CN111256909A - Aero-engine oil-gas separator rotor balance clamp - Google Patents
Aero-engine oil-gas separator rotor balance clamp Download PDFInfo
- Publication number
- CN111256909A CN111256909A CN202010166522.4A CN202010166522A CN111256909A CN 111256909 A CN111256909 A CN 111256909A CN 202010166522 A CN202010166522 A CN 202010166522A CN 111256909 A CN111256909 A CN 111256909A
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- CN
- China
- Prior art keywords
- balance
- rotor
- gas separator
- aero
- balanced
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
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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
- G01M1/12—Static balancing; Determining position of centre of gravity
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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
-
- 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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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Centrifugal Separators (AREA)
Abstract
The scheme discloses an aeroengine oil and gas separator rotor balance clamp in the field of aeroengines, which comprises a balance thread sleeve, a circular table block, a cylindrical block and a base, wherein two supporting rods are arranged on the base, two balancing shafts are detachably connected to the supporting rods, the balancing shafts penetrate through the circular table block and the cylindrical block and are fixedly connected with the circular table block and the cylindrical block, one end with the smaller diameter of the circular table block is fixedly connected with the cylindrical block, and the balancing shafts penetrate through the balance thread sleeve. The balance clamp in the scheme can quickly carry out static balance inspection on the rotor.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to a balance clamp for an aero-engine oil-gas separator rotor.
Background
Aeroengine oil and gas separator is in the use, the fish tail phenomenon can exist in the rotor subassembly, consequently when overhauing the engine, need polish the processing to the rotor, the inspection of can no longer balancing after polishing of current rotor usually, will influence the use and the quality of follow-up rotor like this, in order to guarantee the use of engine, the rotor after polishing need carry out the static balance inspection, and the use of putting into operation again, because rotor structure is special, does not have the professional equipment that carries out the static balance inspection to the rotor now.
Disclosure of Invention
The invention aims to provide a balancing clamp for an aero-engine oil-gas separator rotor, which solves the problem that static balance inspection is inconvenient to carry out after the existing rotor is repaired.
The balanced anchor clamps of aircraft engine oil and gas separator rotor in this scheme, including balanced silk covering, round platform piece, cylinder piece and base, be equipped with two spinal branch poles on the base, two can dismantle on the branch and be connected with balanced axle, balanced axle runs through round platform piece and cylinder piece, and balanced axle and round platform piece and cylinder piece fixed connection, the less one end of round platform piece diameter and cylinder piece fixed connection, balanced axle still runs through balanced silk covering.
The working principle of the scheme is as follows: when the balance screw is used, the balance shaft is taken down from the supporting rods, the balance screw sleeve is taken down from the balance shaft, the rotor to be maintained is sleeved on the balance shaft, the end with the smaller diameter of the rotor is close to the end with the larger diameter of the circular truncated cone block, the balance screw sleeve is sleeved on the rotor, the rotor is fixed between the balance screw sleeve and the circular truncated cone block, the balance shaft is connected with the two supporting rods, the rotor is divided into four sides, and at the moment, the rotor does not rotate, namely, the balance of the other three sides below the rotor is realized; and then the balance screw sleeve is detached from the rotor, the rotor is rotated by ninety degrees, and then the balance screw sleeve is connected with the rotor, so that the rotor does not rotate, namely, the four sides are balanced. Whether device in this scheme of use can the spot test rotor balanced after polishing.
Furthermore, the balance screw sleeve comprises a circular ring and a cylindrical ring, and one end with the larger diameter of the cylindrical ring is fixedly connected with the circular ring.
Further, the balance screw sleeve and the balance shaft are made of light material supports. During measurement, the problem that the balance wire sleeve and the balance shaft have certain weight to cause inaccurate measurement can be avoided.
Furthermore, U-shaped grooves are formed in the upper ends of the two support rods. The balance shaft can be conveniently taken by the arrangement.
Drawings
FIG. 1 is a schematic structural diagram of a rotor balance clamp for an oil-gas separator of an aircraft engine according to the invention;
FIG. 2 is a schematic structural view of the balance shaft of FIG. 1;
fig. 3 is a schematic structural view of the balance silk sleeve in fig. 1.
Detailed Description
The following is further detailed by the specific embodiments:
reference numerals in the drawings of the specification include: the balance mechanism comprises a base 1, a support rod 2, a balance shaft 3, a balance screw sleeve 4, a rotor 5, a circular truncated cone block 6, a cylindrical block 7, a circular ring 8 and a cylindrical ring 9.
The embodiment is substantially as shown in figures 1, 2 and 3 of the accompanying drawings: a balance clamp for an aero-engine oil-gas separator rotor 5 comprises a balance shaft 3, a balance screw sleeve 4, a circular truncated cone block 6, a cylindrical block 7 and a base 1, wherein the balance shaft 3 and the balance screw sleeve 4 are made of light materials, two supporting rods 2 are arranged on the base 1, U-shaped grooves are formed in the upper ends of the two supporting rods 2, the balance shaft 3 is placed in the U-shaped grooves of the supporting rods 2, the balance shaft 3 penetrates through the circular truncated cone block 6 and the cylindrical block 7, the balance shaft 3 is fixedly connected with the circular truncated cone block 6 and the cylindrical block 7, the end, with the smaller diameter, of the circular truncated cone block 6 is fixedly connected with the cylindrical block 7, the balance shaft 3 further penetrates through the balance screw sleeve 4, the balance screw sleeve 4 comprises a circular ring 8 and a cylindrical ring 9, and the end, with the larger; the balance screw sleeve 4 and the balance shaft 3 are made of light material supports.
When the balance screw sleeve is used, the balance shaft 3 is taken down from the supporting rods 2, the balance screw sleeve 4 is taken down from the balance shaft 3, the rotor 5 to be maintained is sleeved on the balance shaft 3, the end, with the smaller diameter, of the rotor 5 is close to the end, with the larger diameter, of the circular truncated cone block 6, the balance screw sleeve 4 is sleeved on the rotor 5, the rotor 5 is fixed between the balance screw sleeve 4 and the circular truncated cone block 6, the balance shaft 3 is connected with the two supporting rods 2, the rotor 5 is divided into four sides, and at the moment, the rotor 5 does not rotate, namely, the balance is carried out on the three sides; then the balance screw sleeve 4 and the rotor 5 are disassembled, the rotor 5 is rotated for ninety degrees, then the balance screw sleeve 4 is connected with the rotor 5, the rotor 5 does not rotate, and the four sides are balanced. Whether device in this scheme of use can determine rotor 5 after polishing fast whether balanced.
The structure is sized according to the following figures.
The foregoing is merely an example of the present invention and common general knowledge of known specific structures and features of the embodiments is not described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (4)
1. The utility model provides an aeroengine oil and gas separator rotor balance anchor clamps which characterized in that: including balanced silk covering, round platform piece, cylinder piece and base, be equipped with two spinal branch poles on the base, two can dismantle on the branch and be connected with balanced axle, balanced axle runs through round platform piece and cylinder piece, and balanced axle and round platform piece and cylinder piece fixed connection, the less one end and the cylinder piece fixed connection of round platform piece diameter, balanced axle still runs through balanced silk covering.
2. The aero-engine oil and gas separator rotor balancing fixture as claimed in claim 1, wherein: the balance screw sleeve comprises a circular ring and a cylindrical ring, and one end of the cylindrical ring with the larger diameter is fixedly connected with the circular ring.
3. The aero-engine oil and gas separator rotor balancing fixture as claimed in claim 2, wherein: the balance screw sleeve and the balance shaft are made of light material supports.
4. The aero-engine oil and gas separator rotor balancing fixture as claimed in claim 3, wherein: and U-shaped grooves are formed at the upper ends of the two supporting rods.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010166522.4A CN111256909A (en) | 2020-03-11 | 2020-03-11 | Aero-engine oil-gas separator rotor balance clamp |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010166522.4A CN111256909A (en) | 2020-03-11 | 2020-03-11 | Aero-engine oil-gas separator rotor balance clamp |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111256909A true CN111256909A (en) | 2020-06-09 |
Family
ID=70951468
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010166522.4A Pending CN111256909A (en) | 2020-03-11 | 2020-03-11 | Aero-engine oil-gas separator rotor balance clamp |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111256909A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4302975A (en) * | 1979-12-18 | 1981-12-01 | Toyota Jidosha Kogyo Kabushiki Kaisha | Device for holding a rotor body in a balance testor |
| CN201311336Y (en) * | 2008-10-30 | 2009-09-16 | 台州宇硕自络槽筒有限公司 | Central shaft for checking dynamic balance of grooved drum |
| CN104006921A (en) * | 2014-05-22 | 2014-08-27 | 郑州磨料磨具磨削研究所有限公司 | Balance shaft for dynamic balance or static balance and fixing method thereof |
| CN104034479A (en) * | 2014-06-05 | 2014-09-10 | 荣成市华东锻压机床有限公司 | Press flywheel static balance testing device |
| CN203981345U (en) * | 2014-06-14 | 2014-12-03 | 南车戚墅堰机车有限公司 | Locomotive wheel static equilibrium assembling test unit |
| CN107328523A (en) * | 2017-09-04 | 2017-11-07 | 中国航发南方工业有限公司 | Turbine rotor balancing test fixture and balancing rig |
-
2020
- 2020-03-11 CN CN202010166522.4A patent/CN111256909A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4302975A (en) * | 1979-12-18 | 1981-12-01 | Toyota Jidosha Kogyo Kabushiki Kaisha | Device for holding a rotor body in a balance testor |
| CN201311336Y (en) * | 2008-10-30 | 2009-09-16 | 台州宇硕自络槽筒有限公司 | Central shaft for checking dynamic balance of grooved drum |
| CN104006921A (en) * | 2014-05-22 | 2014-08-27 | 郑州磨料磨具磨削研究所有限公司 | Balance shaft for dynamic balance or static balance and fixing method thereof |
| CN104034479A (en) * | 2014-06-05 | 2014-09-10 | 荣成市华东锻压机床有限公司 | Press flywheel static balance testing device |
| CN203981345U (en) * | 2014-06-14 | 2014-12-03 | 南车戚墅堰机车有限公司 | Locomotive wheel static equilibrium assembling test unit |
| CN107328523A (en) * | 2017-09-04 | 2017-11-07 | 中国航发南方工业有限公司 | Turbine rotor balancing test fixture and balancing rig |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200609 |
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| RJ01 | Rejection of invention patent application after publication |