JPS57171007A - Turbine nozzle - Google Patents
Turbine nozzleInfo
- Publication number
- JPS57171007A JPS57171007A JP5595281A JP5595281A JPS57171007A JP S57171007 A JPS57171007 A JP S57171007A JP 5595281 A JP5595281 A JP 5595281A JP 5595281 A JP5595281 A JP 5595281A JP S57171007 A JPS57171007 A JP S57171007A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- alpha
- loss
- blade thickness
- line
- 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.)
- Granted
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 improve the efficiency of turbine stage while keeping the blade profile loss to minimum by a method wherein the amount of change in the blade thickness of the blade profile of the turbine nozzle is rendered to be smaller near the following edge of the blade and as well as the inclination angle of the tangent line to a chamber line is rendered to be changed sharply at the downstream side. CONSTITUTION:Let L be the distance from the maximum blade thickness point to the following edge and X be the coordinate from the maximum blade thickness point toward the downstream direction both of which are taken along the chamber line C of the blade profile. Furthermore, the blade thickness at X/L= 0.5 divided by the maximum blade thickness is taken as r and the angle made by the tangent line t2 at X/L=0.3 to the chamber line C and the tangent line t1 at the following edge to the chamber line C is taken as alpha. r and alpha are set so as to fall within the following ranges, 0.25<=r<=0.4 and 15 deg.<=alpha<=30 deg.. When r and alpha are set in the ranges as mentioned above, the total nozzle loss or the sum of the blade profile loss and the secondary flow loss turns to be minimum value and the improvement of the efficiency of the turbine stage is resulted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5595281A JPS57171007A (en) | 1981-04-14 | 1981-04-14 | Turbine nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5595281A JPS57171007A (en) | 1981-04-14 | 1981-04-14 | Turbine nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS57171007A true JPS57171007A (en) | 1982-10-21 |
| JPS641643B2 JPS641643B2 (en) | 1989-01-12 |
Family
ID=13013404
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5595281A Granted JPS57171007A (en) | 1981-04-14 | 1981-04-14 | Turbine nozzle |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS57171007A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107178526A (en) * | 2017-07-11 | 2017-09-19 | 上海电气燃气轮机有限公司 | Axial Compressor Blade Profile design method and Axial Compressor Blade Profile |
-
1981
- 1981-04-14 JP JP5595281A patent/JPS57171007A/en active Granted
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107178526A (en) * | 2017-07-11 | 2017-09-19 | 上海电气燃气轮机有限公司 | Axial Compressor Blade Profile design method and Axial Compressor Blade Profile |
| CN107178526B (en) * | 2017-07-11 | 2019-09-24 | 上海电气燃气轮机有限公司 | Axial Compressor Blade Profile design method and Axial Compressor Blade Profile |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS641643B2 (en) | 1989-01-12 |
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