JPH03122202U - - Google Patents
Info
- Publication number
- JPH03122202U JPH03122202U JP3053390U JP3053390U JPH03122202U JP H03122202 U JPH03122202 U JP H03122202U JP 3053390 U JP3053390 U JP 3053390U JP 3053390 U JP3053390 U JP 3053390U JP H03122202 U JPH03122202 U JP H03122202U
- Authority
- JP
- Japan
- Prior art keywords
- blade
- blade tip
- turbine wheel
- surface side
- viewed
- 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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
第１図は本考案に係るラジアルタービンホイー
ルの翼先端構造の一実施例を示す断面図、第２図
は従来のラジアルタービンの一例を示す断面図、
第３図は第２図の−線拡大断面図である。
１２……動翼、１３……翼先端面、１４……圧
力面、１５……負圧面、１６……クリアランス、
１７……シユラウドケーシング内壁面、１８……
漏れ流れ。
FIG. 1 is a sectional view showing an example of a blade tip structure of a radial turbine wheel according to the present invention, and FIG. 2 is a sectional view showing an example of a conventional radial turbine.
FIG. 3 is an enlarged sectional view taken along the - line in FIG. 2. 12... Moving blade, 13... Blade tip surface, 14... Pressure surface, 15... Negative pressure surface, 16... Clearance,
17... Shroud casing inner wall surface, 18...
leakage flow.
Claims (1)
ンホイール回転軸に直角な断面でみたときに、翼
先端面の翼圧力面側の端部が、翼先端面の翼負圧
面側の端部より半径位置が大きくなるよう形成さ
れたことを特徴とするラジアルタービンホイール
の翼先端構造。 When the blade tip along the shroud line of each blade is viewed in a cross section perpendicular to the turbine wheel rotation axis, the end of the blade tip surface on the blade pressure surface side is radially smaller than the end of the blade tip surface on the blade suction surface side. A blade tip structure of a radial turbine wheel characterized by being formed to have a large position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3053390U JPH03122202U (en) | 1990-03-27 | 1990-03-27 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3053390U JPH03122202U (en) | 1990-03-27 | 1990-03-27 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH03122202U true JPH03122202U (en) | 1991-12-13 |
Family
ID=31533242
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3053390U Pending JPH03122202U (en) | 1990-03-27 | 1990-03-27 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH03122202U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2309097A1 (en) * | 2009-09-30 | 2011-04-13 | Siemens Aktiengesellschaft | Airfoil and corresponding guide vane, blade, gas turbine and turbomachine |
-
1990
- 1990-03-27 JP JP3053390U patent/JPH03122202U/ja active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2309097A1 (en) * | 2009-09-30 | 2011-04-13 | Siemens Aktiengesellschaft | Airfoil and corresponding guide vane, blade, gas turbine and turbomachine |