CN206360724U - Aeroengine rotor counterweight block structure - Google Patents
Aeroengine rotor counterweight block structure Download PDFInfo
- Publication number
- CN206360724U CN206360724U CN201621372536.7U CN201621372536U CN206360724U CN 206360724 U CN206360724 U CN 206360724U CN 201621372536 U CN201621372536 U CN 201621372536U CN 206360724 U CN206360724 U CN 206360724U
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- China
- Prior art keywords
- balance weight
- disk body
- counterweight block
- balance
- block structure
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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.)
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Abstract
A kind of aeroengine rotor counterweight block structure, balance weight is L-shaped, thereon processing bolt hole, at the turbine disk or compressor disc disk body axle journal bolt connection, and the balance weight removable material adjusts quality.Balance weight sets and removes positions of materials, is easy to accurately adjust weight.Balance weight L-shaped short side is arc, and its end face is adjacent to disk body upper bolt hole flange arc edge, the centrifugal force produced in balance weight rotation process is undertaken by disk body flange, prevent bolt because being destroyed by shearing force.Beneficial effect：A) it is simple in construction, installed using disk body assembling with bolt hole, it is not necessary to the design and installation hole on disk body in addition；B) counterweight block assembly technology is simple, reduces balance difficulty；C) it is easy to use, change balance weight convenient and swift.
Description
Technical field:
Aeroengine rotor counterweight block structure.
Background technology
In order to reduce vibration in the course of the work, aeroengine rotor, which is typically necessary in assembling process, enters action
Balance.At present, the dynamic balance treatment both at home and abroad to rotor is generally that after being measured by balancing machine, material is directly removed on disk body
Or balancing weight is installed on disk body and portion of material is removed on balancing weight, so that accurate balance weight is obtained, it is final to protect
Demonstrate,prove the dynamic equilibrium of rotor.Material is directly removed on disk body, although technique is simple, easily balance, but removed past after material
Toward causing certain influence on the intensity of disk body, therefore stricter to the requirement for removing material, the depth, circumferentially distributed to removing material
And the surface roughness gone after material has carried out strict limitation.In addition repeatedly after balance, disk body because material is removed it is excessive without
It can continue to remove material, then can not reach that balance is required.Common counterweight block mode is taken to be balanced, in order to ensure balancing weight
Installation, it is necessary to increase open-celled structure on compressor or turbine disk wheel rim, so as to reduce the intensity of disk body, and opening
Stress concentration is easily produced at hole, potential safety hazard is caused, the life-span of disk body is reduced.
The content of the invention
The technical problem to be solved is simple in construction there is provided a kind of aeroengine rotor counterweight block structure, to disk body
Intensity and aging effects are smaller.
Technical scheme, a kind of aeroengine rotor counterweight block structure, balance weight is L-shaped, thereon processing bolt hole,
For at the turbine disk or compressor disc disk body axle journal bolt connection, the balance weight removable material adjusts quality.
Balance weight sets and removes positions of materials, is easy to accurately adjust weight.
Balance weight L-shaped short side is arc, and its end face is adjacent to disk body upper bolt hole flange arc edge, rotates balance weight
During the centrifugal force that produces undertaken by disk body flange, prevent bolt because being destroyed by shearing force.
This structure is on the basis of the conventional balance mode of both the above, to combine both advantages and improved.
The counterweight block of removable material is installed at compressor disc or turbine disk axle journal bolt connection, wheel rim need not be further added by
Perforate, so as to reduce stress concentration, increases rotor life.Also, balance weight can need to design according to counterweight removes positions of materials.
Beneficial effect：A) it is simple in construction, installed using disk body assembling with bolt hole, it is not necessary to design peace on disk body in addition
Fill hole；B) counterweight block assembly technology is simple, reduces balance difficulty；C) it is easy to use, change balance weight convenient and swift.
Brief description of the drawings
Fig. 1 balance weight graphics
Fig. 2 a are balance block structure front views
Fig. 2 b balance block structure left views
Fig. 3 is schematic diagram after balance weight assembling
1- balance weights, the 2- turbine disks or compressor disc, 3- bolts, 4- nuts
Embodiment：
Set in the balance weight of different weight and remove positions of materials, be easy to accurately adjust weight.
Operation principle：The turbine disk or compressor disc (2) of balance are needed, after being assembled by bolt on axle journal (3), flat
Weighing apparatus airborne measurements go out amount of unbalance and circumferential angle.Then balance weight is removed into material, reached after weight demands, be assemblied in axle journal
At upper bolt, balance weight L-shaped short side is arc, and its end face is adjacent to disk body upper bolt hole flange arc edge, turns balance weight
The centrifugal force produced during dynamic is undertaken by disk body flange, prevents bolt because being destroyed by shearing force.Finally tighten self-locking spiral shell
Female (4), the step of completing counterweight, as shown in Figure 3.
Claims (3)
1. a kind of aeroengine rotor counterweight block structure, it is characterised in that balance weight is L-shaped, thereon processing bolt hole,
For at the turbine disk or compressor disc disk body axle journal bolt connection, the balance weight removable material adjusts quality.
2. aeroengine rotor counterweight block structure as claimed in claim 1, it is characterised in that balance weight sets de-material
Discharge position, is easy to accurately adjust weight.
3. aeroengine rotor counterweight block structure as claimed in claim 1 or 2, it is characterised in that balance weight L-shaped is short
While being arc, its end face is adjacent to disk body upper bolt hole flange arc edge, makes the centrifugal force produced in balance weight rotation process
Undertaken by disk body flange, prevent bolt because being destroyed by shearing force.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621372536.7U CN206360724U (en) | 2016-12-14 | 2016-12-14 | Aeroengine rotor counterweight block structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621372536.7U CN206360724U (en) | 2016-12-14 | 2016-12-14 | Aeroengine rotor counterweight block structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206360724U true CN206360724U (en) | 2017-07-28 |
Family
ID=59375061
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621372536.7U Active CN206360724U (en) | 2016-12-14 | 2016-12-14 | Aeroengine rotor counterweight block structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206360724U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112128147A (en) * | 2020-10-16 | 2020-12-25 | 中国航发四川燃气涡轮研究院 | Simply-assembled reusable balancing device and assembling method |
| CN112160794A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Positioning assembly, turbine disc or compressor disc of positioning assembly and aircraft engine |
| CN113790085A (en) * | 2021-08-31 | 2021-12-14 | 中国船舶重工集团公司第七0三研究所 | On-site dynamic balance structure of marine steam turbine rotor |
| CN113982998A (en) * | 2021-11-02 | 2022-01-28 | 中国航发沈阳发动机研究所 | Compressor complete machine balance structure |
-
2016
- 2016-12-14 CN CN201621372536.7U patent/CN206360724U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112160794A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Positioning assembly, turbine disc or compressor disc of positioning assembly and aircraft engine |
| CN112160794B (en) * | 2020-09-18 | 2023-02-17 | 中国航发四川燃气涡轮研究院 | Positioning assembly, turbine disc or compressor disc of positioning assembly and aircraft engine |
| CN112128147A (en) * | 2020-10-16 | 2020-12-25 | 中国航发四川燃气涡轮研究院 | Simply-assembled reusable balancing device and assembling method |
| CN112128147B (en) * | 2020-10-16 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Simply-assembled reusable balancing device and assembling method |
| CN113790085A (en) * | 2021-08-31 | 2021-12-14 | 中国船舶重工集团公司第七0三研究所 | On-site dynamic balance structure of marine steam turbine rotor |
| CN113982998A (en) * | 2021-11-02 | 2022-01-28 | 中国航发沈阳发动机研究所 | Compressor complete machine balance structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 610500 Xindu Xuefu Road, Xindu District, Chengdu, Sichuan Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 P.O. Box 305, Mianyang City, Sichuan Province Patentee before: CHINA GAS TURBINE EST |
|
| CP03 | Change of name, title or address |