JPS62114105U - - Google Patents
Info
- Publication number
- JPS62114105U JPS62114105U JP68186U JP68186U JPS62114105U JP S62114105 U JPS62114105 U JP S62114105U JP 68186 U JP68186 U JP 68186U JP 68186 U JP68186 U JP 68186U JP S62114105 U JPS62114105 U JP S62114105U
- Authority
- JP
- Japan
- Prior art keywords
- blade
- leading edge
- wall surface
- axial flow
- airfoil
- 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
- 238000010586 diagram Methods 0.000 description 6
- 230000006866 deterioration Effects 0.000 description 1
Description
第1図より第3図は本考案に関し、第1図はケ
ーシング側壁面に固定の静翼図、第2図はボス側
壁面固定の静翼図、第3図はボス側壁面のみ固定
の動翼図、第4図以下は従来例に係り、第4図は
軸流ターボ機械の主要部である動翼および静翼の
略図、第5図は端壁に沿つて馬蹄形渦及び流路渦
が生じることを示す斜視図、第6図は端壁に発達
する壁面境界層の流線の曲率を示す略図、第7図
は端壁上の翼前縁をまわり込む馬蹄形渦と速度分
布を示す略図、第8図は渦が2次流れによる性能
低下(損失)を示す略図、第9図は上記の対策と
して壁面通路内にフインを設けて損失を防止する
考えを示す略図である。
1……静翼、1c……静翼前縁、2……動翼、
2c……動翼前縁、3a……ケーシング側壁面、
3b……ボス側壁面。
Figures 1 through 3 relate to the present invention; Figure 1 is a diagram of the stator vane fixed to the casing side wall, Figure 2 is a diagram of the stator vane fixed to the boss side wall, and Figure 3 is the movable vane fixed only to the boss side wall. Figure 4 shows a schematic view of the moving blade and stationary blade, which are the main parts of an axial flow turbomachine, and Figure 5 shows a horseshoe-shaped vortex and a flow path vortex along the end wall. Fig. 6 is a schematic diagram showing the streamline curvature of the wall boundary layer that develops on the end wall, and Fig. 7 is a schematic diagram showing the horseshoe-shaped vortex surrounding the leading edge of the wing on the end wall and the velocity distribution. , FIG. 8 is a schematic diagram illustrating performance deterioration (loss) due to secondary flow of vortices, and FIG. 9 is a schematic diagram illustrating the idea of providing fins in the wall passage as a countermeasure to the above-mentioned problem to prevent loss. 1... Stationary blade, 1c... Stationary blade leading edge, 2... Moving blade,
2c... Leading edge of rotor blade, 3a... Casing side wall surface,
3b...Boss side wall surface.
Claims (1)
あつて、翼を固定する壁面、またはシユラウド面
などの端壁面近傍の翼形前縁を、流路中央部翼形
の前縁より、下流側に位置させる形状とした軸流
ターボ機械翼列。 The leading edge of the airfoil near the end wall surface, such as the wall surface on which the blade is fixed or the shroud surface, of the stator blade or rotor blade that constitutes the axial flow turbomachine, is located downstream of the leading edge of the airfoil in the center of the flow path. Axial flow turbomachinery blade row shaped to be located at.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP68186U JPS62114105U (en) | 1986-01-09 | 1986-01-09 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP68186U JPS62114105U (en) | 1986-01-09 | 1986-01-09 |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS62114105U true JPS62114105U (en) | 1987-07-20 |
Family
ID=30777873
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP68186U Pending JPS62114105U (en) | 1986-01-09 | 1986-01-09 |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS62114105U (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH09184451A (en) * | 1995-11-17 | 1997-07-15 | United Technol Corp <Utc> | Turbo machine blade |
US8317466B2 (en) | 2007-01-12 | 2012-11-27 | Mitsubishi Heavy Industries, Ltd. | Blade structure of gas turbine |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5688903A (en) * | 1979-12-20 | 1981-07-18 | Toshiba Corp | Turbine nozzle blade |
JPS5820903A (en) * | 1981-07-29 | 1983-02-07 | Hitachi Ltd | Stationary blade of turbine |
-
1986
- 1986-01-09 JP JP68186U patent/JPS62114105U/ja active Pending
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5688903A (en) * | 1979-12-20 | 1981-07-18 | Toshiba Corp | Turbine nozzle blade |
JPS5820903A (en) * | 1981-07-29 | 1983-02-07 | Hitachi Ltd | Stationary blade of turbine |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH09184451A (en) * | 1995-11-17 | 1997-07-15 | United Technol Corp <Utc> | Turbo machine blade |
US8317466B2 (en) | 2007-01-12 | 2012-11-27 | Mitsubishi Heavy Industries, Ltd. | Blade structure of gas turbine |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4826400A (en) | Curvilinear turbine airfoil | |
JP5300874B2 (en) | Blade with non-axisymmetric platform and depression and protrusion on outer ring | |
JP2753217B2 (en) | Wings for gas turbine engines | |
GB2264755A (en) | Stator blade construction | |
CA1157779A (en) | Compression section for an axial flow rotary machine | |
JPH10274001A (en) | Turbulence promotion structure of cooling passage of blade inside gas turbine engine | |
DE60044228D1 (en) | Compressor rotor configuration | |
JPS61114005U (en) | ||
EP0775249A1 (en) | Flow directing assembly for the compression section of a rotary machine | |
JP2673156B2 (en) | Fan blade | |
US20210215055A1 (en) | Turbomachine stator element | |
JPS6133968B2 (en) | ||
JPS62114105U (en) | ||
JPH10306702A (en) | Gas turbine blade | |
JPH0692723B2 (en) | Axial flow fluid machine | |
JP3626899B2 (en) | End wall structure between turbine blades | |
JP3402176B2 (en) | Blades for turbomachinery | |
JPH0689651B2 (en) | Axial flow fluid machine | |
JPH04287802A (en) | Steam turbine nozzle | |
JPS5933841Y2 (en) | radial turbine wheel | |
JP4090613B2 (en) | Axial flow turbine | |
JPH0658115B2 (en) | Engine cooling turbine | |
JPS6241802U (en) | ||
JP3541479B2 (en) | Axial compressor stationary vane | |
JPS61187502A (en) | Blade construction of axial flow turbo-machine |