CN113211339B - A frock clamp for horizontal balanced of aviation turboshaft engine single-disk - Google Patents
A frock clamp for horizontal balanced of aviation turboshaft engine single-disk Download PDFInfo
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- CN113211339B CN113211339B CN202110293094.6A CN202110293094A CN113211339B CN 113211339 B CN113211339 B CN 113211339B CN 202110293094 A CN202110293094 A CN 202110293094A CN 113211339 B CN113211339 B CN 113211339B
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- core rod
- positioning
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- positioning disc
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/02—Details of balancing machines or devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Testing Of Balance (AREA)
Abstract
The invention discloses a tool clamp for single-disc horizontal balance of an aircraft turboshaft engine, belonging to the technical field of maintenance and balance of an aircraft engine compressor rotor. This set of frock clamp has realized the balanced detection of rotor single disc on horizontal balancing machine to clamping, dismantlement convenient and fast, this frock structure does not polish with the rotor and gets rid of the regional production of material and interfere, but direct normal position adjustment unbalance amount, need not divide repeatedly, has promoted work efficiency.
Description
Technical Field
The invention relates to the technical field of maintenance and balance of an aircraft engine compressor rotor, in particular to a tool clamp for single-disc horizontal balance of an aircraft turboshaft engine.
Background
Before assembling a compressor of a certain type of aero-engine, five single disks of a first-stage rotor to a fourth-stage rotor and a centrifugal impeller of the compressor need to be vertically balanced. The vertical balance needs to use a special vertical balance machine, the vertical balance machine has a more complex structure compared with a horizontal balance machine, and the investment and the utilization rate of equipment are not high due to the independent configuration of the equipment. And need polish according to the measuring condition and remove the material on the base body in balanced testing process, inconvenient operation on vertical balancing machine. The existing horizontal balancing machine is simple in structure and convenient to detect and polish, and if the horizontal balancing machine can be used for detecting an engine single disc through certain transformation, the equipment utilization rate of the existing production line is improved, the task elasticity of the production line is increased, and materials are easily polished and removed on a base body.
Disclosure of Invention
In order to overcome the defects that the detection cost is high, materials are not easy to polish and the like caused by the detection of the conventional engine rotor blade on a vertical balancing machine, the invention aims to solve the technical problems that: the provided tool clamp can be used for detecting the horizontal balancing machine by using a single disc of the aviation turboshaft engine.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a work fixture for horizontal balancing of a single disk of an aviation turboshaft engine,
the device comprises a first clamp, a second clamp, a third clamp and a fourth clamp which are respectively used for mounting a first-stage rotor, a second-stage rotor, a third-stage rotor and a centrifugal impeller of an engine;
the first clamp comprises a first core rod and a first positioning disc fixed on the first core rod, and a first bolt and a first nut are inserted into the first positioning disc;
the second fixture comprises a second core rod and a second positioning disc fixed on the second core rod, and a transition shaft shoulder is arranged on one side, close to the positioning end face of the second positioning disc, of the second core rod;
the third fixture comprises a third core rod and a third positioning disc fixed on the third core rod, and a third bolt and a third nut are inserted into the third positioning disc;
the fourth fixture comprises a fourth core rod and a fourth positioning disc fixed on the fourth core rod, a shaft sleeve in sliding connection with the fourth core rod is arranged at one end of the fourth core rod, an auxiliary positioning disc is arranged at one end, close to the fourth positioning disc, of the shaft sleeve, and a fourth bolt and a fourth nut are arranged between the fourth positioning disc and the auxiliary positioning disc in an inserting mode.
Furthermore, two ends of the first core rod, the second core rod, the third core rod and the fourth core rod are provided with central holes with cone protectors.
Further, the radial run-out tolerance of the first core rod, the second core rod, the third core rod and the fourth core rod is not more than 0.02, and the surface roughness is not more than 0.4.
Further, the installation positions of the first positioning disc, the second positioning disc, the third positioning disc and the fourth positioning disc ensure that the centers of gravity of the first-stage rotor, the second-stage rotor, the third-stage rotor and the centrifugal impeller are respectively located at the central positions of the first core rod, the second core rod, the third core rod and the fourth core rod.
Furthermore, the circumference of one side of the positioning end face on the first positioning disk, the third positioning disk and the fourth positioning disk is provided with a step face, and the radial circle run-out tolerance of the step face and the positioning end face is not more than 0.02.
Furthermore, the first positioning disc is provided with at least four first bolts and first nuts which are arranged around the axis of the first core rod in a central symmetry manner.
Furthermore, at least two third bolts and third nuts which are arranged around the axis of the third mandrel in a centrosymmetric manner are arranged on the third positioning disc.
Furthermore, a third ejection bolt in threaded connection with the third positioning plate is further arranged on the third positioning plate, and the tail of the third ejection bolt faces one side of the positioning end face of the third positioning plate.
Furthermore, at least two fourth bolts and fourth nuts which are symmetrically arranged around the axis of the fourth mandrel are arranged between the fourth positioning disc and the auxiliary positioning disc.
Furthermore, fourth ejection bolts in threaded connection with the fourth positioning plate and the auxiliary positioning plate are arranged on the fourth positioning plate and the auxiliary positioning plate, and tail portions of the fourth ejection bolts face one side of the positioning end face of the positioning plate where the fourth ejection bolts are located.
The invention has the beneficial effects that: the set of tool clamp can be used for positioning and switching the rotor single disc, so that the balance detection of the rotor single disc on a horizontal balancing machine is realized, the clamping and the dismounting are convenient and fast, meanwhile, the tool structure does not interfere with a material removing area of the rotor in a grinding manner, the unbalance amount can be directly adjusted in situ, repeated split charging is not needed, and the working efficiency is improved.
Drawings
FIG. 1 is a schematic view of a first clamp structure according to the present invention.
Fig. 2 is a schematic view of a second clamp structure of the present invention.
FIG. 3 is a schematic view of a third clamp structure according to the present invention.
Fig. 4 is a schematic view of a fourth clamp structure according to the present invention.
The numbers marked in the figure are 1-first clamp, 2-second clamp, 3-third clamp, 4-fourth clamp, 11-first mandrel, 12-first positioning disc, 13-first bolt, 14-first nut, 21-second mandrel, 22-second positioning disc, 23-transition shoulder, 31-third mandrel, 32-third positioning disc, 33-third bolt, 34-third nut, 35-third ejector bolt, 41-fourth mandrel, 42-fourth positioning disc, 43-shaft sleeve, 44-auxiliary positioning disc, 45-fourth bolt, 46-fourth nut, 47-fourth ejector bolt.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1-4, the single-disc horizontal balancing tool clamp for the aviation turboshaft engine comprises a first clamp 1, a second clamp 2, a third clamp 3 and a fourth clamp 4 which are respectively used for installing a first-stage rotor, a second-stage rotor, a third-stage rotor and a centrifugal impeller of the engine;
the first clamp 1 comprises a first core rod 11 and a first positioning disc 12 fixed on the first core rod 11, wherein a first bolt 13 and a first nut 14 are inserted into the first positioning disc 12;
the second fixture 2 comprises a second core rod 21 and a second positioning disc 22 fixed on the second core rod 21, and a transition shaft shoulder 23 is arranged on one side of the second core rod 21 close to the positioning end face of the second positioning disc 22;
the third fixture 3 comprises a third core rod 31 and a third positioning disc 32 fixed on the third core rod 31, and a third bolt 33 and a third nut 34 are inserted and arranged on the third positioning disc 32;
the fourth fixture 4 includes a fourth core rod 41 and a fourth positioning disc 42 fixed on the fourth core rod 41, a shaft sleeve 43 slidably connected to the fourth core rod 41 is disposed at one end of the fourth core rod 41, an auxiliary positioning disc 44 is disposed at one end of the shaft sleeve 43 close to the fourth positioning disc 42, and a fourth bolt 45 and a fourth nut 46 are inserted between the fourth positioning disc 42 and the auxiliary positioning disc 44.
For 5 products of the engine needing vertical balance, the residual unbalance is required to be controlled within a specific range at the rotating speed of not less than 1000rpm, wherein the first-stage rotor to the third-stage rotor of the gas compressor are in single-side static balance, and the centrifugal impeller and the fourth-stage rotor of the gas compressor are in double-side dynamic balance. Adopt four sets of anchor clamps that this application provided, can fix a position the switching to one-level rotor, two level four rotors, three-level rotor and centrifugal impeller respectively, then use it for carry out the balance detection on the horizontal balancing machine.
In the specific detection, the method comprises the following steps:
1. establishing a single-disc digital model of a compressor rotor, and analyzing a balance risk point;
2. specific parameters of a balancing device are formulated according to a single-disc balance supporting mode of a compressor rotor, a connection mode of a tool and a rotor, a driving mode, a driving position, a balance swing frame type and the like;
3. the balance device is subjected to simulation work analysis, so that interference with a polishing removal material is avoided, and the working efficiency is ensured;
4. heating or cooling the compressor rotor, penetrating the compressor rotor into a core rod of a corresponding clamp, and contacting the compressor rotor with a positioning disc, wherein the core rod and the rotor are positioned and installed in an interference fit manner;
5. for the first-stage rotor and the third-stage rotor, after the first-stage rotor and the third-stage rotor are installed, the corresponding first bolt 13 and the third bolt 33 need to be screwed down to assist in fixing the rotors; the second-stage and fourth-stage rotors need to be provided with transition shaft shoulders 23 to realize stable contact between the rotors and the core rods due to special axial sections of the rotors; for the centrifugal impeller, after one surface of the centrifugal impeller is stably contacted with the fourth positioning disc 42, a shaft sleeve 43 is penetrated on the fourth core rod 41, and the shaft sleeve 43 is tightened by using a fourth bolt 45, so that the auxiliary positioning disc 44 is tightly pressed against the other surface of the centrifugal impeller;
6. placing a tool clamp provided with a compressor rotor on a horizontal balancing machine for balancing;
7. and according to the detection condition, carrying out in-situ grinding by using a pneumatic grinding head, removing the material adjustment unbalance amount in the specified area until the balance is qualified, and finally taking down the rotor.
The tool clamp has the following preferred scheme:
for the core rod, because the core rod is to be placed on a horizontal balancing machine for detection, central holes with protecting cones are arranged at two ends of the first core rod 11, the second core rod 21, the third core rod 31 and the fourth core rod 41, so that the positioning and the installation are convenient. Since the precision of the balance detection is high, and the precision of the rotor may be affected by the error of the tooling fixture, the radial runout tolerance of the first core rod 11, the second core rod 21, the third core rod 31 and the fourth core rod 41 should be not greater than 0.02. To facilitate rotor assembly, the surface roughness of each core rod should not be greater than 0.4.
For the positioning disc, in order to ensure that the tool and the rotor rotate stably on the horizontal balancing machine, the mounting positions of the first positioning disc 12, the second positioning disc 22, the third positioning disc 32 and the fourth positioning disc 42 should ensure that the centers of gravity of the first-stage rotor, the second-stage rotor, the third-stage rotor and the centrifugal impeller are respectively located at the central positions of the first mandrel 11, the second mandrel 21, the third mandrel 31 and the fourth mandrel 41. Similarly, in order to facilitate positioning and installation and ensure the precision of the tool, step surfaces are arranged on the circumferential edges on one side of the positioning end surfaces on the first positioning disk 12, the third positioning disk 32 and the fourth positioning disk 42, and the radial circular runout tolerance of the step surfaces and the positioning end surfaces is not more than 0.02.
For the auxiliary positioning structure, the main function is auxiliary limiting function, and the condition of accidental loosening in the high-speed rotation process is avoided. Specifically, at least four first bolts 13 and first nuts 14 which are arranged around the axis of the first core rod in a centrosymmetric manner are arranged on the first positioning disc 12; the third positioning disc 32 is provided with at least two third bolts 33 and third nuts 34 which are arranged around the axis of the third core rod 31 in a centrosymmetric manner; at least two fourth bolts 45 and fourth nuts 46 which are arranged around the axis of the fourth core rod 41 in a central symmetry manner are arranged between the fourth positioning disc 42 and the auxiliary positioning disc 44. The positions and the number of the first bolt 13, the third bolt 33 and the fourth bolt 45 are mainly designed according to the structure of each rotor, so that the bolts can penetrate through gaps of the rotors, and meanwhile, the grinding of materials is not influenced as much as possible.
Further, in order to facilitate the disassembly of the detected rotor, a third ejector bolt 35 in threaded connection with the third positioning disk 32 is further arranged on the third positioning disk 32, and the tail of the third ejector bolt 35 faces one side of the positioning end face of the third positioning disk 32; and fourth ejection bolts 47 in threaded connection with the fourth positioning plate 42 and the auxiliary positioning plate 44 are arranged on the fourth positioning plate and the auxiliary positioning plate 44, and the tail parts of the fourth ejection bolts 47 face one side of the positioning end faces of the positioning plates where the fourth ejection bolts are respectively arranged. After the detection is finished, the rotor can be ejected out of the core rod by rotating the ejection bolt, so that the stable disassembly of the rotor is realized.
The four sets of tool fixtures are arranged, so that the problem of installation of the single-disc vertical balance-to-horizontal balance switching of the compressor rotor is solved, and the flexibility of field production tasks can be improved on the premise of ensuring the product quality. Meanwhile, the tool structure does not interfere with a material removing area of the rotor in a grinding mode, unbalance can be directly adjusted in situ, repeated split charging is not needed, and production efficiency is improved.
Claims (8)
1. A frock clamp for horizontal balanced of aviation turboshaft engine single-disk, characterized by:
the device comprises a first clamp (1), a second clamp (2), a third clamp (3) and a fourth clamp (4) which are respectively used for mounting a first-stage rotor, a second-stage rotor, a third-stage rotor and a centrifugal impeller of an engine;
the first clamp (1) comprises a first core rod (11) and a first positioning disc (12) fixed on the first core rod (11), and a first bolt (13) and a first nut (14) are inserted into the first positioning disc (12);
the second clamp (2) comprises a second core rod (21) and a second positioning disc (22) fixed on the second core rod (21), and a transitional shaft shoulder (23) is arranged on one side, close to the positioning end face of the second positioning disc (22), of the second core rod (21);
the third clamp (3) comprises a third core rod (31) and a third positioning disc (32) fixed on the third core rod (31), and a third bolt (33) and a third nut (34) are inserted into the third positioning disc (32);
the fourth fixture (4) comprises a fourth core rod (41) and a fourth positioning disc (42) fixed on the fourth core rod (41), one end of the fourth core rod (41) is provided with a shaft sleeve (43) in sliding connection with the fourth core rod (41), one end, close to the fourth positioning disc (42), of the shaft sleeve (43) is provided with an auxiliary positioning disc (44), and a fourth bolt (45) and a fourth nut (46) are arranged between the fourth positioning disc (42) and the auxiliary positioning disc (44) in a penetrating mode;
the two ends of the first core rod (11), the second core rod (21), the third core rod (31) and the fourth core rod (41) are provided with central holes with guard cones, the radial circular runout tolerance of the first core rod (11), the second core rod (21), the third core rod (31) and the fourth core rod (41) is not more than 0.02, and the surface roughness is not more than 0.4.
2. The tooling clamp for the single-disc horizontal balance of the aviation turboshaft engine according to claim 1, characterized in that: the mounting positions of the first positioning disc (12), the second positioning disc (22), the third positioning disc (32) and the fourth positioning disc (42) ensure that the gravity centers of the first-stage rotor, the second-stage rotor, the third-stage rotor and the centrifugal impeller are respectively positioned at the central positions of the first mandril (11), the second mandril (21), the third mandril (31) and the fourth mandril (41).
3. The tooling clamp for horizontal balancing of the single disk of the aviation turboshaft engine according to claim 2, characterized in that: the circumference of location terminal surface one side on first positioning disk (12), third positioning disk (32) and fourth positioning disk (42) all is equipped with the step face, the radial circle of step face and location terminal surface tolerance of beating is all not more than 0.02.
4. The tooling clamp for horizontal balancing of the single disk of the aviation turboshaft engine according to claim 2, characterized in that: the first positioning disc (12) is provided with at least four first bolts (13) and first nuts (14) which are arranged around the axis of the first mandrel (11) in a centrosymmetric manner.
5. The tooling clamp for horizontal balancing of the single disk of the aviation turboshaft engine according to claim 2, characterized in that: and at least two third bolts (33) and third nuts (34) which are arranged around the axis of the third core rod (31) in a central symmetry manner are arranged on the third positioning plate (32).
6. The tooling clamp for horizontal balancing of the single disk of the aviation turboshaft engine according to claim 5, characterized in that: and a third ejection bolt (35) in threaded connection with the third positioning plate (32) is further arranged on the third positioning plate (32), and the tail part of the third ejection bolt (35) faces one side of the positioning end face of the third positioning plate (32).
7. The tooling clamp for the single-disc horizontal balance of the aviation turboshaft engine according to claim 2, characterized in that: at least two fourth bolts (45) and fourth nuts (46) which are arranged around the axis of the fourth core rod (41) in a central symmetry manner are arranged between the fourth positioning disk (42) and the auxiliary positioning disk (44).
8. The tooling clamp for horizontal balancing of the single disk of the aviation turboshaft engine according to claim 7, characterized in that: and fourth ejection bolts (47) in threaded connection with the fourth positioning plate (42) and the auxiliary positioning plate (44) are arranged on the fourth positioning plate and the auxiliary positioning plate, and the tail parts of the fourth ejection bolts (47) face one sides of the positioning end surfaces of the positioning plates where the fourth ejection bolts are respectively arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110293094.6A CN113211339B (en) | 2021-03-18 | 2021-03-18 | A frock clamp for horizontal balanced of aviation turboshaft engine single-disk |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110293094.6A CN113211339B (en) | 2021-03-18 | 2021-03-18 | A frock clamp for horizontal balanced of aviation turboshaft engine single-disk |
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| Publication Number | Publication Date |
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| CN113211339A CN113211339A (en) | 2021-08-06 |
| CN113211339B true CN113211339B (en) | 2023-03-31 |
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| CN202110293094.6A Active CN113211339B (en) | 2021-03-18 | 2021-03-18 | A frock clamp for horizontal balanced of aviation turboshaft engine single-disk |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114161347B (en) * | 2021-10-20 | 2023-09-15 | 中国航发四川燃气涡轮研究院 | High-pressure compressor rotor centering fixture |
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