JPS62114105U

JPS62114105U -

Info

Publication number: JPS62114105U
Application number: JP68186U
Authority: JP
Priority date: 1986-01-09
Filing date: 1986-01-09
Publication date: 1987-07-20

Description

[Brief explanation of the drawing]

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

[Scope of utility model registration request]

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.