CN213827976U - Blade root milling clamp for small and medium-sized combustion engine turbine blades - Google Patents
Blade root milling clamp for small and medium-sized combustion engine turbine blades Download PDFInfo
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- CN213827976U CN213827976U CN202021992010.5U CN202021992010U CN213827976U CN 213827976 U CN213827976 U CN 213827976U CN 202021992010 U CN202021992010 U CN 202021992010U CN 213827976 U CN213827976 U CN 213827976U
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Abstract
The utility model provides a mill blade root anchor clamps for middle and small combustion engine turbine blade, it can solve current middle and small combustion engine turbine blade and mill the blade root and fix a position through watering the square chest, has the high problem that pollutes high energy consumption, machining efficiency low and can increase the final blade root size for the unqualified risk of profile. The positioning device comprises a positioning seat, wherein a supporting lug is formed on the top surface of the positioning seat, two blade body inner arc positioning surfaces are respectively formed on the front and the back of the top surface of the supporting lug, and an axial positioning surface is also formed on the front end surface of the supporting lug; the top surface of the positioning seat is also fixedly provided with an air inlet side positioning block, and positioning bosses which can be attached to the air inlet edges of the turbine blades of the medium and small combustion engines are respectively formed at the front and the rear of the side surface of the air inlet side positioning block; still install the main subassembly that compresses tightly on the top surface of positioning seat, the main subassembly that compresses tightly is equipped with two main pressing surfaces, and two main pressing surfaces correspond the setting with anterior two blade inner arc locating surfaces respectively for the back of the body arc profile that pastes and compress tightly the blade.
Description
Technical Field
The utility model relates to a processing frock field of middle and small combustion engine turbine blade specifically is a mill blade root anchor clamps that is used for middle and small combustion engine turbine blade.
Background
After the national thirteen-five energy strategy planning and adjustment, the development of the high-end equipment manufacturing industry is continuously promoted in China, the important special item of two machines of an aero-engine and a gas turbine is comprehensively started and implemented, a plurality of policies are continuously issued, the key technology of the two machines is broken through, the basic research and the technology of the independent innovation of the two machines are established, and the national scientific and technological work is the key point.
FIG. 1 shows a high-pressure turbine blade of a certain type of gas turbine, which is a turbine blade of a medium and small gas turbine, the blade is a high-temperature alloy precision-cast blade, the profile of the blade body is precisely cast, the weight of the finished product is 20g, the total length of the blade is 45mm, the width of the blade root is 29mm, and the blade root needs to be milled. For the blade with the small overall dimension, the design of the milling tool, the clamping efficiency and the stability of the processing quality are difficult problems for a long time.
At present, the commonly used blade root milling and clamping mode in the industry is to add a procedure of pouring a square box, fix a blade body in a small square box through tin-bismuth alloy, and then mill and process a blade root in a square box positioning mode. This approach has the following disadvantages: 1) the square box pouring process becomes a high-energy-consumption and high-pollution process and is a process which is gradually eliminated in the future; 2) the blade body is fixed in the square box through the tin-bismuth alloy, a reference conversion process is actually added, the molded surface of the blade is formed by precision casting, and the risk that the final blade root size is unqualified relative to the molded surface is increased by adding one reference conversion process; 3) after the blade root is machined, a square box removing procedure needs to be added, namely a square box is poured and a square box is removed, so that the process route is lengthened, and the production period is prolonged.
Disclosure of Invention
The mill blade root to current middle and small gas turbine blade is fixed a position through watering the square chest, has high pollution high energy consumption, machining efficiency low and can increase the technical problem of final blade root size for the unqualified risk of profile, the utility model provides a mill blade root anchor clamps for middle and small gas turbine blade, it can direct clamping location blade, need not to water the square chest, and pollution-free low energy consumption improves machining efficiency to final blade root size is for the good uniformity of profile size relation.
The technical scheme is as follows: the utility model provides a mill blade root anchor clamps for middle and small combustion engine turbine blade which characterized in that: the blade body positioning device comprises a positioning seat, wherein a supporting convex block arranged along the front-back direction is formed on the top surface of the positioning seat, two blade body inner arc positioning surfaces are formed on the front side and the back side of the top surface of the supporting convex block respectively, an axial positioning surface is further formed on the front end surface of the supporting convex block, when the blade body of the small and medium-sized gas turbine blade is placed on the supporting convex block, the four blade body inner arc positioning surfaces can be simultaneously attached to the inner arc molded surfaces of the blade body, and the axial positioning surfaces can be attached to the edge plate surfaces of the small and medium-sized gas turbine blade; an air inlet side positioning block is fixedly arranged on the top surface of the positioning seat in the air inlet side direction of the small and medium-sized gas turbine blades, and positioning bosses which can be attached to the air inlet side of the small and medium-sized gas turbine blades are respectively formed at the front and the rear of the side surface of the air inlet side positioning block; still install main pressure subassembly on the top surface of positioning seat, be equipped with two main pressure planes on the main pressure subassembly, two main pressure planes correspond the setting with anterior two blade inner arc locating surface respectively for the laminating compresses tightly the back of the body profile of blade.
It is further characterized in that:
the positioning seat is fixedly arranged on the top surface of the bottom plate.
The top surface of the positioning seat is provided with a key groove arranged along the front-back direction in the air inlet side direction of the turbine blade of the medium-small combustion engine, and the lower end of the air inlet side positioning block is inserted into the key groove in a matched manner and is fixedly connected with the positioning seat.
The positioning boss is of a vertically arranged strip-shaped structure, and oblique chamfers are respectively machined on the front side surface and the rear side surface of the positioning boss close to one side of the air inlet edge.
The main compression assembly comprises a compression seat, a pressure plate and a main compression screw, the compression seat is of an inverted U-shaped structure and is fixedly mounted on the top surface of the positioning seat, and the supporting bump and the air inlet side positioning block are both positioned in a U-shaped groove of the compression seat; the pressing plate is inserted in the U-shaped groove in a sliding fit mode, the rear end of the pressing plate is rotatably connected with the pressing seat through a horizontal shaft, and the two main pressing surfaces are arranged on the bottom surface of the front end of the pressing plate; the top of the pressing seat is provided with a first vertical threaded hole, and the main pressing screw is assembled in the first vertical threaded hole in a threaded fit mode and can press the front end of the pressing plate.
The blade body pressing device is characterized by further comprising a first auxiliary pressing screw, a second vertical threaded hole is formed in the top of the pressing seat, the first auxiliary pressing screw is assembled in the second vertical threaded hole in a threaded fit mode and can press the back arc molded surface of the blade body, and the first auxiliary pressing screw and one of the inner arc positioning surfaces of the blade body at the rear portion are arranged correspondingly.
The blade pressing device is characterized by further comprising a second auxiliary pressing screw, an inclined threaded hole is formed in the top of the pressing seat, the second auxiliary pressing screw is assembled in the inclined threaded hole in a threaded matching mode and can press the back arc molded surface of the blade body, and the second auxiliary pressing screw corresponds to the other rear inner arc positioning surface of the blade body.
The utility model has the advantages that:
the utility model discloses a mill blade root anchor clamps for middle and small gas turbine blade adopts the mode of the four sections whole locating surfaces of blade body inner arc (being four blade body inner arc locating surfaces), two whole locating points of blade body side of admitting air (being two location bosss), the excessive location of a locating surface of blade axial (being axial locating surface), adopts two sections whole pressing surfaces (being two main pressing surfaces) to compress tightly simultaneously, can realize the stable clamping location to middle and small gas turbine blade, clamping reliability and stability are high, and anchor clamps simple structure simultaneously, and the frock cost is low, and the simple operation; because the square box does not need to be poured, the environment is protected, the pollution is not caused, the energy consumption is low, the reference conversion is carried out for one time, the blade root is directly positioned and processed by the blade body molded surface which is subjected to the precision casting, the size of the blade root is good in consistency relative to the size of the molded surface finally, the square box does not need to be poured, the square box does not need to be removed, two procedures are reduced, the production period is shortened, and the processing efficiency is improved.
Drawings
FIG. 1 is a schematic overall structure diagram of a high-pressure turbine blade of a certain type of combustion engine;
FIG. 2 is a front view of the present invention;
fig. 3 is a schematic view of the overall structure of the present invention along one direction (the bottom plate is not shown);
fig. 4 is a schematic view of the overall structure of the present invention along another direction (the bottom plate is not shown);
FIG. 5 is a schematic view of the overall structure of the positioning base;
FIG. 6 is a schematic overall structure diagram of an air inlet side positioning block;
FIG. 7 is a schematic view of the overall structure of the pressing base;
fig. 8 is a schematic view of the entire structure of the platen.
Reference numerals: 1-a bottom plate; 2-positioning seat; 3-supporting the bumps; 4-positioning surface of inner arc of blade body; 5-axial positioning surface; 6-turbine blades of medium and small combustion engines; 7-leaf body; 8-inner arc profile; 9-edge plate surface; 10-air inlet side positioning blocks; 11-an air inlet side; 12-positioning a boss; 13-a primary compression face; 14-back arc profile; 15-key groove; 16-chamfering; 17-a compression seat; 18-a platen; 19-main compression screw; 20-U-shaped slots; 21-horizontal shaft hole; 22-horizontal axis; 23-a vertical threaded hole I; 24-auxiliary compression screw one; 25-auxiliary compression screw II; 26-vertical threaded hole II; 27-oblique threaded hole; 28-a through hole; 29-through groove.
Detailed Description
Referring to fig. 1 to 8, the utility model discloses a blade root milling clamp for small and medium-sized combustion engine turbine blades, which comprises a bottom plate 1 and a positioning seat 2, wherein the positioning seat 2 is fixedly installed on the top surface of the bottom plate 1 through a cylindrical pin and a screw; a supporting convex block 3 arranged along the front-back direction is formed on the top surface of the positioning seat 2, two blade body inner arc positioning surfaces 4 are formed on the front and back of the top surface of the supporting convex block 3 respectively, an axial positioning surface 5 is further formed on the front end surface of the supporting convex block 3, when the blade body 7 of the small and medium-sized gas turbine blade 6 is placed on the supporting convex block 3, the four blade body inner arc positioning surfaces 4 can be attached to the inner arc molded surface 8 of the blade body 7 at the same time, and the axial positioning surface 5 can be attached to the edge plate surface 9 of the small and medium-sized gas turbine blade 6; an air inlet side positioning block 10 is fixedly arranged on the top surface of the positioning seat 2 in the air inlet side direction of the small and medium-sized combustion engine turbine blades 6, and positioning bosses 12 capable of being attached to air inlet edges 11 of the small and medium-sized combustion engine turbine blades 6 are respectively formed in the front and at the back of the side surface of the air inlet side positioning block 10; still install the main subassembly that compresses tightly on the top surface of positioning seat 2, be equipped with two main pressing surfaces 13 on the main subassembly that compresses tightly, two main pressing surfaces 13 correspond the setting with anterior two blade body inner arc locating surfaces 4 respectively for the back of the body profile 14 of laminating and compressing tightly blade 7.
Referring to fig. 2 and 5, a key groove 15 arranged along the front-back direction is formed in the top surface of the positioning seat 2 in the air inlet side direction of the turbine blade 6 of the medium-small combustion engine, and the lower end of the air inlet side positioning block 10 is inserted into the key groove 15 in a matching manner and is fixedly connected with the positioning seat 2 through a cylindrical pin and a screw. By the design, the positioning and installation of the air inlet side positioning block are facilitated, and the air inlet edge of the blade can be accurately positioned by the air inlet side positioning block.
Referring to fig. 6, the positioning boss 12 is a vertically arranged bar structure, and the front and rear side surfaces of the positioning boss 12 near the air inlet edge 11 are respectively processed with an oblique chamfer 16. By the design, the contact area between the positioning boss and the air inlet edge of the blade is reduced, and the positioning is more accurate and reliable.
Referring to fig. 2 to 8, the main pressing assembly includes a pressing base 17, a pressing plate 18 and a main pressing screw 19, the pressing base 17 is in an inverted U-shaped structure and is fixedly mounted on the top surface of the positioning base 2 through a cylindrical pin and a screw, and the supporting protrusion 3 and the air inlet side positioning block 10 are both located in a U-shaped groove 20 of the pressing base 17; the pressing plate 18 is inserted into the U-shaped groove 20 in a sliding fit mode, namely the left side surface and the right side surface of the pressing plate 18 are in sliding fit with the two side surfaces of the U-shaped groove 20, the rear end of the pressing plate 18 and the pressing seat 17 are provided with horizontal shaft holes 21 which are communicated with each other, a horizontal shaft 22 penetrates through the horizontal shaft holes 21 in the pressing plate 18, the two ends of the horizontal shaft 22 are respectively inserted into the horizontal shaft holes 21 in the pressing seat 17, the pressing plate 18 is connected with the pressing seat 17 in a rotating mode, and the two main pressing surfaces 13 are arranged on; the top of the pressing seat 17 is provided with a vertical threaded hole I23, and a main pressing screw 19 is assembled in the vertical threaded hole I23 in a threaded fit mode and can press the front end of the pressing plate 18. So design, compact structure screws main housing screw, can make two main housing screw on the clamp plate laminate and compress tightly the back arc profile of blade body, loosens main housing screw, upwards rotates the clamp plate, can relieve the compressing tightly to the blade, convenient operation, simple structure.
See fig. 2 to 8, the utility model discloses a mill blade root anchor clamps for middle and small combustion engine turbine blade still includes supplementary housing screw 24 and supplementary housing screw two 25, vertical screw hole two 26 and slant screw hole 27 have still been opened at the top that compresses tightly seat 17, supplementary housing screw 24 screw-thread fit assembles in vertical screw hole two 26 and can compress tightly back of the body arc profile 14 of blade 7, supplementary housing screw 24 corresponds the setting with one of them blade inner arc locating surface 4 at rear portion, supplementary housing screw two 25 screw-thread fit assembles in slant screw hole 27 and can compress tightly back of the body arc profile 14 of blade 7, supplementary housing screw two 25 corresponds the setting with another blade inner arc locating surface 4 at rear portion. By the design, the auxiliary compression screw I and the auxiliary compression screw II can further compress the back arc molded surface of the blade body, so that the clamping stability of the blade is better. In this embodiment, the pressure plate 18 is provided with a through hole 28 for avoiding the auxiliary compression screw one 24 and a through groove 29 for avoiding the auxiliary compression screw two 25, respectively, as shown in fig. 8.
The use process of the clamp of the utility model is adopted under the following specific description: the method comprises the steps of placing the turbine blades 6 of the small and medium-sized combustion engines on the supporting convex blocks 3 of the positioning seats 2 with the inner arc sides facing downwards, ensuring that four blade body inner arc positioning surfaces 4 are simultaneously attached to inner arc molded surfaces 8 of blade bodies 7, ensuring that an axial positioning surface 5 is attached to a flange plate surface 9, ensuring that two positioning bosses 12 on an air inlet side positioning block 10 are simultaneously attached to an air inlet edge 11 of each blade 7, screwing a main compression screw 19, driving a compression plate 18 to compress the blades, enabling two main compression surfaces 13 to be simultaneously attached to back arc molded surfaces 14 of the blade bodies 7, sequentially screwing an auxiliary compression screw one 24 and an auxiliary compression screw two 25 to compress the back arc molded surfaces 14 of the blade bodies 7, and completing clamping.
Claims (7)
1. The utility model provides a mill blade root anchor clamps for middle and small combustion engine turbine blade which characterized in that: the blade body positioning device comprises a positioning seat, wherein a supporting convex block arranged along the front-back direction is formed on the top surface of the positioning seat, two blade body inner arc positioning surfaces are formed on the front side and the back side of the top surface of the supporting convex block respectively, an axial positioning surface is further formed on the front end surface of the supporting convex block, when the blade body of the small and medium-sized gas turbine blade is placed on the supporting convex block, the four blade body inner arc positioning surfaces can be simultaneously attached to the inner arc molded surfaces of the blade body, and the axial positioning surfaces can be attached to the edge plate surfaces of the small and medium-sized gas turbine blade; an air inlet side positioning block is fixedly arranged on the top surface of the positioning seat in the air inlet side direction of the small and medium-sized gas turbine blades, and positioning bosses which can be attached to the air inlet side of the small and medium-sized gas turbine blades are respectively formed at the front and the rear of the side surface of the air inlet side positioning block; still install main pressure subassembly on the top surface of positioning seat, be equipped with two main pressure planes on the main pressure subassembly, two main pressure planes correspond the setting with anterior two blade inner arc locating surface respectively for the laminating compresses tightly the back of the body profile of blade.
2. The blade root milling clamp for the turbine blades of the small and medium-sized combustion engines as claimed in claim 1, wherein: the positioning seat is fixedly arranged on the top surface of the bottom plate.
3. The milling blade root clamp for the turbine blades of small and medium-sized combustion engines according to claim 1 or 2, characterized in that: the top surface of the positioning seat is provided with a key groove arranged along the front-back direction in the air inlet side direction of the turbine blade of the medium-small combustion engine, and the lower end of the air inlet side positioning block is inserted into the key groove in a matched manner and is fixedly connected with the positioning seat.
4. The milling blade root clamp for the turbine blades of small and medium-sized combustion engines according to claim 1 or 2, characterized in that: the positioning boss is of a vertically arranged strip-shaped structure, and oblique chamfers are respectively machined on the front side surface and the rear side surface of the positioning boss close to one side of the air inlet edge.
5. The milling blade root clamp for the turbine blades of small and medium-sized combustion engines according to claim 1 or 2, characterized in that: the main compression assembly comprises a compression seat, a pressure plate and a main compression screw, the compression seat is of an inverted U-shaped structure and is fixedly mounted on the top surface of the positioning seat, and the supporting bump and the air inlet side positioning block are both positioned in a U-shaped groove of the compression seat; the pressing plate is inserted in the U-shaped groove in a sliding fit mode, the rear end of the pressing plate is rotatably connected with the pressing seat through a horizontal shaft, and the two main pressing surfaces are arranged on the bottom surface of the front end of the pressing plate; the top of the pressing seat is provided with a first vertical threaded hole, and the main pressing screw is assembled in the first vertical threaded hole in a threaded fit mode and can press the front end of the pressing plate.
6. The blade root milling clamp for the turbine blades of the small and medium-sized combustion engines as claimed in claim 5, wherein: the blade body pressing device is characterized by further comprising a first auxiliary pressing screw, a second vertical threaded hole is formed in the top of the pressing seat, the first auxiliary pressing screw is assembled in the second vertical threaded hole in a threaded fit mode and can press the back arc molded surface of the blade body, and the first auxiliary pressing screw and one of the inner arc positioning surfaces of the blade body at the rear portion are arranged correspondingly.
7. The blade root milling clamp for the turbine blades of the small and medium-sized combustion engines as claimed in claim 6, wherein: the blade pressing device is characterized by further comprising a second auxiliary pressing screw, an inclined threaded hole is formed in the top of the pressing seat, the second auxiliary pressing screw is assembled in the inclined threaded hole in a threaded matching mode and can press the back arc molded surface of the blade body, and the second auxiliary pressing screw corresponds to the other rear inner arc positioning surface of the blade body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021992010.5U CN213827976U (en) | 2020-09-14 | 2020-09-14 | Blade root milling clamp for small and medium-sized combustion engine turbine blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021992010.5U CN213827976U (en) | 2020-09-14 | 2020-09-14 | Blade root milling clamp for small and medium-sized combustion engine turbine blades |
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| Publication Number | Publication Date |
|---|---|
| CN213827976U true CN213827976U (en) | 2021-07-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021992010.5U Active CN213827976U (en) | 2020-09-14 | 2020-09-14 | Blade root milling clamp for small and medium-sized combustion engine turbine blades |
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| CN (1) | CN213827976U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113523846A (en) * | 2020-09-14 | 2021-10-22 | 无锡透平叶片有限公司 | Blade root milling clamp for small and medium-sized combustion engine turbine blades |
-
2020
- 2020-09-14 CN CN202021992010.5U patent/CN213827976U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113523846A (en) * | 2020-09-14 | 2021-10-22 | 无锡透平叶片有限公司 | Blade root milling clamp for small and medium-sized combustion engine turbine blades |
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