JPS6018202U - Turbo fluid machine blade - Google Patents
Turbo fluid machine bladeInfo
- Publication number
- JPS6018202U JPS6018202U JP10886883U JP10886883U JPS6018202U JP S6018202 U JPS6018202 U JP S6018202U JP 10886883 U JP10886883 U JP 10886883U JP 10886883 U JP10886883 U JP 10886883U JP S6018202 U JPS6018202 U JP S6018202U
- Authority
- JP
- Japan
- Prior art keywords
- fluid machine
- blade
- machine blade
- turbo fluid
- turbo
- 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.)
- Pending
Links
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
第１図は従来のターボ流体機械の羽根の組立状態を示す
斜視図、第２図は従来のターボ流体機械の羽根の組立状
態を示す正面図、第３図は本考案のターボ流体機械の羽
根の一実施例を示す斜視図、第４図は本考案のターボ流
体機械の羽根の一実施例の組立状態を示す正面図、第５
図及び第６図は真白端面の噛み合い状態を示す説明図、
第７図は本考案の他の実施例における真白端面の噛み合
い状態を示す正面図である。
２・・・羽根、４・・・植込部、５・・・具合、６・・
・翼形部、１０．１１・・・真白端面、１０ａ、２０・
・・凸形突起、１１ａ、１９・・・凹形溝。
第３図
第４図Figure 1 is a perspective view showing the assembled state of the blades of a conventional turbo fluid machine, Figure 2 is a front view showing the assembled state of the blades of a conventional turbo fluid machine, and Figure 3 is the blade of the turbo fluid machine of the present invention. FIG. 4 is a perspective view showing an embodiment of the blade of the turbofluid machine of the present invention; FIG.
Figures 6 and 6 are explanatory diagrams showing the meshing state of pure white end surfaces,
FIG. 7 is a front view showing the meshing state of pure white end surfaces in another embodiment of the present invention. 2... Feather, 4... Implanted part, 5... Condition, 6...
・Airfoil section, 10.11...pure white end surface, 10a, 20・
... Convex projection, 11a, 19... Concave groove. Figure 3 Figure 4
Claims (1)
根組立体において、その各羽根の具合の相互に隣接する
端面の相互間を凸形突起と凹形溝との噛合構造に構成し
たターボ流体機械の羽根。In a blade assembly in which a predetermined number of blades are implanted on the circumference of an impeller disk, an interlocking structure is formed between a convex protrusion and a concave groove between mutually adjacent end surfaces of each blade. The blade of a turbofluid machine configured as follows.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10886883U JPS6018202U (en) | 1983-07-15 | 1983-07-15 | Turbo fluid machine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10886883U JPS6018202U (en) | 1983-07-15 | 1983-07-15 | Turbo fluid machine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6018202U true JPS6018202U (en) | 1985-02-07 |
Family
ID=30253829
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10886883U Pending JPS6018202U (en) | 1983-07-15 | 1983-07-15 | Turbo fluid machine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6018202U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011106449A (en) * | 2009-11-12 | 2011-06-02 | General Electric Co <Ge> | Turbine rotating blade and rotor |
| JP2012072750A (en) * | 2010-09-30 | 2012-04-12 | Hitachi Ltd | Turbine moving blade |
| JP2017048791A (en) * | 2015-09-03 | 2017-03-09 | ゼネラル・エレクトリック・カンパニイ | Damper pin for damping adjacent turbine blades |
-
1983
- 1983-07-15 JP JP10886883U patent/JPS6018202U/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011106449A (en) * | 2009-11-12 | 2011-06-02 | General Electric Co <Ge> | Turbine rotating blade and rotor |
| JP2012072750A (en) * | 2010-09-30 | 2012-04-12 | Hitachi Ltd | Turbine moving blade |
| JP2017048791A (en) * | 2015-09-03 | 2017-03-09 | ゼネラル・エレクトリック・カンパニイ | Damper pin for damping adjacent turbine blades |
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