JPS5867999A - Moving vane structure in axial flow type fluid machine - Google Patents

Abstract

PURPOSE:To improve the fluid performance and efficiency by fitting ribs on a moving vane so as to rectify the boundary layer flow on the vane surface and to control the inflow angle into a stationary vane. CONSTITUTION:Ribs 6 with a height nearly equal to the thickness of the boundary layer on a moving vane is provided on the vane surface of the moving vane 3 in the axial direction. Approximately five to ten ribs 6 are provided on every moving vane 3, and the angle of a rib 6 in relation to a shaft 2 is made larger for the rib 6 nearer to the tip of the moving vane 3. Accordingly, the boundary layer flow on the moving vane 3 is rectified and the secondary flow loss near the tip of the moving vane 3 is reduced, and the leakage loss from the gap at the tip of the moving vane 3 can be reduced, thereby the efficiency can be remarkably improved and the inflow angle into the stationary vane can be made uniform, thus the fluid performance can be improved.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to the structure of moving blades in axial flow fluid machines such as trickle blowers and trickle compressors, and furthermore, to control the boundary layer flow generated on the peaks or blade surfaces of the rotor blades. It was designed to do so.

In the conventional e+ flow type fluid machine,
To control the boundary layer tlJ generated on the blade surface, there are methods such as providing a large number of holes on the surface of the rotor blade and sucking the boundary layer of the JK surface through the holes, or making the rotor X a compound blade.

The present invention improves the fluid performance by flowing the boundary layer flow t-m over the rotor blade, and simultaneously reduces the leakage violet flowing through the gap between the rotor blade and the casing blade, thereby achieving the same efficiency. Moving blades in flow-type fluid machines m! The purpose is to provide a lip 1c on the rotor blade of a trickle type fluid machine to rectify the boundary layer flow on the blade surface.

Axial flow pressure i! of the boundary layer formed on the wing surface. tll decoration is important, and the present invention is one means for that purpose.According to the present invention, not only is there a great effect on the efficiency of flow type fluid machines, but also the surging characteristics are improved by flowing the flow. be able to.

The present invention will be explained below using a complete example of a hydraulic pressure machine, with reference to Figures 91g1 and 2.

The flow tl'iJK[fD in the trickle compressor casing can be divided into two parts: the boundary layer flow near the casing wall, and the other potential flow that has no viscosity. Since frictional losses in the compressor occur within this boundary layer, frictional losses can be greatly reduced by controlling this boundary layer.

A typical pattern of boundary layer flow over a rotor blade at pressure ** is shown in FIG. In the figure, 1 is a casing, 2 is a rotor blade 9 attached to the shaft 2, and the open eyelid 5 on the blade surface of this mman 3 represents a boundary layer flow. As shown in the figure, the closer to the base end of the rotor blade 3, the stronger the influence of the centrifugal force is, so the boundary flow 5 near the tip of the rotor blade 3 is bent into a radial direction. Therefore,
The boundary layer flow 5 flows toward the tip of the rotor blade, and a secondary flow occurs near the tip of the rotor blade, resulting in a large loss. Makin, the flow is moving #! When the flow that has passed through the stationary blade 3 flows into the stationary blade 4, its inflow angle is not equal to one foot on the stationary blade. This non-uniformity of the inflow angle in the rearward direction causes a large collision loss.

The present invention eliminates this bias in the flow and allows the flow to flow. The outline is shown in figure s2. In the figure, 2 is the mfL pressure shaft, and 3 is! ItlX
, 6 is a lip for rectification attached to the blade surface of the rotor blade 3, and this lip 6 is formed approximately in the axial direction. Currently, only boundary I- is a problem, so the severity of reply 6 is IIJ
The thickness of the boundary layer on JIjL is approximately the same (usually 2 to 3 degrees). By providing these six ribs, it is possible to flow the visibility layer t-m on the rotor blade and flow into the stationary blade at a uniform inflow angle, thereby reducing the number of collisions. Friend, this LI flow lip 6 suppresses the boundary layer flow from being bent in the backward direction, so it is possible to completely prevent secondary flow and also to prevent the flow from passing through the gap between the casing wall and the rotor blade 3. It is also possible to reduce the number of children who are left behind, thereby increasing efficiency. The number of reps 6 is about 5 to 10 per sheet of dynamic JIK 3.

Friend, if the rectification is sudden, it will cause a large resistance and friction loss, so the closer the rotor blade 30 is to the above-mentioned Lip 6I/i, the larger the angle it makes with the compression rock shaft 2. That's what I do.

In the present invention, since the lip is attached to the rotor blade, boundary layer flow tki can flow in terms of fluid performance.
Therefore, it is possible to reduce the secondary flow loss near the root end of the rotor blade, and also to reduce the leakage loss from the gap at the tip of the rotor blade, resulting in a significant efficiency improvement. There is. Furthermore, since the inflow angle to the stator vane can be controlled, the collision loss at the stator vane can be significantly reduced, and the fluidity Xt can be increased. Furthermore, the present invention is also advantageous against surging. In other words, the rectification of the flow is effective in preventing separation of the boundary layer, which is a trigger for surging, and is therefore far superior to conventional systems in terms of surging.

[Brief explanation of the drawing]

Figure 1 is a schematic diagram of an axial flow pressure assembly to explain the boundary layer flow pattern on the rotor blade, and Figure 2 is the structure of the present invention.
FIG. 3... m 10,000, 5... boundary layer accent, 6... reply. vi i eye

Claims (1)

[Claims] This is an axial flow type fluid machine structure, characterized in that a lip is attached to the wJ band of the axial flow type fluid machine so that the flow flows across the boundary on the blade surface.