CN214095804U - Super large combustion engine turbine blade position degree detects instrument - Google Patents
Super large combustion engine turbine blade position degree detects instrument Download PDFInfo
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- CN214095804U CN214095804U CN202023124877.1U CN202023124877U CN214095804U CN 214095804 U CN214095804 U CN 214095804U CN 202023124877 U CN202023124877 U CN 202023124877U CN 214095804 U CN214095804 U CN 214095804U
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Abstract
The utility model discloses a super large gas turbine blade position degree detection tool, which is used for detecting the position degree of a processed tenon profile and a processed blade shroud profile and comprises a base, a first positioning component, a first measuring block, a second positioning component and a second measuring block; the first positioning assembly and the first measuring block are fixed on the left side of the base, and the second positioning assembly and the second measuring block are fixed on the right side of the base; the first measuring block and the second measuring block are respectively positioned at the opposite outward sides of the first positioning component and the second positioning component. The utility model discloses a first locating component and second locating component are fixed a position respectively turbine blade tenon place end and turbine blade shroud place end and are laid, recycle first measuring block and second measuring block and detect the position degree of tenon profile and blade shroud profile respectively for the benchmark, reasonable in design, simple structure can be fast with turbine blade location installation and can carry out accurate position degree measurement to tenon and blade shroud part, have improved measurement of efficiency effectively.
Description
Technical Field
The utility model relates to a turbine blade detects and surveys utensil technical field, especially relates to a super large gas turbine blade position degree detects instrument.
Background
The turbine blade of the combustion engine is one of important parts of the gas turbine, as shown in fig. 1, the turbine blade generally comprises four parts, namely a tenon, an extending root, a blade body and a blade shroud, and has the characteristics of complex structure, long service life, multi-fuel applicability and the like. At present, the core technology for manufacturing turbine blades of combustion engines, particularly the core technology for manufacturing turbine blades of large-scale combustion turbines and ultra-large gas turbines, is in an absolute technical blockade state abroad for a long time, although China is always researching the turbine blades, the turbine blades are still in the research and development level of laboratories, and a large number of engineering application technical problems still need to be solved.
With the improvement of scientific research technology and manufacturing equipment in China, the end machining technology of the turbine blade of the combustion engine and the end machining technology of the large-scale combustion turbine are gradually solved and mastered in China, deep research is carried out on the end machining technology of the turbine blade of the ultra-large combustion engine, a machining tool and a machining method for the turbine blade of the ultra-large combustion engine are correspondingly produced, and based on the end machining tool and the machining method, the key size of the machined turbine blade of the ultra-large combustion engine is determined to be processed in a flush mode. At present, the tool for detecting the position degree of the end part molded surface of the ultra-large gas turbine blade is lacked in the prior art, if universal measuring tools such as a three-coordinate measuring instrument are used for detecting, the efficiency is low, the cost is high, the practicability is poor, and the production requirement is difficult to meet.
SUMMERY OF THE UTILITY MODEL
Therefore, the position degree detection tool for the turbine blade of the ultra-large combustion engine is needed to solve the problems, the turbine blade can be quickly positioned and installed, and accurate position degree measurement can be carried out on the tenon and the blade crown.
The utility model discloses a following technical scheme realizes:
a tool for detecting the position degree of a turbine blade of an oversized gas turbine is used for detecting the position degree of a processed tenon molded surface and a processed blade shroud molded surface and comprises a base, a first positioning assembly, a first measuring block, a second positioning assembly and a second measuring block; the first positioning assembly and the first measuring block are fixed on the left side of the base, and the second positioning assembly and the second measuring block are fixed on the right side of the base; the first measuring block and the second measuring block are respectively positioned at the opposite outward sides of the first positioning component and the second positioning component.
In one embodiment, the front side surface of the first measuring block is parallel to the side surface of the leading edge tenon of the turbine blade, and the front side surface of the first measuring block is provided with a first horizontal measuring groove; the rear side face of the first measuring block is parallel to the side face of the rear edge tenon of the turbine blade, and a second horizontal measuring groove is formed in the rear side face of the first measuring block.
In one embodiment, the front side surface of the second measuring block is parallel to the side surface of the leading edge shroud of the turbine blade, and the front side surface of the second measuring block is provided with a third horizontal measuring groove; the rear side face of the second measuring block is parallel to the side face of the trailing edge shroud of the turbine blade, and a fourth horizontal measuring groove is formed in the rear side face of the second measuring block.
In one embodiment, the measuring device further comprises a third measuring block, wherein the third measuring block is fixed on the front side or the rear side of the base and corresponds to the leading edge tenon side or the trailing edge tenon side of the turbine blade; the free end of the third measuring block is provided with a first step surface corresponding to the first concave tooth of the tenon, and a second step surface corresponding to the last concave tooth of the tenon.
In one embodiment, the first positioning assembly comprises a first positioning block, a second positioning block and a third positioning block, the first positioning block is provided with a first supporting end used for being in contact with the back surface of the extending root of the turbine blade, the second positioning block is provided with a second supporting end used for being in contact with the front edge surface of the extending root of the turbine blade, and the third positioning block is provided with a third supporting end used for being in contact with the bottom side surface of the extending root of the turbine blade.
In one embodiment, the second positioning assembly comprises a fourth positioning block, a fifth positioning block and a sixth positioning block, the fourth positioning block is provided with a fourth supporting end used for being in contact with the blade body of the turbine blade in a back-facing mode, the fifth positioning block is provided with a fifth supporting end used for being in contact with the blade body front edge surface of the turbine blade, and the sixth positioning block is provided with a sixth supporting end used for being in contact with the blade body of the turbine blade in a back-facing mode.
In one embodiment, the sixth positioning block is a movable positioning block and comprises a connecting seat and a movable block, a movable groove is formed in the connecting seat, and the movable block is movably embedded in the movable groove and is connected with the groove bottom of the movable groove through an elastic piece; one side of the connecting seat is provided with a threaded through hole, a jacking bolt penetrates through the threaded through hole, and the jacking bolt penetrates through the threaded through hole and abuts against the side face of the movable block.
In one embodiment, the side surface of the movable block is provided with a wedge-shaped groove which is obliquely and inwardly arranged from the opening direction of the movable groove to the bottom direction of the movable groove; the thread through hole is arranged corresponding to the wedge-shaped groove and is vertical to the inclined plane of the wedge-shaped groove.
In one embodiment, the turbine blade positioning device further comprises a pressing mechanism for pressing the turbine blade to measure, wherein the pressing mechanism is fixed on the upper surface of the base and is positioned in the middle between the first positioning assembly and the second positioning assembly.
In one embodiment, the surface of the base is provided with a plurality of through grooves.
Compared with the prior art, the technical scheme of the utility model following advantage and beneficial effect have at least:
the utility model discloses a first locating component fixes a position and lays turbine blade tenon place end, fix a position through second locating component to turbine blade shroud place end and lay, recycle first measuring block and detect the position degree of tenon profile for the benchmark, utilize the second measuring block to detect the position degree of blade shroud profile for the benchmark, whole device reasonable in design, moreover, the steam generator is simple in structure, can fix a position the turbine blade installation fast and can carry out accurate position degree measurement to tenon and blade shroud part, and the detection operation at both ends can go on simultaneously, effectively, the measurement of efficiency is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic structural diagram of a turbine blade according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a tool for detecting the position degree of a turbine blade of an oversized gas turbine according to an embodiment of the present invention;
FIG. 3 is an enlarged schematic view at A in FIG. 2;
FIG. 4 is an enlarged schematic view at B of FIG. 2;
fig. 5 is an assembly schematic view of the turbine blade and the turbine blade position degree detection tool for the ultra-large combustion engine provided by the embodiment of the present invention;
FIG. 6 is an enlarged schematic view at C of FIG. 5;
FIG. 7 is a left side view of FIG. 5;
FIG. 8 is a right side view of FIG. 5;
fig. 9 is an internal schematic view of a sixth positioning block according to an embodiment of the present invention.
Icon: 1-base, 11-through groove, 12-suspension ring, 2-first positioning component, 21-first positioning block, 211-first supporting end, 22-second positioning block, 221-second supporting end, 23-third positioning block, 231-third supporting end, 3-first measuring block, 31-first horizontal measuring groove, 32-second horizontal measuring groove, 4-second positioning component, 41-fourth positioning block, 411-fourth supporting end, 42-fifth positioning block, 421-fifth supporting end, 43-sixth positioning block, 431-sixth supporting end/movable block, 4311-wedge groove, 432-connecting seat, 4321-movable groove, 4322-threaded through hole, 433-elastic component, 434-top pressure bolt, 5-second measuring block, 51-third horizontal measuring groove, 52-fourth horizontal measuring groove, 6-third measuring block, 61-first step surface, 62-second step surface, 7-pressing mechanism, 8-turbine blade, 81-tenon, 811-first concave tooth, 812-last concave tooth, 82-root extension, 83-blade body, 84-blade crown and 9-measuring rod.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the following description will combine the drawings in the embodiments of the present invention to describe a turbine blade position degree detection tool for an ultra-large combustion engine more clearly and completely. The drawings show preferred embodiments of the tool for detecting the position of the turbine blade of the super-large combustion engine, however, the tool for detecting the position of the turbine blade of the super-large combustion engine can be realized in many different forms, and is not limited to the embodiments described herein. Rather, these embodiments are provided to make the disclosure of the tool for detecting the position of a turbine blade of an ultra-large combustion engine more thorough.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the present invention belongs. The terms "central," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like, when used in reference to a particular orientation or positional relationship, are used for convenience in describing the invention and to simplify the description, but are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be construed as limiting the invention.
In the description of the present invention, it should be further noted that the terms "disposed," "mounted," "connected," and "connected" used herein should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1, the turbine blade 8 of the present invention mainly includes four parts, i.e., a tenon 81, an extension root 82, a blade body 83, and a blade shroud 84, wherein the tenon 81 has a plurality of formed surfaces, including a basin-shaped tenon tooth, a back-shaped tenon tooth, a leading edge tenon side surface, and a trailing edge tenon side surface; the extending root 82 is positioned between the tenon 81 and the blade body 83, and the detection of the tenon part is completed by positioning the end of the extending root 82 where the tenon of the turbine blade is positioned; the blade body 83 is a twisted blade with a variable cross section, the cross section area of which is gradually increased from the root to the top, and the concave side surface of the blade body 83 is generally called a basin-facing surface, and the convex side surface of the blade body 83 is called a back-facing surface; the other end of the blade body 83 is a tip shroud 84, the tip shroud 84 also has a plurality of machined surfaces, mainly including the tip shroud 84 top surface, the leading edge tip shroud 84 side surface and the trailing edge tip shroud 84 side surface, and the tip shroud part is inspected by positioning the blade body 83 at the end where the turbine blade tip shroud is located.
As shown in fig. 1, fig. 2 and fig. 5, an embodiment of the present invention provides a tool for detecting the position degree of a turbine blade of an ultra-large combustion engine, which is used for detecting the position degree of a profile of a tenon 81 and a profile of a blade shroud 84 after machining, and includes a base 1, a first positioning assembly 2, a first measuring block 3, a second positioning assembly 4 and a second measuring block 5; the first positioning component 2 and the first measuring block 3 are fixed on the left side of the base 1, and the second positioning component 4 and the second measuring block 5 are fixed on the right side of the base 1; the first measuring block 3 and the second measuring block 5 are respectively positioned at the opposite outward sides of the first positioning component 2 and the second positioning component 4. Can fix a position through first locating component 2 and lay turbine blade 8 tenon place end, can fix a position through second locating component 4 and lay turbine blade 8 blade shroud place end, recycle first measuring block 3 and detect for the position degree of benchmark to the tenon profile, utilize second measuring block 5 to detect for the position degree of benchmark to the blade shroud profile, carry out accurate position degree measurement to tenon 81 and blade shroud 84 part, and the detection operation at both ends can go on simultaneously, the efficiency of measurement has been improved effectively.
Specifically, the base 1 is used for providing a reference plane for the positioning component and the measuring block, and ensuring the reliability of the horizontal positions of the positioning component and the measuring block, and the base 1 is generally plate-shaped, but may also be in other shapes. The base 1, the positioning component and the measuring block are aligned and connected in a bolt and pin mode, and can also be connected in a welding mode or an industrial glue bonding mode.
Further, as shown in fig. 1, 2, 5 and 7, the front side surface of the first measuring block 3 is designed to be parallel to the side surface of the leading edge tenon of the turbine blade 8, the front side surface of the first measuring block 3 is provided with a first horizontal measuring groove 31, and a measuring tool such as a measuring rod 9 can be installed or placed in the first horizontal measuring groove 31 to measure the side surface of the leading edge tenon of the turbine blade 8; the rear side surface of the first measuring block 3 is designed to be parallel to the rear edge tenon side surface of the turbine blade 8, the rear side surface of the first measuring block 3 is provided with a second horizontal measuring groove 32, and measuring tools such as a measuring rod 9 can be installed or placed in the second horizontal measuring groove 32 so as to measure the rear edge tenon side surface of the turbine blade 8.
Further, as shown in fig. 1, fig. 2, fig. 5 and fig. 8, the front side surface of the second measuring block 5 is designed to be parallel to the side surface of the leading edge shroud 84 of the turbine blade 8, the front side surface of the second measuring block 5 is provided with a third horizontal measuring groove 51, and a measuring tool such as a measuring rod 9 can be installed or placed in the third horizontal measuring groove 51 to measure the side surface of the leading edge shroud of the turbine blade 8; the rear side surface of the second measuring block 5 is designed to be parallel to the trailing edge shroud side surface of the turbine blade 8, the rear side surface of the second measuring block 5 is provided with a fourth horizontal measuring groove 52, and measuring tools such as a measuring rod 9 can be installed or placed in the fourth horizontal measuring groove 52 to measure the trailing edge shroud side surface of the turbine blade 8.
Further, as shown in fig. 2, 3, 5 and 6, a third measuring block 6 is further included, and the third measuring block 6 is fixed on the front side or the rear side of the base 1 and corresponds to the leading edge tenon side or the trailing edge tenon side of the turbine blade 8; the free end of the third measuring block 6 is formed with a first step surface 61 corresponding to the first concave tooth 811 of the tenon 81, a second step surface 62 corresponding to the last concave tooth 812 of the tenon 81, and the measuring rod 9 is placed on the first concave tooth 811 and the last concave tooth 812 and is compared with the first step surface 61 and the second step surface 62 in height, so that the position degree of the tenon tooth can be measured. For example, after the measuring bar 9 is placed on the first concave tooth 811 and the last concave tooth 812, when the horizontal height of the measuring bar 9 at the first concave tooth 811 is consistent with the first step surface 61, and the horizontal height of the measuring bar 9 at the last concave tooth 812 is consistent with the second step surface 62, the tenon tooth position is correct.
Further, as shown in fig. 2, 3 and 5, the first positioning assembly 2 includes a first positioning block 21, a second positioning block 22 and a third positioning block 23, the first positioning block 21 is provided with a first supporting end 211 for contacting with a back surface of the extended root of the turbine blade 8, the second positioning block 22 is provided with a second supporting end 221 for contacting with a front edge surface of the extended root of the turbine blade 8, and the third positioning block 23 is provided with a third supporting end 231 for contacting with a bottom side surface of the extended root of the turbine blade 8. The tenon-located end of the turbine blade 8 can be spatially positioned in the three directions of the X-axis, the Y-axis and the Z-axis by the first support end 211, the second support end 221 and the third support end 231.
In addition, because the length direction of stretching the root 82 is longer, the first supporting end 211 can be formed with two, distribute at the both ends of stretching the root 82 length direction to contact with stretching the root 82 dorsad simultaneously, thereby play stable effectual positioning action. The third support end 231 is embodied as a process ball to make point contact with the bottom side of the stub 82.
Further, as shown in fig. 2, 4 and 5, the second positioning assembly 4 includes a fourth positioning block 41, a fifth positioning block 42 and a sixth positioning block 43, the fourth positioning block 41 is provided with a fourth supporting end 411 for contacting with the blade body of the turbine blade 8 in a back-to-face manner, the fifth positioning block 42 is provided with a fifth supporting end 421 for contacting with the blade body leading edge surface of the turbine blade 8, and the sixth positioning block 43 is provided with a sixth supporting end 431 for contacting with the blade body of the turbine blade 8 in a back-to-face manner. The tip of the turbine blade 8 at which the tip shroud is located can be spatially positioned in the three directions of the X axis, the Y axis and the Z axis by the fourth supporting end 411, the fifth supporting end 421 and the sixth supporting end 431. Preferably, the sixth supporting end 431 and the fourth supporting end 411 are located on the same straight line in the front-rear direction, thereby achieving effective supporting and positioning and avoiding generation of a shearing force.
In addition, the fourth supporting end 411 and the fifth supporting end 421 are specifically pin rods respectively inserted into the fourth positioning block 41 and the fifth positioning block 42, and the peripheral surfaces thereof are arc surfaces to respectively make point contact with the back surface of the blade body and the front edge surface of the blade body, and are convenient to replace when the positioning accuracy is reduced due to the abrasion of the pin rods.
Further, as shown in fig. 4 and 9, the sixth positioning block 43 is a movable positioning block, and includes a connecting seat 432 and a movable block 431, a movable groove 4321 is formed on the connecting seat 432, and the movable block 431 is movably embedded in the movable groove 4321 and connected with the groove bottom of the movable groove 4321 through an elastic member 433; one side of the connecting seat 432 is provided with a threaded through hole 4322, a jacking bolt 434 penetrates through the threaded through hole 4322, and the jacking bolt 434 penetrates through the threaded through hole 4322 and abuts against the side surface of the movable block. Preferably, the movable block 431 and the fourth supporting end 411 are located at the same line in the front-rear direction, thereby achieving effective supporting and positioning and avoiding generation of a shearing force.
Specifically, after the turbine blade 8 is placed on the base 1, the back surface of the blade body is in contact with the movable block 431 and presses the movable block 431 into the movable groove 4321, at this time, the elastic piece 433 presses the movable block 431 against the back surface of the blade body, and after the turbine blade 8 is installed in place, the jacking bolt 434 is screwed inwards to limit the displacement of the movable block 431 in the movable groove 4321, so that the turbine blade 8 is accurately placed on the positioning assembly.
Further, as shown in fig. 9, a wedge-shaped groove 4311 is formed in a side surface of the movable block 431, and the wedge-shaped groove 4311 is formed obliquely inward (inside the movable block 431) from the opening direction of the movable groove 4321 to the groove bottom direction of the movable groove 4321; the through hole 4322 is formed corresponding to the wedge-shaped groove 4311 and perpendicular to the inclined surface of the wedge-shaped groove 4311, so that the pressing bolt 434 can abut against the inclined surface of the wedge-shaped groove 4311 after being screwed inward, thereby effectively limiting the displacement of the movable block 431 in the movable groove 4321.
Further, as shown in fig. 2 and 5, a pressing mechanism 7 for pressing the turbine blade 8 for measurement is further included, the pressing mechanism 7 is fixed on the base 1 and located in the middle between the first positioning component 2 and the second positioning component 4, and the specific configuration of the pressing mechanism 7 is the prior art and will not be described herein again. During the use, hold-down mechanism 7 presses and holds the middle part at the blade body 83 basin of turbine blade 8 to the face, from last down firmly press turbine blade 8 and hold on first locating component 2 and second locating component 4, accomplish compressing tightly of turbine blade 8 and fix.
Further, as shown in fig. 2, a plurality of through grooves 11 may be formed on the surface of the base 1, so as to achieve the purpose of reducing weight.
Further, as shown in fig. 2, a lifting ring 12 is correspondingly arranged on the upper surface of the base 1, and the detection tool is transported through the lifting ring 12, so that the accuracy of the positioning assembly and the measurement block arranged on the base 1 is prevented from being affected.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A tool for detecting the position degree of a turbine blade of an oversized gas turbine is used for detecting the position degree of a processed tenon molded surface and a processed blade shroud molded surface, and is characterized by comprising a base, a first positioning assembly, a first measuring block, a second positioning assembly and a second measuring block; the first positioning assembly and the first measuring block are fixed on the left side of the base, and the second positioning assembly and the second measuring block are fixed on the right side of the base; the first measuring block and the second measuring block are respectively positioned at the opposite outward sides of the first positioning component and the second positioning component.
2. The tool for detecting the position degree of the turbine blade of the ultra-large combustion engine as claimed in claim 1, wherein the front side surface of the first measuring block is parallel to the front edge tenon side surface of the turbine blade, and a first horizontal measuring groove is formed in the front side surface of the first measuring block; the rear side face of the first measuring block is parallel to the side face of the rear edge tenon of the turbine blade, and a second horizontal measuring groove is formed in the rear side face of the first measuring block.
3. The tool for detecting the position degree of the turbine blade of the ultra-large combustion engine as claimed in claim 1, wherein the front side surface of the second measuring block is parallel to the side surface of the leading edge shroud of the turbine blade, and a third horizontal measuring groove is formed in the front side surface of the second measuring block; the rear side face of the second measuring block is parallel to the side face of the trailing edge shroud of the turbine blade, and a fourth horizontal measuring groove is formed in the rear side face of the second measuring block.
4. The tool for detecting the position degree of the turbine blade of the ultra-large combustion engine as claimed in any one of claims 1 to 3, further comprising a third measuring block, wherein the third measuring block is fixed on the front side or the rear side of the base and corresponds to the leading edge tenon side or the trailing edge tenon side of the turbine blade; the free end of the third measuring block is provided with a first step face corresponding to the first concave tooth of the tenon, and a second step face corresponding to the last concave tooth of the tenon.
5. The tool for detecting the position degree of the turbine blade of the ultra-large combustion engine as claimed in claim 1, wherein the first positioning assembly comprises a first positioning block, a second positioning block and a third positioning block, the first positioning block is provided with a first supporting end used for being in contact with the back surface of the extending root of the turbine blade, the second positioning block is provided with a second supporting end used for being in contact with the front edge surface of the extending root of the turbine blade, and the third positioning block is provided with a third supporting end used for being in contact with the bottom side surface of the extending root of the turbine blade.
6. The tool for detecting the position degree of the turbine blade of the ultra-large combustion engine as claimed in claim 1, wherein the second positioning assembly comprises a fourth positioning block, a fifth positioning block and a sixth positioning block, the fourth positioning block is provided with a fourth supporting end for contacting with the blade body of the turbine blade in a back-to-face manner, the fifth positioning block is provided with a fifth supporting end for contacting with the blade body leading edge surface of the turbine blade, and the sixth positioning block is provided with a sixth supporting end for contacting with the blade body of the turbine blade in a back-to-face manner.
7. The tool for detecting the position degree of the turbine blade of the ultra-large combustion engine according to claim 6, wherein the sixth positioning block is a movable positioning block and comprises a connecting seat and a movable block, a movable groove is formed in the connecting seat, and the movable block is movably embedded in the movable groove and connected with the groove bottom of the movable groove through an elastic piece; one side of the connecting seat is provided with a threaded through hole, a jacking bolt penetrates through the threaded through hole, and the jacking bolt penetrates through the threaded through hole and abuts against the side face of the movable block.
8. The tool for detecting the position degree of the turbine blade of the ultra-large combustion engine as claimed in claim 7, wherein a wedge-shaped groove is formed in the side surface of the movable block, and the wedge-shaped groove is formed from the opening direction of the movable groove to the bottom direction of the movable groove in an inclined inward mode; the thread through hole is formed corresponding to the wedge-shaped groove and is perpendicular to the inclined plane of the wedge-shaped groove.
9. The tool for detecting the position degree of the turbine blade of the ultra-large combustion engine according to any one of claims 1 and 5 to 8, further comprising a pressing mechanism for pressing the turbine blade for measurement, wherein the pressing mechanism is fixed on the base and is located in the middle between the first positioning assembly and the second positioning assembly.
10. The tool for detecting the position degree of the turbine blade of the ultra-large combustion engine as claimed in claim 1, wherein a plurality of through grooves are formed in the surface of the base.
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| CN202023124877.1U CN214095804U (en) | 2020-12-22 | 2020-12-22 | Super large combustion engine turbine blade position degree detects instrument |
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| CN202023124877.1U CN214095804U (en) | 2020-12-22 | 2020-12-22 | Super large combustion engine turbine blade position degree detects instrument |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114001630A (en) * | 2021-11-10 | 2022-02-01 | 中国航发南方工业有限公司 | Blade body groove eccentricity measuring device and method for guide blade |
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2020
- 2020-12-22 CN CN202023124877.1U patent/CN214095804U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114001630A (en) * | 2021-11-10 | 2022-02-01 | 中国航发南方工业有限公司 | Blade body groove eccentricity measuring device and method for guide blade |
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Address after: No. 2899, Nanwu Road, Chengdu Economic and Technological Development Zone (Longquanyi District), Sichuan 610100 Patentee after: Chengdu Hehong Technology Co.,Ltd. Address before: No. 458, East air route, Chengdu Economic and Technological Development Zone, Sichuan 610199 Patentee before: CHENGDU HONF TECHNOLOGY Co.,Ltd. |
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