CN204419273U - A kind of turbine rotor blade position structure - Google Patents
A kind of turbine rotor blade position structure Download PDFInfo
- Publication number
- CN204419273U CN204419273U CN201520009092.XU CN201520009092U CN204419273U CN 204419273 U CN204419273 U CN 204419273U CN 201520009092 U CN201520009092 U CN 201520009092U CN 204419273 U CN204419273 U CN 204419273U
- Authority
- CN
- China
- Prior art keywords
- tenon tooth
- turbine rotor
- blade
- listrium
- root segment
- Prior art date
- 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.)
- Expired - Fee Related
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Abstract
A kind of turbine rotor blade position structure, is characterized in that: described turbine rotor blade position structure, comprises blade, listrium, stretches root segment and tenon tooth; Wherein: blade, listrium, stretch root segment and tenon tooth connects successively; Have two circular flats in the side of stretching root segment, precision casting is shaped; Blade and listrium set four locating points, sets two locating points at the circle centre position of two circular flats; In above six locating points any 4 all not coplanar.Advantage of the present utility model: turbine rotor blade position structure described in the utility model, solves locating point and the distant problem of tenon tooth, reduces lever principle to the impact of tenon tooth machining accuracy, thus improves the up-to-standard rate of tenon tooth dimensioned.
Description
Technical field
The utility model relates to aeroengine field, particularly a kind of turbine rotor blade position structure.
Background technique
In the structure of current aero-turbine rotor blade, the blade passage surface be made up of blade outer surface and listrium upper surface adopts precision casting, and tenon tooth then adopts precision optical machinery to process.When processing the size of tenon tooth, generally on blade and listrium, set six locating points, adopt six point location method determination machining benchmarks, positioning principle is: utilize blade passage every 4 all not coplanar six points on the surface, determine a three dimensional space reference coordinate plane, thus complete the staff cultivation of blade is located.Six locating points are all on blade and listrium, and blade, stretched between listrium and tenon tooth root segment isolation, six locating points and tenon tooth distant, the tolerance produced by locating point, under the effect of lever principle, produce larger impact to tenon tooth dimensioned, cause tenon tooth work precision low, up-to-standard rate declines.
Model utility content
The purpose of this utility model is to provide a kind of turbine rotor blade position structure of improvement, to solve locating point and the distant problem of tenon tooth, reduce lever principle to the impact of tenon tooth machining accuracy, thus improving the up-to-standard rate of tenon tooth dimensioned, spy provides a kind of turbine rotor blade position structure.
The utility model provides a kind of turbine rotor blade position structure, it is characterized in that: described turbine rotor blade position structure, comprises blade 1, listrium 2, stretches root segment 3 and tenon tooth 4;
Wherein: blade 1, listrium 2, stretch root segment 3 and tenon tooth 4 connects successively; Have two circular flats 5 in the side of stretching root segment 3, precision casting is shaped; Blade 1 and listrium 2 set four locating points, sets two locating points at the circle centre position of two circular flats 5; In above six locating points any 4 all not coplanar; A three dimensional space reference coordinate plane can be determined, thus complete the staff cultivation of blade is located.
Described has two circular flats 5 in the side of stretching root segment 3, and the diameter of circular flat 5 is 3 ~ 5mm.
Set two locating points, the distance of furthered locating point and tenon tooth 4 stretching on root segment 3, solve locating point and the distant problem of tenon tooth 4, reduce the impact of lever principle on tenon tooth machining accuracy, thus improve the up-to-standard rate of tenon tooth 4 dimensioned.
Advantage of the present utility model:
Turbine rotor blade position structure described in the utility model, solves locating point and the distant problem of tenon tooth, reduces lever principle to the impact of tenon tooth machining accuracy, thus improves the up-to-standard rate of tenon tooth dimensioned.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the utility model is described in further detail:
Fig. 1 is turbine rotor blade position structure schematic diagram.
Embodiment
Embodiment 1
Present embodiments provide a kind of turbine rotor blade position structure, it is characterized in that: described turbine rotor blade position structure, comprise blade 1, listrium 2, stretch root segment 3 and tenon tooth 4;
Wherein: blade 1, listrium 2, stretch root segment 3 and tenon tooth 4 connects successively; Have two circular flats 5 in the side of stretching root segment 3, precision casting is shaped; Blade 1 and listrium 2 set four locating points, sets two locating points at the circle centre position of two circular flats 5; In above six locating points any 4 all not coplanar; A three dimensional space reference coordinate plane can be determined, thus complete the staff cultivation of blade is located.
Described has two circular flats 5 in the side of stretching root segment 3, and the diameter of circular flat 5 is 3mm.
Set two locating points, the distance of furthered locating point and tenon tooth 4 stretching on root segment 3, solve locating point and the distant problem of tenon tooth 4, reduce the impact of lever principle on tenon tooth machining accuracy, thus improve the up-to-standard rate of tenon tooth 4 dimensioned.
Embodiment 2
Present embodiments provide a kind of turbine rotor blade position structure, it is characterized in that: described turbine rotor blade position structure, comprise blade 1, listrium 2, stretch root segment 3 and tenon tooth 4;
Wherein: blade 1, listrium 2, stretch root segment 3 and tenon tooth 4 connects successively; Have two circular flats 5 in the side of stretching root segment 3, precision casting is shaped; Blade 1 and listrium 2 set four locating points, sets two locating points at the circle centre position of two circular flats 5; In above six locating points any 4 all not coplanar; A three dimensional space reference coordinate plane can be determined, thus complete the staff cultivation of blade is located.
Described has two circular flats 5 in the side of stretching root segment 3, and the diameter of circular flat 5 is 4mm.
Set two locating points, the distance of furthered locating point and tenon tooth 4 stretching on root segment 3, solve locating point and the distant problem of tenon tooth 4, reduce the impact of lever principle on tenon tooth machining accuracy, thus improve the up-to-standard rate of tenon tooth 4 dimensioned.
Embodiment 3
Present embodiments provide a kind of turbine rotor blade position structure, it is characterized in that: described turbine rotor blade position structure, comprise blade 1, listrium 2, stretch root segment 3 and tenon tooth 4;
Wherein: blade 1, listrium 2, stretch root segment 3 and tenon tooth 4 connects successively; Have two circular flats 5 in the side of stretching root segment 3, precision casting is shaped; Blade 1 and listrium 2 set four locating points, sets two locating points at the circle centre position of two circular flats 5; In above six locating points any 4 all not coplanar; A three dimensional space reference coordinate plane can be determined, thus complete the staff cultivation of blade is located.
Described has two circular flats 5 in the side of stretching root segment 3, and the diameter of circular flat 5 is 5mm.
Set two locating points, the distance of furthered locating point and tenon tooth 4 stretching on root segment 3, solve locating point and the distant problem of tenon tooth 4, reduce the impact of lever principle on tenon tooth machining accuracy, thus improve the up-to-standard rate of tenon tooth 4 dimensioned.
Claims (2)
1. a turbine rotor blade position structure, is characterized in that: described turbine rotor blade position structure, comprises blade (1), listrium (2), stretches root segment (3) and tenon tooth (4);
Wherein: blade (1), listrium (2), stretch root segment (3) and tenon tooth (4) connects successively; Have two circular flats (5) in the side of stretching root segment (3), precision casting is shaped; At blade (1) and upper setting four locating points of listrium (2), set two locating points at the circle centre position of two circular flats (5); In above six locating points any 4 all not coplanar.
2. according to turbine rotor blade position structure according to claim 1, it is characterized in that: described has two circular flats (5) in the side of stretching root segment (3), and the diameter of circular flat (5) is 3 ~ 5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520009092.XU CN204419273U (en) | 2015-01-06 | 2015-01-06 | A kind of turbine rotor blade position structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520009092.XU CN204419273U (en) | 2015-01-06 | 2015-01-06 | A kind of turbine rotor blade position structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204419273U true CN204419273U (en) | 2015-06-24 |
Family
ID=53469655
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520009092.XU Expired - Fee Related CN204419273U (en) | 2015-01-06 | 2015-01-06 | A kind of turbine rotor blade position structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204419273U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106737172A (en) * | 2016-12-21 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Grinding attachment |
| CN108372337A (en) * | 2016-12-20 | 2018-08-07 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of positioning of blade and fixing device and its realize blade positioning and fixed method |
| WO2019136672A1 (en) * | 2018-01-11 | 2019-07-18 | 贵州智慧能源科技有限公司 | Turbine blade flange plate based on spline curve design |
-
2015
- 2015-01-06 CN CN201520009092.XU patent/CN204419273U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108372337A (en) * | 2016-12-20 | 2018-08-07 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of positioning of blade and fixing device and its realize blade positioning and fixed method |
| CN106737172A (en) * | 2016-12-21 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Grinding attachment |
| WO2019136672A1 (en) * | 2018-01-11 | 2019-07-18 | 贵州智慧能源科技有限公司 | Turbine blade flange plate based on spline curve design |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150624 Termination date: 20220106 |
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| CF01 | Termination of patent right due to non-payment of annual fee |