CN113681466A - Novel integrated machining clamp for turbine blade of aero-engine and machining process of novel integrated machining clamp - Google Patents
Novel integrated machining clamp for turbine blade of aero-engine and machining process of novel integrated machining clamp Download PDFInfo
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- CN113681466A CN113681466A CN202110962257.5A CN202110962257A CN113681466A CN 113681466 A CN113681466 A CN 113681466A CN 202110962257 A CN202110962257 A CN 202110962257A CN 113681466 A CN113681466 A CN 113681466A
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- 238000003754 machining Methods 0.000 title claims abstract description 48
- 238000000227 grinding Methods 0.000 claims abstract description 21
- 230000036339 tooth positioning Effects 0.000 claims abstract description 21
- 238000012545 processing Methods 0.000 claims abstract description 13
- 239000000463 material Substances 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 10
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000013461 design Methods 0.000 abstract description 3
- 238000003825 pressing Methods 0.000 description 4
- 238000011161 development Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000002929 anti-fatigue Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 206010016256 fatigue Diseases 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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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
- B24B41/00—Component parts such as frames, beds, carriages, headstocks
- B24B41/06—Work supports, e.g. adjustable steadies
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The invention discloses a novel integrated machining clamp for an aircraft engine turbine blade and a machining process of the novel integrated machining clamp, wherein the novel integrated machining clamp comprises a base, a support arranged on the base, and a chuck assembly and an end face positioning assembly which are respectively arranged on the support; the clamping head component comprises a tenon tooth positioning block arranged on the support, a tenon tooth clamping block matched and connected with the tenon tooth positioning block and a locking piece arranged on the tenon tooth clamping block, a tenon tooth groove used for clamping the blade is formed between the tenon tooth positioning block and the tenon tooth clamping block, and tooth teeth are arranged on the end face of the tenon tooth positioning block close to the tenon tooth clamping block and on the end face of the tenon tooth clamping block close to the tenon tooth positioning block. The processing fixture is reliable in structure and good in use performance, and the processing and positioning accuracy is improved. And the grinding processing is convenient. The machining process adopts a design principle of process concentration, the machining surfaces with the same positioning mode are concentrated into one procedure for machining, and the machining precision is ensured through the precision of numerical control powerful grinding equipment. Reduce repeated clamping error, reduce frock manufacturing cost.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a novel integrated machining clamp for an aero-engine turbine blade and a machining process of the novel integrated machining clamp.
Background
At present, a large number of advanced aero-engines are urgently needed in China, and high performance, high reliability and long service life are required. The turbine working blade is used as a key part in an aircraft engine, works in a high-temperature and high-pressure severe environment, is impacted by high-temperature gas, and simultaneously does high-speed rotation motion around a turbine shaft to bear huge centrifugal force, alternating stress and thermal stress load, and needs high reliability and anti-fatigue capability.
The turbine working blade has a complex structure: the tenon adopts fir type tenon tooth, and some blade apex designs have the blade shroud, have the tooth that obturages on the blade shroud. The blade body is a space curved surface, the interior of the blade body is provided with a cooling channel, the blade body is provided with various air film holes and exhaust holes, and the surface of the blade body is provided with a heat insulation coating or a seepage layer. Due to its harsh operating conditions, the risk of fatigue failure is high, and the dimensional accuracy requirements are very high, for example: the tolerance of the profile tolerance of the tenon tooth is generally 0.01 mm-0.02 mm.
The traditional turbine working blade processing adopts a process scheme with dispersed working procedures, various special tools need to be manufactured, clamping is carried out for many times, processing tasks of all parts are respectively completed on different equipment, and the process preparation and the production and manufacturing period are longer. Under the new trend of current high-density model development, the requirement of fast and efficient model development can not be met, and a large amount of tool waste is caused. Meanwhile, due to the long process route and the accumulation of multi-process multi-factor errors, the processing precision of products is reduced, and the pre-ground model verification is influenced.
Disclosure of Invention
In order to solve the technical problems, the invention provides a novel integrated machining clamp for an aero-engine turbine blade and a machining process thereof.
The technical scheme for solving the technical problems is as follows: a novel integrated machining clamp for an aircraft engine turbine blade comprises a base, a support arranged on the base, and a chuck assembly and an end face positioning assembly which are respectively arranged on the support;
the clamping head component comprises a tenon tooth positioning block arranged on the support, a tenon tooth clamping block matched and connected with the tenon tooth positioning block and a locking piece arranged on the tenon tooth clamping block, a tenon tooth groove used for clamping the blade is formed between the tenon tooth positioning block and the tenon tooth clamping block, and the tenon tooth positioning block is close to the end face of the tenon tooth clamping block and the end face of the tenon tooth clamping block close to the tenon tooth positioning block are both provided with teeth.
Furthermore, the end face positioning component comprises an end face supporting block arranged on the support and a positioning column arranged on the end face supporting block, and the positioning column faces the tenon tooth groove and corresponds to the tenon tooth groove.
Furthermore, the tenon tooth locating piece is including setting up the location supporting seat on the support and setting up the location head on the location supporting seat, and tooth setting is at location head lateral wall.
Furthermore, the tenon tooth clamping block comprises a clamping support seat arranged on the base and a clamping head arranged on the clamping support seat, a gap is formed between the clamping support seat and the positioning support seat, and a tenon tooth groove is formed between the positioning head and the clamping head.
Furthermore, the locking part adopts a stud, a threaded hole matched with the stud is formed in the positioning supporting seat, and the stud is screwed in to drive the clamping supporting seat and the clamping head to clamp.
Furthermore, the support is including setting up first plate body on the base, the second plate body of being connected perpendicularly with first plate body and setting are at first plate body with strengthening rib between the second plate body, first plate body and second plate body are connected and are L type structure, and cartridge assembly and terminal surface locating component set up respectively on the second plate body.
The invention also provides a novel integrated machining process for the turbine blade of the aero-engine, which comprises the following steps:
s1: fixing a processing clamp on a machine tool workbench, then fixing the rough material on the processing clamp,
s2: positioning by using a 6-point reference of the blank, and grinding the tenon tooth and the exhaust end face;
s3: and after the tenon tooth and the exhaust end face are ground, grinding the radial face of the tenon basin, the radial face of the tenon back, the air inlet end face of the tenon and the surface of the blade tip by taking the tenon tooth and the exhaust end face as positioning references.
Further, in the step S2, the 6 datum locations include two points B1 and B2 and a point B3 of the blade tip profile back as a first datum, a point a2 of the dovetail air inlet end face and a point a1 of the blade tip profile air inlet edge as a second datum, and a point F6 on the flow channel of the dovetail flange plate as a third datum.
Further, the machining grinding in step S3 includes the following steps:
s3.1: rotating the C shaft of the workbench to enable the air inlet end face to be horizontally placed upwards, and then grinding the air inlet end face;
s3.2: then, rotating the C shaft of the workbench to enable the back radial surface to be horizontally placed upwards, and then grinding the back radial surface;
s3.3: rotating the C shaft of the workbench by 180 degrees, then rotating the A shaft to enable the radial surface of the basin to be horizontally placed upwards, and then grinding the radial surface of the basin;
s3.4: the A axis of the workbench rotates, so that the blade tip is horizontally placed upwards, and then the blade tip is ground.
The invention has the following beneficial effects: the novel integrated machining clamp for the turbine blade of the aero-engine and the machining process of the turbine blade of the aero-engine are reliable in structure and good in use performance, the tenon tooth surface and the tenon end face are used as positioning references, the pre-installation gap between the tenon tooth groove and the tenon surface is moderate, the centering performance of the tenon tooth surface is good, the repeated positioning precision is high, and the machining positioning accuracy is improved. In addition, the tenon tooth of tenon tooth locating piece and tenon tooth clamp block sets up to the symmetric distribution, and each machined surface is opened wide nature in the course of working is good, and abrasive machining is convenient. The machining process adopts a design principle of process concentration, the machining surfaces with the same positioning mode are concentrated into one procedure for machining, and the machining precision is ensured through the precision of numerical control powerful grinding equipment. The positioning mode is not completely the same, but the surfaces which can guarantee the size precision through one-time clamping, automatic station changing and continuous processing are combined into the same procedure for carrying out, so that the precision advantage of the equipment is exerted to the maximum extent, the manual operation error is reduced, the repeated clamping error is reduced, and the tool manufacturing cost is reduced.
Drawings
FIG. 1 is a schematic view of a machining jig according to the present invention;
FIG. 2 is a schematic view of a chuck assembly according to the present invention;
FIG. 3 is a schematic structural view of an end face positioning assembly according to the present invention;
FIG. 4 is a schematic view of a tenon tooth positioning block according to the present invention;
FIG. 5 is a schematic view of a tenon tooth clamping block according to the present invention;
FIG. 6 is a schematic view of the stand according to the present invention;
FIG. 7 is a schematic view of the machining fixture of the present invention;
FIG. 8 is a schematic view of a blade datum point distribution according to the present invention.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
As shown in figure 1, the novel integrated machining clamp for the turbine blade of the aircraft engine comprises a base 1, a support 2 arranged on the base 1, and a chuck assembly 3 and an end face positioning assembly 4 which are respectively arranged on the support 2. The base 1 provides reliable support for the whole clamp, and the base 1 is provided with 1 phi 80 positioning hole, 1 phi 8 pin hole, 3M 8 counter bores for screws, 2 phi 6 pin holes and 4M 8 threaded holes; the phi 80 positioning hole is connected with a phi 80 circular table of the machine tool workbench, and the bottom surface of the positioning hole is attached to the end surface of the phi 80 circular table of the machine tool workbench and used for positioning the clamp on the machine tool workbench; the phi 8 pin hole is connected with a phi 8 movable pin of a machine tool workbench on the circular table and used for angular positioning of a clamp, and the screw counter bore is connected with the machine tool workbench through an M8 socket head cap screw. 2 phi 6 pin holes and 4M 8 screw holes are used for connecting the support 2. The support 2 is of an L-shaped structure, 2 phi 6 pin holes and 4 phi 9 through holes for screws are formed in the bottom surface of the support and are connected with the base 1 through the screws and the cylindrical pins; the side surface of the support 2 is provided with 4 phi 6 pin holes and 6M 6 screw holes for connecting the chuck component 3 and the end face supporting component.
As shown in fig. 2, the chuck assembly 3 includes a tenon tooth positioning block 30 disposed on the support 2, a tenon tooth clamping block 31 cooperatively connected with the tenon tooth positioning block 30, and a locking member 32 disposed on the tenon tooth clamping block 31, a tenon tooth groove 33 for clamping the blade is formed between the tenon tooth positioning block 30 and the tenon tooth clamping block 31, and teeth 34 are disposed on an end surface of the tenon tooth positioning block 30 close to the tenon tooth clamping block 31 and an end surface of the tenon tooth clamping block 31 close to the tenon tooth positioning block 30. The locking part 32 adopts a stud, and a threaded hole matched with the stud is arranged on the positioning support seat 301 of the tenon tooth positioning block 30. The tenon tooth clamping block 31 has a groove structure with a thin middle part and thick two ends, and the structure enables the tooth ends to elastically deform when stressed. The stud of the chuck component 3 is fixed on the tenon tooth positioning block 30 through the screw rod at one end, the screw rod at the other end passes through the phi 11 through hole on the tenon tooth clamping block 31 to be connected with the hexagon nut, and the hexagon nut is rotated to drive the tenon tooth clamping block 31 to elastically deform and compress the tenon tooth of the blade during operation, so that the blade is fixed on the clamp.
When the fixture is used, the base 1 of the fixture is fixed on a workbench, and the tenon of the blade penetrates through the tenon tooth groove 33 formed by the tenon tooth positioning block 30 and the tenon tooth clamping block 31; the tenon front edge positioning surface leans against the end surface positioning pin; rotating the hexagon nut on the stud clockwise, driving the tenon tooth pressing block of the chuck component 3 to elastically deform until the tenon tooth pressing block is contacted with and pressed against the tenon tooth profile, and keeping the tenon tooth profile and the tenon tooth groove 33 profile tightly attached; and the hexagon nut is rotated anticlockwise, the pressure applied to the tenon tooth pressing block is released, the elastic deformation of the tenon tooth pressing block disappears, the tenon tooth groove 33 profile is separated from the tenon tooth profile of the blade and is loosened, and the blade can be taken down from the clamp.
As shown in fig. 3, the end face positioning assembly 4 includes an end face support block 40 disposed on the support 2 and a positioning column 41 disposed on the end face support block 40, and the positioning column 41 faces the tenon tooth groove 33 and corresponds to the tenon tooth groove 33. The positioning column 41 is used for limiting the end face of the blade, and the end face supporting block 40 is provided with 2 phi 6 pin holes, 2 phi 7 through holes for screws and 1 phi 6 through hole, and is connected with the support 2 through a phi 6 cylindrical pin and an M6 hexagon socket angle screw; the phi 6 through hole is used for installing the end positioning column 41.
As shown in fig. 4 to 5, the tenon tooth positioning block 30 includes a positioning support base 301 disposed on the support base 2 and a positioning head 302 disposed on the positioning support base 301, and the tooth 34 is disposed on a side wall of the positioning head 302. The tenon tooth clamping block 31 comprises a clamping support seat 340 arranged on the base 1 and a clamping head 341 arranged on the clamping support seat 340, a gap is formed between the clamping support seat 340 and the positioning support seat 301, and a tenon tooth groove 33 is formed between the positioning head 302 and the clamping head 341.
As shown in fig. 6, the support 2 includes a first plate 20 disposed on the base 1, a second plate 21 perpendicularly connected to the first plate 20, and a reinforcing rib 22 disposed between the first plate 20 and the second plate 21, the first plate 20 and the second plate 21 are connected to form an L-shaped structure, and the chuck assembly 3 and the end surface positioning assembly 4 are disposed on the second plate 21, respectively. The reinforcing ribs 22 improve the connection strength of the first plate body 20 and the second plate body 21, and the structural performance is improved.
As shown in fig. 7 to 8, the invention also provides a novel integrated machining process for an aircraft engine turbine blade, which comprises the following steps:
s1: fixing a processing clamp on a machine tool workbench, then fixing the rough material on the processing clamp,
s2: positioning by using a 6-point reference of the blank, and grinding the tenon tooth and the exhaust end face; in the step S2, the 6 datum locations include two points B1 and B2 and a point B3 of the blade tip profile back as a first datum, a point a2 of the dovetail air inlet end face and a point a1 of the blade tip profile air inlet edge as a second datum, and a point F6 on the flow channel of the dovetail edge plate as a third datum.
S3: and after the tenon tooth and the exhaust end face are ground, grinding the radial face of the tenon basin, the radial face of the tenon back, the air inlet end face of the tenon and the surface of the blade tip by taking the tenon tooth and the exhaust end face as positioning references.
The machining and grinding in step S3 includes the steps of:
s3.1: rotating the C shaft of the workbench to enable the air inlet end face to be horizontally placed upwards, and then grinding the air inlet end face;
s3.2: then, rotating the C shaft of the workbench to enable the back radial surface to be horizontally placed upwards, and then grinding the back radial surface;
s3.3: rotating the C shaft of the workbench by 180 degrees, then rotating the A shaft to enable the radial surface of the basin to be horizontally placed upwards, and then grinding the radial surface of the basin;
s3.4: the A axis of the workbench rotates, so that the blade tip is horizontally placed upwards, and then the blade tip is ground.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (9)
1. A novel integrated machining clamp for an aircraft engine turbine blade is characterized by comprising a base (1), a support (2) arranged on the base (1), and a chuck assembly (3) and an end face positioning assembly (4) which are respectively arranged on the support (2);
the clamping head component (3) is including setting up tenon tooth locating piece (30) on support (2), with tenon tooth that tenon tooth locating piece (30) cooperation is connected presss from both sides tight piece (31) and sets up retaining member (32) on the tight piece (31) of tenon tooth clamp, tenon tooth locating piece (30) with the tenon tooth presss from both sides and forms tenon tooth groove (33) that are used for the clamping blade between tight piece (31) of tenon tooth clamp, tenon tooth locating piece (30) are close to the terminal surface that the tenon tooth pressed from both sides tight piece (31) the tenon tooth presss from both sides tight piece (31) and is close to the terminal surface of tenon tooth locating piece (30) all is provided with tooth (34).
2. The novel integrated machining fixture for the turbine blade of the aircraft engine as claimed in claim 1, characterized in that the end face positioning assembly (4) comprises an end face support block (40) arranged on the support (2) and a positioning column (41) arranged on the end face support block (40), and the positioning column (41) faces the mortise slot (33) and corresponds to the mortise slot (33).
3. The novel integrated machining clamp for the turbine blade of the aircraft engine as claimed in claim 1, wherein the tenon tooth positioning block (30) comprises a positioning support seat (301) arranged on the support (2) and a positioning head (302) arranged on the positioning support seat (301), and the tooth (34) is arranged on the side wall of the positioning head (302).
4. The novel integrated machining clamp for the turbine blade of the aero-engine as claimed in claim 3, wherein the tenon tooth clamping block (31) comprises a clamping support seat (340) arranged on the base (1) and a clamping head (341) arranged on the clamping support seat (340), a gap is formed between the clamping support seat (340) and the positioning support seat (301), and a tenon tooth groove (33) is formed between the positioning head (302) and the clamping head (341).
5. The novel integrated machining clamp for the turbine blade of the aero-engine as claimed in claim 4, wherein the locking member (32) is a stud, a threaded hole matched with the stud is formed in the positioning support seat (301), and the clamping support seat (340) and the clamping head (341) are driven to clamp through screwing of the stud.
6. The novel integrated machining clamp for the turbine blade of the aero-engine as claimed in any one of claims 1 to 5, wherein the support (2) comprises a first plate body (20) arranged on the base (1), a second plate body (21) perpendicularly connected with the first plate body (20), and a reinforcing rib (22) arranged between the first plate body (20) and the second plate body (21), the first plate body (20) and the second plate body (21) are connected to form an L-shaped structure, and the chuck assembly (3) and the end face positioning assembly (4) are respectively arranged on the second plate body (21).
7. A novel integrated machining process for an aircraft engine turbine blade, characterized in that the machining fixture of any one of claims 1 to 6 is adopted for machining, and the novel integrated machining process comprises the following steps:
s1: fixing a processing clamp on a machine tool workbench, then fixing the rough material on the processing clamp,
s2: positioning by using a 6-point reference of the blank, and grinding the tenon tooth and the exhaust end face;
s3: and after the tenon tooth and the exhaust end face are ground, grinding the radial face of the tenon basin, the radial face of the tenon back, the air inlet end face of the tenon and the surface of the blade tip by taking the tenon tooth and the exhaust end face as positioning references.
8. The novel integrated machining process for the turbine blade of the aero-engine as claimed in claim 7, wherein in the step S2, the 6 datum locations include two points B1 and B2 and a point B3 of the blade tip profile back as a first datum, a point A2 of the tenon air inlet end face and a point A1 of the blade tip profile air inlet edge as a second datum, and a point F6 on the flow channel of the tenon edge plate as a third datum.
9. The novel integrated machining process for the turbine blade of the aero-engine as claimed in claim 7, wherein the machining and grinding in the step S3 includes the following steps:
s3.1: rotating the C shaft of the workbench to enable the air inlet end face to be horizontally placed upwards, and then grinding the air inlet end face;
s3.2: then, rotating the C shaft of the workbench to enable the back radial surface to be horizontally placed upwards, and then grinding the back radial surface;
s3.3: rotating the C shaft of the workbench by 180 degrees, then rotating the A shaft to enable the radial surface of the basin to be horizontally placed upwards, and then grinding the radial surface of the basin;
s3.4: the A axis of the workbench rotates, so that the blade tip is horizontally placed upwards, and then the blade tip is ground.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110962257.5A CN113681466A (en) | 2021-08-20 | 2021-08-20 | Novel integrated machining clamp for turbine blade of aero-engine and machining process of novel integrated machining clamp |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110962257.5A CN113681466A (en) | 2021-08-20 | 2021-08-20 | Novel integrated machining clamp for turbine blade of aero-engine and machining process of novel integrated machining clamp |
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| Publication Number | Publication Date |
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| CN113681466A true CN113681466A (en) | 2021-11-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110962257.5A Pending CN113681466A (en) | 2021-08-20 | 2021-08-20 | Novel integrated machining clamp for turbine blade of aero-engine and machining process of novel integrated machining clamp |
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| CN (1) | CN113681466A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114473866A (en) * | 2022-02-25 | 2022-05-13 | 武汉数字化设计与制造创新中心有限公司 | Automatic clamp and method for grinding and polishing blade robot |
| CN114800161A (en) * | 2022-06-13 | 2022-07-29 | 西安朋邦工贸有限公司 | Clamping fixture and clamping method for machining tenon of turbine working blade |
| CN114888610A (en) * | 2022-05-31 | 2022-08-12 | 哈尔滨汽轮机厂有限责任公司 | Tooth-shaped positioning block for positioning blade and clamping and aligning method for machining blade steam passage |
| CN117260588A (en) * | 2023-11-14 | 2023-12-22 | 中国航发沈阳黎明航空发动机有限责任公司 | Low vortex working vane three-coordinate detection universal positioning device |
| CN118578165A (en) * | 2024-08-06 | 2024-09-03 | 国营川西机器厂 | High-precision self-positioning device and method for engine blade |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104384872A (en) * | 2014-09-11 | 2015-03-04 | 重庆Abb江津涡轮增压系统有限公司 | Machining method of turbine blade |
| CN105312864A (en) * | 2015-12-09 | 2016-02-10 | 中国南方航空工业(集团)有限公司 | Machining method of turbine working blade |
| WO2017031618A1 (en) * | 2015-08-21 | 2017-03-02 | 深圳智慧能源技术有限公司 | Broaching machine and broaching tool for machining circular arc groove |
| CN106624897A (en) * | 2016-12-28 | 2017-05-10 | 无锡透平叶片有限公司 | Rotary machining fixture for small and medium-sized square steel tenon-tooth-shaped root blades |
| CN108372337A (en) * | 2016-12-20 | 2018-08-07 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of positioning of blade and fixing device and its realize blade positioning and fixed method |
-
2021
- 2021-08-20 CN CN202110962257.5A patent/CN113681466A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104384872A (en) * | 2014-09-11 | 2015-03-04 | 重庆Abb江津涡轮增压系统有限公司 | Machining method of turbine blade |
| WO2017031618A1 (en) * | 2015-08-21 | 2017-03-02 | 深圳智慧能源技术有限公司 | Broaching machine and broaching tool for machining circular arc groove |
| CN105312864A (en) * | 2015-12-09 | 2016-02-10 | 中国南方航空工业(集团)有限公司 | Machining method of turbine working blade |
| CN108372337A (en) * | 2016-12-20 | 2018-08-07 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of positioning of blade and fixing device and its realize blade positioning and fixed method |
| CN106624897A (en) * | 2016-12-28 | 2017-05-10 | 无锡透平叶片有限公司 | Rotary machining fixture for small and medium-sized square steel tenon-tooth-shaped root blades |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114473866A (en) * | 2022-02-25 | 2022-05-13 | 武汉数字化设计与制造创新中心有限公司 | Automatic clamp and method for grinding and polishing blade robot |
| CN114888610A (en) * | 2022-05-31 | 2022-08-12 | 哈尔滨汽轮机厂有限责任公司 | Tooth-shaped positioning block for positioning blade and clamping and aligning method for machining blade steam passage |
| CN114800161A (en) * | 2022-06-13 | 2022-07-29 | 西安朋邦工贸有限公司 | Clamping fixture and clamping method for machining tenon of turbine working blade |
| CN114800161B (en) * | 2022-06-13 | 2023-08-15 | 西安朋邦工贸有限公司 | Clamping fixture and clamping method for machining tenon of turbine working blade |
| CN117260588A (en) * | 2023-11-14 | 2023-12-22 | 中国航发沈阳黎明航空发动机有限责任公司 | Low vortex working vane three-coordinate detection universal positioning device |
| CN117260588B (en) * | 2023-11-14 | 2024-01-30 | 中国航发沈阳黎明航空发动机有限责任公司 | Low vortex working vane three-coordinate detection universal positioning device |
| CN118578165A (en) * | 2024-08-06 | 2024-09-03 | 国营川西机器厂 | High-precision self-positioning device and method for engine blade |
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Application publication date: 20211123 |
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