JPS57171006A - Moving blade of turbine - Google Patents
Moving blade of turbineInfo
- Publication number
- JPS57171006A JPS57171006A JP5682281A JP5682281A JPS57171006A JP S57171006 A JPS57171006 A JP S57171006A JP 5682281 A JP5682281 A JP 5682281A JP 5682281 A JP5682281 A JP 5682281A JP S57171006 A JPS57171006 A JP S57171006A
- Authority
- JP
- Japan
- Prior art keywords
- moving blade
- root
- deflection angle
- distance
- turbine
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
PURPOSE:To reduce the secondary flow loss at the root of a moving blade by a method wherein the deflection angle at the position within a specified range of distance from the root of the moving blade is rendered to be smaller than the deflection angle at the root of the moving blade by an angular range of specified value on the impulse stage moving blade of an axial flow turbine. CONSTITUTION:The position, which lies in the distance H from the root of the moving blade of the turbine and the distance H satisfies with the following relation, 1.05<=(Di+2H)/Di<=1.15 (wherein Di is the root diameter of the moving blade of the turbine) is determined. The deflection angle at the position with the distance H is rendered to be smaller than the deflection angle at the root by the value in the range of 0-7 deg.. Now that the deflection angle epsilonb at the position with the distance H is rendered to be smaller thanthe conventional deflection angle, which is equal to he deflection angle epsilona at the root, flow lines 62 can have larger radii of curvature than conventional flow lines 61, resulting in enabling to reduce the pressure difference angle the passage from the front surface 31 side to the rear surface 32 side. In such a manner as mentioned above, the development of the secondary flow within the moving blade is suppressed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5682281A JPS57171006A (en) | 1981-04-15 | 1981-04-15 | Moving blade of turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5682281A JPS57171006A (en) | 1981-04-15 | 1981-04-15 | Moving blade of turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS57171006A true JPS57171006A (en) | 1982-10-21 |
Family
ID=13038059
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5682281A Pending JPS57171006A (en) | 1981-04-15 | 1981-04-15 | Moving blade of turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS57171006A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6431829B1 (en) | 1999-06-03 | 2002-08-13 | Ebara Corporation | Turbine device |
| US6799948B2 (en) | 2001-01-12 | 2004-10-05 | Mitsubishi Heavy Industries, Ltd. | Blade of a gas turbine |
-
1981
- 1981-04-15 JP JP5682281A patent/JPS57171006A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6431829B1 (en) | 1999-06-03 | 2002-08-13 | Ebara Corporation | Turbine device |
| US6799948B2 (en) | 2001-01-12 | 2004-10-05 | Mitsubishi Heavy Industries, Ltd. | Blade of a gas turbine |
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