CN114485327A - Device for precisely measuring turbine disc blade assembly and grinding method - Google Patents
Device for precisely measuring turbine disc blade assembly and grinding method Download PDFInfo
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- CN114485327A CN114485327A CN202210197985.6A CN202210197985A CN114485327A CN 114485327 A CN114485327 A CN 114485327A CN 202210197985 A CN202210197985 A CN 202210197985A CN 114485327 A CN114485327 A CN 114485327A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
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Abstract
The invention discloses a device for precisely measuring a turbine disc blade assembly, which comprises a supporting base, a calibration component, a bridge type measurer and a measured component, wherein the calibration component is arranged on the supporting base; v-shaped platforms for placing the alignment components or the tested components are symmetrically arranged on the upper part of the supporting base; the label aligning component comprises a standard disc and a central shaft in the middle; the bridge type measurer comprises a cross beam in the middle, wherein support frames are fixed at two ends of the cross beam, a V-shaped groove matched with a V-shaped table is arranged at the bottom of each support frame, at least one vertical through hole is formed in the middle of the upper surface of the cross beam, a dial indicator is fixedly inserted in each through hole, the head of the dial indicator is arranged at the upper part of the cross beam, and the measuring head of the dial indicator is arranged at the lower part of the cross beam; the tested assembly comprises a turbine disc containing turbine blades and a fixed assembly. The device is used for carrying out precision measurement on the measured component, so that the machining amount needing to be ground is obtained, and the accurate grinding of the turbine disc blade is further realized. The invention can realize high-precision measurement and grinding of the turbine blade, and has simple structure and easy operation.
Description
Technical Field
The invention relates to the technical field of machining, in particular to a device for precisely measuring a turbine disc blade assembly and a grinding method.
Background
Within the turbine disk assembly, a ring of turbine blades is mounted. In general, the new turbine blade is longer than the turbine blade required by the standard, and the whole diameter is larger, so that the turbine blade needs to be measured firstly, and the difference value is obtained by comparing the measured data with the standard data, so that the grinding feed amount is obtained, and the grinding processing can be carried out on an external circular grinder, so that the whole diameter of the turbine disk assembly meets the requirement. The current measurement to new turbine blade all directly adopts slide caliper to measure, but because turbine blade's shape is comparatively special, consequently, use slide caliper measurement in-process, the measuring position relies on artifical naked eye to judge completely, measurement process is comparatively difficult, and slide caliper is because the reason of measuring range and measurement accuracy, the difficult realization of measurement to the great turbine disc of diameter, also hardly reach the requirement in the precision, in addition, to turbine blade measurement in-process, need make the turbine disc keep vertical state, otherwise the measured value has great error, use slide caliper measurement's process, it can't keep vertical state to avoid making the turbine disc, lead to the measured value to have great error.
Disclosure of Invention
The invention aims to provide a device which is simple in structure, convenient and fast to operate and capable of realizing high-precision measurement of turbine blades.
Another object of the present invention is to provide a method for precisely measuring a turbine disk blade assembly based on the above apparatus for precisely measuring a turbine disk blade assembly, so as to precisely grind a turbine disk blade.
The invention is realized by the following technical scheme: the device for precisely measuring the blade assembly of the turbine disk comprises a supporting base, a calibration component, a bridge type measurer and a measured component;
v-shaped platforms for placing the alignment components or the tested components are symmetrically arranged on the upper part of the supporting base;
the mark aligning component comprises a standard disc in the middle and a central shaft which penetrates through the standard disc and is fixed with the standard disc;
the bridge type measurer comprises a cross beam in the middle, support frames are fixed at two ends of the cross beam, a V-shaped groove matched with a V-shaped table is formed in the bottom of each support frame, at least one vertical through hole is formed in the middle of the upper surface of the cross beam, a dial indicator is fixedly inserted into each through hole, the head of each dial indicator is arranged on the upper portion of the cross beam, and the measuring head of each dial indicator is arranged on the lower portion of the cross beam;
the tested assembly comprises a turbine disc containing turbine blades and a fixing assembly for fixing the turbine disc.
The working principle of the technical scheme is that the turbine blades on the turbine disc are precisely measured by constructing the vertical position relation between the dial indicator and the turbine disc and utilizing the accurate reading of the dial indicator. And wherein utilize the standard dish in the standard subassembly to realize zero setting correction to the percentage table, further improve the precision measurement process to turbine disk blade subassembly.
In order to better realize the invention, the outer diameter of the standard disk is divided into three sections, the diameter of each section corresponds to the size of the standard diameter, and tip positioning holes for fixing the center shaft are further arranged at two ends of the center shaft.
In order to better realize the invention, the bridge type measurer further comprises a measuring shell which is coated on the lower part of the dial indicator and is fixed with the dial indicator, the measuring shell is fixed in a through hole in the middle of the cross beam, a measuring rod is arranged in the measuring shell, the top of the measuring rod is in contact with a measuring head on the lower part of the dial indicator, the lower part of the measuring rod extends out of the measuring shell, and a spring which enables the measuring rod to extend out of the measuring shell is further arranged in the measuring shell, so that the measuring rod can reciprocate up and down in the measuring shell.
In order to better realize the invention, further, a longitudinal through hole is further formed in the side edge of the cross beam of the bridge type measurer, the longitudinal through hole in the cross beam is intersected with the vertical through hole in the cross beam, a locking shaft is embedded in the longitudinal through hole in the cross beam, and the locking shaft can fix the measuring shell embedded in the vertical through hole of the cross beam.
In order to better realize the invention, further, a fixing component in the tested component comprises a positioning shaft embedded in the middle of the turbine disc, the positioning shaft is sequentially embedded with a first positioning sleeve and a pressing sleeve from inside to outside, the leftmost end of the positioning shaft is provided with an external thread, the external thread is connected with a locking nut, the locking nut enables the pressing sleeve to press the first positioning sleeve, the first positioning sleeve and the turbine disc are fixed, the positioning shaft and the turbine disc are further fixed, and tip positioning holes are further formed in two ends of the positioning shaft.
In order to better implement the invention, a gasket is further arranged between the locking nut and the pressing sleeve.
In order to better realize the invention, the right end of the positioning shaft in the tested assembly is a round fixed block, a second positioning sleeve is arranged between the round fixed block and the turbine disc, a bushing is arranged between the turbine disc and the positioning shaft in the second positioning sleeve, and tip positioning holes are further arranged at two ends of the positioning shaft.
In order to better realize the invention, the supporting base comprises a groined base formed by square aluminum profiles, corner connecting pieces are further arranged at corners of the base, two bottom plates are symmetrically arranged at the upper part of the base, a V-shaped table is fixedly arranged in the middle of the upper part of each bottom plate, and the two V-shaped tables are symmetrically arranged.
The method for precisely grinding the turbine disc blade assembly comprises the steps of precisely measuring the measured assembly by using the device for precisely measuring the turbine disc blade assembly, obtaining the machining amount needing to be ground, positioning by using the top positioning holes at two ends of the positioning shaft in the measured assembly through the cylindrical grinding machine, and grinding the diameter of the turbine blade to the diameter of a standard disc in the standard assembly.
In order to better implement the method of the present invention, further, the specific steps of performing precision measurement on the turbine disk blade assembly are as follows:
s1: two ends of a central shaft in the label aligning component are arranged on a V-shaped table of a supporting base, so that a standard disc in the label aligning component can rotate in a suspended mode;
s2: then, the supporting frames at the two ends of the bridge-type measurer are arranged on the central shaft, the measuring head of the dial indicator is in contact with the standard disc, the dial indicator in the bridge-type measurer is corrected through the outer diameter of the standard disc, and the dial indicator is zeroed;
s3: taking down the corrected bridge type measurer and the calibrated alignment assembly, and placing the measured assembly on a V-shaped table of a supporting base to enable a turbine disc of the measured assembly to rotate in a suspended mode;
s4: and arranging the corrected bridge type measurer on the measured assembly, rotating the turbine disc to enable each turbine blade on the turbine disc to pass through a measuring head at the lower part of the dial indicator, and recording the reading of the dial indicator when each turbine blade passes through the measuring head, wherein the reading is the machining amount of the turbine blade needing to be ground.
Compared with the prior art, the invention has the following advantages and beneficial effects:
(1) according to the turbine blade grinding device, the position relation between the dial indicator and the turbine disc blade is established, and the turbine blade on the turbine disc is precisely measured by using the accurate reading of the dial indicator, so that the accurate grinding process is guaranteed;
(2) the invention realizes zero-setting correction of the dial indicator by utilizing the standard disk in the calibration component, further improves the precision measurement process of the turbine disk blade component, and the standard disk has a plurality of outer diameter standards and can correct and measure the turbine disk components with different outer diameter requirements;
(3) according to the invention, the position structure of the dial indicator is optimized, so that the height of the dial indicator can be adjusted, and the precise measurement of turbine disc assemblies with different sizes is realized;
(4) the invention can overcome the technical problems of low operation precision and larger error of the traditional turbine disc blade assembly measurement, ensures the coaxiality of the turbine disc blade assembly measurement, thereby improving the precision and further realizing the high-precision measurement and grinding of the turbine blade, and has the advantages of simple structure, easy operation and suitability for wide popularization and application.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic isometric view of a southeast isometric view of a targeting process performed in the present invention;
FIG. 2 is a schematic view of a northwest isometric structure of the benchmarking process performed in the present invention
FIG. 3 is a schematic isometric view of a southeast of a turbine disk blade assembly according to the present invention;
FIG. 4 is a schematic northwest isometric view of a turbine disk blade assembly according to the present invention;
FIG. 5 is a perspective view of the support base of the present invention;
FIG. 6 is a perspective view of the targeting module of the present invention;
FIG. 7 is a schematic cross-sectional view of a targeting assembly of the present invention;
FIG. 8 is a perspective view of the bridge type measuring device of the present invention;
FIG. 9 is a schematic cross-sectional view of a bridge type measuring device according to the present invention;
FIG. 10 is a perspective view of the tested module of the present invention;
FIG. 11 is a schematic cross-sectional view of a device under test according to the present invention.
Wherein: 1-supporting base, 11-V-shaped platform, 12-base, 13-corner connecting piece, 14-bottom plate, 2-to mark subassembly, 21-standard dish, 22-center pin, 3-bridge type caliber, 31-crossbeam, 32-support frame, 33-percentage table, 34-measuring stick, 35-measuring shell, 36-spring, 37-locking shaft, 4-measured subassembly, 41-turbine dish, 42-locating shaft, 43-first position sleeve, 44-pressing sleeve, 45-lock nut, 46-gasket, 47-second position sleeve, 48-bush.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, the definitions of "first" and "second" are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly including one or more of such features. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; 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 meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1:
the present embodiment provides a precision measurement apparatus for a turbine disk blade assembly, whose main structure is shown in fig. 1 to 4, and includes a supporting base 1, a targeting assembly 2, a bridge type measurer 3, and a measured assembly 4; the upper part of the supporting base 1 is symmetrically provided with V-shaped platforms 11 for placing the label alignment component 2 or the tested component 4, as shown in FIG. 5; the targeting module 2 comprises a standard disk 21 at the middle part and a central shaft 22 which penetrates through the standard disk 21 and is fixed with the standard disk, as shown in fig. 6 and 7; the bridge type measurer 3 comprises a cross beam 31 in the middle, support frames 32 are fixed at two ends of the cross beam 31, a V-shaped groove matched with the V-shaped table 11 is formed in the bottom of each support frame 32, at least one vertical through hole is formed in the middle of the upper surface of the cross beam 31, a dial indicator 33 is fixedly inserted into each through hole, the head of each dial indicator 33 is arranged on the upper portion of the cross beam 31, and the measuring head of each dial indicator 33 is arranged on the lower portion of the cross beam 31, as shown in fig. 8 and 9; the measured component 4 includes a turbine disk 41 including turbine blades, and a fixing component for fixing the turbine disk 41, as shown in fig. 10 and 11.
Based on this a device for turbine disc blade subassembly precision measurement, the process of carrying out precision measurement to turbine disc blade subassembly is as follows:
s1: now, two ends of a central shaft 22 in the label aligning component 2 are arranged on the V-shaped table 11 of the supporting base 1, so that the standard disc 21 in the label aligning component 2 can rotate in a suspended mode;
s2: then, the supporting frames 32 at the two ends of the bridge-type measurer 3 are placed on the central shaft 22, the measuring heads of the dial indicator 33 are in contact with the standard disc 21, the dial indicator 33 in the bridge-type measurer 3 is corrected through the outer diameter of the standard disc 21, and the dial indicator 33 is zeroed, as shown in fig. 1 and 2;
s3: taking down the corrected bridge type measurer 3 and the calibrated alignment assembly 2, and placing the tested assembly 4 on the V-shaped table 11 of the supporting base 1, so that the turbine disc 41 of the tested assembly 4 can rotate in a suspended manner;
s4: the corrected bridge measuring device 3 is arranged on the measured component 4, the turbine disk 41 is rotated, each turbine blade on the turbine disk 41 passes through the lower measuring head of the dial indicator 33, and the reading of the dial indicator 33 when each turbine blade passes through the measuring head is recorded, wherein the reading is the machining amount of the turbine blade needing to be ground, and the reading is shown in fig. 3 and 4.
Example 2:
in this embodiment, based on the above embodiment, the structure of the target assembly 2 is further defined, as shown in fig. 6 and 7, the outer diameter of the standard disk 21 is divided into three sections, each section has a diameter corresponding to the standard diameter, and tip positioning holes for fixing the center shaft 22 are further provided at two ends of the center shaft. The gauge disk 21 has a plurality of outer diameter gauges that allow for calibration and measurement of turbine disk assemblies having different outer diameter requirements. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.
Example 3:
in this embodiment, on the basis of the above embodiment, the structure of the bridge type measurer 3 is further limited, as shown in fig. 8 and 9, the bridge type measurer 3 further includes a measuring casing 35 covering the lower portion of the dial indicator 33 and fixed to the dial indicator 33, the measuring casing 35 is fixed in the through hole in the middle of the cross beam 31, a measuring rod 34 is disposed inside the measuring casing 35, the top of the measuring rod 34 contacts with a measuring head on the lower portion of the dial indicator, the lower portion of the measuring rod 34 extends out of the measuring casing 35, and a spring 36 for extending the measuring rod 34 out of the measuring casing 35 is further disposed inside the measuring casing 35, so that the measuring rod 34 can reciprocate up and down in the measuring casing 35. The structure of the measuring shell 35 and the measuring rod 34 is additionally arranged, so that damage to the dial indicator 33 is avoided. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.
Example 4:
in this embodiment, the structure of the bridge type measuring device 3 is further limited on the basis of the above embodiments, as shown in fig. 8 and fig. 9, a longitudinal through hole is further formed in a side edge of the cross beam 31 of the bridge type measuring device 3, the longitudinal through hole in the cross beam 31 intersects with the vertical through hole in the cross beam 31, a locking shaft 36 is inserted into the longitudinal through hole in the cross beam 31, and the locking shaft 36 can fix the measuring housing 35 inserted into the vertical through hole in the cross beam 31. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.
Example 5:
in this embodiment, on the basis of the above embodiment, the structure of the measured component 4 is further limited, as shown in fig. 10 and 11, the fixed component in the measured component 4 includes a positioning shaft 42 inserted in the middle of the turbine disc 41, the positioning shaft 42 is sequentially nested from inside to outside with a first positioning sleeve 43 and a pressing sleeve 44, the leftmost end of the positioning shaft 42 is provided with an external thread, and the thread is connected with a locking nut 45, the locking nut 45 enables the pressing sleeve 44 to press the first positioning sleeve 43, so that the first positioning sleeve 43 is fixed to the turbine disc 41, the positioning shaft 42 is further fixed to the turbine disc, and tip positioning holes are further formed in two ends of the positioning shaft 42. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.
Example 6:
in this embodiment, on the basis of the above embodiments, the structure of the measured component 4 is further limited, as shown in fig. 10 and 11, and a gasket 46 is further disposed between the lock nut 45 and the pressing sleeve 44. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.
Example 7:
in this embodiment, the structure of the measured component 4 is further limited on the basis of the above embodiment, as shown in fig. 10 and 11, the right end of the positioning shaft 42 in the measured component 4 is a circular fixing block, a second positioning sleeve 47 is disposed between the circular fixing block and the turbine disk 41, a bushing 48 is disposed between the turbine disk 41 and the positioning shaft 42 inside the second positioning sleeve 47, and tip positioning holes are further disposed at two ends of the positioning shaft 42. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.
Example 8:
in this embodiment, on the basis of the above embodiment, the structure of the supporting base 1 is further defined, as shown in fig. 5, the supporting base 1 includes a "groined-shaped" base 12 formed by a square aluminum profile, corner connectors 13 are further disposed at corners of the base 12, two bottom plates 14 are symmetrically disposed on the upper portion of the base 12, a V-shaped platform 11 is fixedly mounted in the middle above each bottom plate 14, and the two V-shaped platforms 11 are symmetrically disposed. Other parts of this embodiment are the same as those of the above embodiment, and are not described again.
Example 9:
the embodiment provides a method for precisely grinding a turbine disk blade assembly, and the specific process is that the device for precisely measuring a turbine disk blade assembly described in the embodiment is used for precisely measuring a measured assembly 4, so that the machining amount needing to be ground is obtained, a cylindrical grinding machine is used for positioning by using tip positioning holes at two ends of a positioning shaft 42 in the measured assembly 4, and then the diameter of a turbine blade is ground to the diameter of a standard disk 22 in a calibration assembly 2. The specific steps of performing the precision measurement on the turbine disc blade assembly are the same as those in the above embodiments, and are not described again.
It is to be understood that the operation principle and operation of the apparatus structure for precision grinding of turbine disk blade assemblies according to an embodiment of the present invention, such as the dial gauge 33 and the spring 37, are well known in the art and will not be described in detail herein.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. The device for precisely measuring the blade component of the turbine disk is characterized by comprising a supporting base (1), a calibration component (2), a bridge type measurer (3) and a measured component (4);
the upper part of the supporting base (1) is symmetrically provided with a V-shaped platform (11) for placing the alignment component (2) or the tested component (4);
the target aligning component (2) comprises a standard disc (21) in the middle and a central shaft (22) which penetrates through the standard disc (21) and is fixed with the standard disc;
the bridge type measurer (3) comprises a cross beam (31) in the middle, supporting frames (32) are fixed at two ends of the cross beam (31), a V-shaped groove matched with the V-shaped table (11) is formed in the bottom of each supporting frame (32), at least one vertical through hole is formed in the middle of the upper surface of the cross beam (31), a dial indicator (33) is fixedly inserted into each through hole, the head of the dial indicator (33) is arranged on the upper portion of the cross beam (31), and the measuring head of the dial indicator (33) is arranged on the lower portion of the cross beam (31);
the tested component (4) comprises a turbine disc (41) containing turbine blades and a fixing component for fixing the turbine disc (41).
2. The device for the precision measurement of the blade assembly of the turbine disk according to the claim 1 is characterized in that the outer diameter of the standard disk (21) is divided into three sections, the diameter of each section corresponds to the size of the standard diameter, and the two ends of the central shaft (22) are also provided with tip positioning holes for fixing the central shaft.
3. The device for precisely measuring the blade assembly of the turbine disk blade as recited in claim 2, wherein the bridge type measurer (3) further comprises a measuring casing (35) covering the lower part of the dial indicator (33) and fixed with the dial indicator (33), the measuring casing (35) is fixed in a through hole in the middle of the cross beam (31), a measuring rod (34) is arranged inside the measuring casing (35), the top of the measuring rod (34) is in contact with a measuring head at the lower part of the dial indicator, the lower part of the measuring rod (34) extends out of the measuring casing (35), and a spring (36) which enables the measuring rod (34) to extend out of the measuring casing (35) is further arranged inside the measuring casing (35), so that the measuring rod (34) can reciprocate up and down inside the measuring casing (35).
4. The device for precisely measuring the blade assembly of the turbine disc as claimed in claim 3, wherein the bridge type measurer (3) is further provided with a longitudinal through hole at the side of the cross beam (31), the longitudinal through hole in the cross beam (31) is intersected with the vertical through hole in the cross beam (31), and a locking shaft (37) is inserted into the longitudinal through hole in the cross beam (31), and the locking shaft (37) can fix the measuring shell (35) inserted into the vertical through hole in the cross beam (31).
5. The device for precisely measuring the blade assembly of the turbine disk according to any one of claims 1 to 4, wherein a fixing assembly of the tested assembly (4) comprises a positioning shaft (42) inserted in the middle of the turbine disk (41), the positioning shaft (42) is sequentially nested with a first positioning sleeve (43) and a pressing sleeve (44) from inside to outside, the leftmost end of the positioning shaft (42) is provided with an external thread, the thread is connected with a locking nut (45), the locking nut (45) enables the pressing sleeve (44) to press the first positioning sleeve (43), the first positioning sleeve (43) and the turbine disk (41) are fixed, the positioning shaft (42) and the turbine disk are further fixed, and tip positioning holes are further formed in two ends of the positioning shaft (42).
6. An apparatus for precision measurement of a turbine disc blade assembly according to any of the claims 5, characterized in that a washer (46) is further provided between the lock nut (45) and the pressing sleeve (44).
7. The device for precisely measuring the blade assembly of the turbine disk according to any one of claims 1 to 4, wherein a circular fixing block is arranged at the right end of the positioning shaft (42) in the tested assembly (4), a second positioning sleeve (47) is arranged between the circular fixing block and the turbine disk (41), a bushing (48) is arranged between the turbine disk (41) and the positioning shaft (42) in the second positioning sleeve (47), and tip positioning holes are further arranged at two ends of the positioning shaft (42).
8. The device for precisely measuring the blade assembly of the turbine disc according to any one of claims 1 to 4, wherein the supporting base (1) comprises a # -shaped base (12) formed by a square aluminum profile, corner connecting pieces (13) are further arranged at corners of the base (12), two bottom plates (14) are symmetrically arranged at the upper part of the base (12), a V-shaped platform (11) is fixedly arranged at the middle part above each bottom plate (14), and the two V-shaped platforms (11) are symmetrically arranged.
9. A method for precisely grinding a turbine disc blade component, which is characterized in that a device for precisely measuring a turbine disc blade component according to any one of claims 1 to 8 is used for precisely measuring a component to be measured (4), so as to obtain the machining amount to be ground, the machining amount is positioned by using tip positioning holes at two ends of a positioning shaft (42) in the component to be measured (4) through an external grinding machine, and then the diameter of a turbine blade is ground to the diameter of a standard disc (22) in a calibration component (2).
10. The method for precision grinding of a turbine disk blade assembly of claim 9, wherein the steps of precisely measuring the turbine disk blade assembly are as follows:
s1: two ends of a central shaft (22) in the label aligning component (2) are arranged on a V-shaped table (11) of a supporting base (1) so that a standard disc (21) in the label aligning component (2) can rotate in a suspended mode;
s2: then, the supporting frames (32) at the two ends of the bridge type measurer (3) are arranged on the central shaft (22), the measuring head of the dial indicator (33) is in contact with the standard disc (21), the dial indicator (33) in the bridge type measurer (3) is corrected through the outer diameter of the standard disc (21), and the dial indicator (33) is zeroed;
s3: the corrected bridge type measurer (3) and the calibrated alignment assembly (2) are taken down, and the tested assembly (4) is placed on the V-shaped table (11) of the supporting base (1), so that the turbine disc (41) of the tested assembly (4) can rotate in a suspended mode;
s4: the corrected bridge type measurer (3) is arranged on a measured assembly (4), a turbine disk (41) is rotated, each turbine blade on the turbine disk (41) passes through a measuring head at the lower part of a dial indicator (33), and the reading of the dial indicator (33) when each turbine blade passes through the measuring head is recorded, wherein the reading is the machining amount of the turbine blade needing to be ground.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210197985.6A CN114485327A (en) | 2022-03-02 | 2022-03-02 | Device for precisely measuring turbine disc blade assembly and grinding method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210197985.6A CN114485327A (en) | 2022-03-02 | 2022-03-02 | Device for precisely measuring turbine disc blade assembly and grinding method |
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| CN114485327A true CN114485327A (en) | 2022-05-13 |
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| CN202210197985.6A Pending CN114485327A (en) | 2022-03-02 | 2022-03-02 | Device for precisely measuring turbine disc blade assembly and grinding method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115094215A (en) * | 2022-06-24 | 2022-09-23 | 中国航发北京航空材料研究院 | Shot type ultrasonic impact strengthening device for turbine disc mortise and using method thereof |
| CN115284130A (en) * | 2022-07-04 | 2022-11-04 | 青岛中科国晟动力科技有限公司 | Rotor blade tip grinding method |
-
2022
- 2022-03-02 CN CN202210197985.6A patent/CN114485327A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115094215A (en) * | 2022-06-24 | 2022-09-23 | 中国航发北京航空材料研究院 | Shot type ultrasonic impact strengthening device for turbine disc mortise and using method thereof |
| CN115284130A (en) * | 2022-07-04 | 2022-11-04 | 青岛中科国晟动力科技有限公司 | Rotor blade tip grinding method |
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