method of a mortise of a turbine disc of an aircraft engine is characterized by comprising the following steps: the method specifically comprises the following steps:
the method comprises the following steps: disassembling the front end of the inner hole broaching machine, and removing the inner hole broaching device;
step two: placing the knife box supporting plate in the hole of the bed head and fixing the knife box supporting plate by using a bolt;
step three: installing a cutter relieving device on the front surface of the front panel of the machine tool at the upper part of the cutter box supporting plate, installing an upper limit and a lower limit, and placing the cutter box on the cutter box supporting plate for sliding connection;
step four: installing a hydraulic cylinder body and a hydraulic station, and installing the hydraulic cylinder body on the upper part of a front panel of a machine tool;
step five: mounting the turbine disc clamp on a cutter relieving device;
step six: and (3) putting down the cutter relieving device and positioning the cutter relieving device at a lower limit position, broaching the broaching cutter feeding turbine disc, lifting the cutter relieving device after the broaches completely leave the disc body, retracting the broaches to recover to an initial position, repositioning and clamping the broaching part of the turbine disc after the turbine disc is indexed, putting down the cutter relieving device to the lower limit position for broaching, and repeating the steps until all broaching is finished.
2. A method for manufacturing a mortise of a turbine disk of an aircraft engine according to claim 1, wherein: the knife box supporting plate comprises a base and an upper cover, the base is connected with the upper cover through screws and pins, a rectangular groove track is formed in the base, a lower base plate is arranged on the bottom surface inside the groove, a base plate is arranged on the inner wall surface of the groove, and a left pressing plate and a right pressing plate are arranged on the base.
3. A method for manufacturing a mortise of a turbine disk of an aircraft engine according to claim 1, wherein: the hydraulic cylinder body is arranged on the upper portion of a front panel of the machine tool through a cylinder support and connected with the cutter relieving device, and the cylinder support is used for positioning and supporting the hydraulic cylinder body and providing downward pressure, so that stability in the broaching process is guaranteed.
4. A method for manufacturing a mortise of a turbine disk of an aircraft engine according to claim 1, wherein: the cutter box comprises a body seat and a handle seat, one end of the body seat is connected with the handle seat through a pin, the body seat is provided with a square groove, and a cutter is arranged in the square groove and is pressed tightly by a pressing block; the side surface of the other end of the body seat is connected with a stop iron, and the top end of the body seat is connected with a hanging ring.
5. A method for manufacturing a mortise of a turbine disk of an aircraft engine according to claim 1, wherein: the cutter relieving device comprises a base plate and a sliding plate, the base plate is arranged on the front face of a front panel of the machine tool, a sliding groove is formed in the base plate, the sliding plate is driven by a hydraulic cylinder to slide up and down in the sliding groove of the base plate, and a wedge iron is arranged between the base plate and the sliding plate and used for adjusting a gap.
6. A method for manufacturing a mortise of a turbine disk of an aircraft engine according to claim 1, wherein: the turbine disc clamp comprises a clamp body seat, a disc and a positioning ring, the clamp body seat is connected with the cutter relieving device, the mandrel penetrates through the disc to be connected to the front end face of the clamp body seat, the disc can rotate around the mandrel, the positioning ring is connected to the surface of the disc through a screw, and the turbine disc is installed on the surface of the positioning ring and fixed through a pressing plate.
7. A method for manufacturing a mortise of a turbine disk of an aircraft engine according to claim 6, wherein: the outer circle of the disc is uniformly provided with positioning holes along the circumferential direction, and is provided with a handle and a positioning pin for indexing positioning.
8. A method for manufacturing a mortise of a turbine disk of an aircraft engine according to claim 1, wherein: the lower limit is a positioning block on the front surface of the front panel of the machine tool, and the upper limit is a hydraulic cylinder body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911148005.8A CN110961722A (en) | 2019-11-21 | 2019-11-21 | Manufacturing method of mortise of turbine disc of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911148005.8A CN110961722A (en) | 2019-11-21 | 2019-11-21 | Manufacturing method of mortise of turbine disc of aero-engine |
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| Publication Number | Publication Date |
|---|---|
| CN110961722A true CN110961722A (en) | 2020-04-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911148005.8A Pending CN110961722A (en) | 2019-11-21 | 2019-11-21 | Manufacturing method of mortise of turbine disc of aero-engine |
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| CN (1) | CN110961722A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111702610A (en) * | 2020-07-07 | 2020-09-25 | 中国航发动力股份有限公司 | Engine wheel disc annular row special-shaped tongue-and-groove sharp edge treatment method |
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|---|---|---|---|---|
| DE19715771C1 (en) * | 1997-04-16 | 1998-11-12 | Hoffmann Kurt Gmbh & Co Kg | Machine tool for steam- or gas-turbine rotor discs |
| CN101664883A (en) * | 2009-08-28 | 2010-03-10 | 沈阳黎明航空发动机(集团)有限责任公司 | Fixture special for mortise of broaching disc type part |
| US7827661B2 (en) * | 2008-08-06 | 2010-11-09 | United Technologies Corporation | Control of white-etched layer during machining |
| CN105689789A (en) * | 2014-11-28 | 2016-06-22 | 中国石油天然气集团公司 | Wheel disc broaching device |
| CN205927330U (en) * | 2016-08-26 | 2017-02-08 | 中航动力股份有限公司 | Broaching rim plate takes out device that is pressed from both sides broach |
| CN107962262A (en) * | 2017-12-01 | 2018-04-27 | 中国航发沈阳黎明航空发动机有限责任公司 | The electrode and processing unit (plant) and method of turbine disc mortise electrolysis cutting rapid shaping |
| CN108555387A (en) * | 2018-06-25 | 2018-09-21 | 浙江畅尔智能装备股份有限公司 | A kind of automatic handling device and control method for turbine disc mortise broaching |
| CN109434188A (en) * | 2018-12-29 | 2019-03-08 | 浙江畅尔智能装备股份有限公司 | A kind of workbench for broaching lathe |
-
2019
- 2019-11-21 CN CN201911148005.8A patent/CN110961722A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19715771C1 (en) * | 1997-04-16 | 1998-11-12 | Hoffmann Kurt Gmbh & Co Kg | Machine tool for steam- or gas-turbine rotor discs |
| US7827661B2 (en) * | 2008-08-06 | 2010-11-09 | United Technologies Corporation | Control of white-etched layer during machining |
| CN101664883A (en) * | 2009-08-28 | 2010-03-10 | 沈阳黎明航空发动机(集团)有限责任公司 | Fixture special for mortise of broaching disc type part |
| CN105689789A (en) * | 2014-11-28 | 2016-06-22 | 中国石油天然气集团公司 | Wheel disc broaching device |
| CN205927330U (en) * | 2016-08-26 | 2017-02-08 | 中航动力股份有限公司 | Broaching rim plate takes out device that is pressed from both sides broach |
| CN107962262A (en) * | 2017-12-01 | 2018-04-27 | 中国航发沈阳黎明航空发动机有限责任公司 | The electrode and processing unit (plant) and method of turbine disc mortise electrolysis cutting rapid shaping |
| CN108555387A (en) * | 2018-06-25 | 2018-09-21 | 浙江畅尔智能装备股份有限公司 | A kind of automatic handling device and control method for turbine disc mortise broaching |
| CN109434188A (en) * | 2018-12-29 | 2019-03-08 | 浙江畅尔智能装备股份有限公司 | A kind of workbench for broaching lathe |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111702610A (en) * | 2020-07-07 | 2020-09-25 | 中国航发动力股份有限公司 | Engine wheel disc annular row special-shaped tongue-and-groove sharp edge treatment method |
| CN111702610B (en) * | 2020-07-07 | 2021-05-25 | 中国航发动力股份有限公司 | Engine wheel disc annular row special-shaped tongue-and-groove sharp edge treatment method |
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Application publication date: 20200407 |
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