JPH0327803U

JPH0327803U -

Info

Publication number: JPH0327803U
Application number: JP8687589U
Authority: JP
Priority date: 1989-07-26
Filing date: 1989-07-26
Publication date: 1991-03-20
Anticipated expiration: 2004-07-26
Also published as: JPH0738641Y2

Description

[Brief explanation of drawings]

第１図は本考案の第１実施例を、回転軸線を通
る平面に沿つて示す図である。第２図は、本考案
の第２実施例を、回転軸線を通る平面に沿つて示
す図である。第３図ないし第８図は第２実施例に
おける整流用インサート材の平状例を示す図であ
つて、第３図は第１の例の内面図、第４図は第３
図の−断面図、第５図は第２の例の内面図、
第６図は第５図の−断面図、第７図は第３の
例の内面図、第８図は第７図の−断面図であ
る。第９図は、従来の多段軸流タービンの最終段
付近の流体通路の一例を、回転軸線を通る平面に
沿つて示す図、第１０図は同じく最終段動翼の先
端部翼列まわりの正常流れを示す図である。第１
１図はオフ・デザイン状態における最終段動翼の
先端部翼列流れを示す図である。１……ケーシング壁面、２……ロータハブ、３
……最終段動翼、３ａ……翼先端部、３ｂ……翼
背面、３ｃ……翼腹面、４……最終段静翼、５…
…前段動翼、６……淀領域、７……円周溝、８…
…円環、９……隙間、１０……整流用インサート
材、１５……剥離。 FIG. 1 is a view showing a first embodiment of the present invention along a plane passing through the axis of rotation. FIG. 2 is a view showing a second embodiment of the present invention along a plane passing through the axis of rotation. 3 to 8 are views showing flat examples of the rectifying insert material in the second embodiment, in which FIG. 3 is an inner view of the first example, and FIG. 4 is an inner view of the third example.
Fig. 5 is an inner view of the second example;
FIG. 6 is a cross-sectional view taken from FIG. 5, FIG. 7 is an inner view of the third example, and FIG. 8 is a cross-sectional view taken from FIG. 7. Figure 9 is a diagram showing an example of a fluid passage near the final stage of a conventional multi-stage axial flow turbine along a plane passing through the axis of rotation, and Figure 10 is a diagram showing the normal flow around the tip row of the final stage rotor blade. It is a diagram showing a flow. 1st
FIG. 1 is a diagram showing the flow of the blade row at the tip of the final stage rotor blade in an off-design state. 1...Casing wall surface, 2...Rotor hub, 3
...Last stage rotor blade, 3a...Blade tip, 3b...Blade back surface, 3c...Blade ventral surface, 4...Final stage stationary blade, 5...
...Front-stage rotor blade, 6... Stagnation area, 7... Circumferential groove, 8...
... Circular ring, 9 ... Gap, 10 ... Rectifying insert material, 15 ... Peeling.

Claims

[Claims for Utility Model Registration] (1) In an axial-flow turbine consisting of multiple stages, a casing wall facing the tip of the final stage rotor blade is coated from a position upstream of the leading edge of the rotor blade. A groove is cut out along the circumferential direction from a position downstream of the edge to a position upstream of the trailing edge, and a groove is cut out along the circumferential direction within the groove and on the inner wall surface and bottom of the groove. A multistage axial flow turbine characterized by having a ring arranged at a distance from the center. (2) In an axial-flow turbine consisting of multiple stages, at least a portion of the casing wall facing the tip of the final stage rotor blade is installed in the range from the leading edge to the trailing edge of the rotor blade. A multistage axial flow turbine characterized in that a groove is provided with a portion cut out along the circumferential direction, and an annular rectifying insert material is embedded in the groove.