JPH05340203A - Reinforced turbocharger vane - Google Patents

Abstract

PURPOSE: To prevent deformation of a part of a turbocharger stator by hard materials during cleaning. CONSTITUTION: An airfoil 10 for a turbocharger stator is generally hollow and is constituted by a convex wall 12, a concave wall 14, a leading edge 16 and a trailing edge 18. The airfoil 10 is provided with a reinforcement plate 20 that extends from the trailing edge 18 to interior part of the extending wall 12, and is reinforced by this plate. The reinforced portion corresponds to the area that is prone to deform.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a vane of an exhaust turbine supercharger used for a large two-cycle or four-cycle diesel engine.

[0002]

BACKGROUND OF THE INVENTION In such large diesel engines, heavy oil is often used, which produces very messy exhaust gas. Therefore, the solid carbon-containing substance is deposited on the stator-side blade of the diesel engine, that is, the stationary blade, resulting in a decrease in efficiency. Therefore, in order to maintain the performance of the turbocharger, it has to be regularly cleaned. This cleaning is usually done by introducing a hard material into the exhaust gas upstream of the supercharger. The material strikes the inner surface of the turbine and removes dirt.

However, in this cleaning method, since the speed of the exhaust gas is considerably high, there is a problem that the suction surface of the blade is deformed by the collision of the hard material with the blade.

[0004]

SUMMARY OF THE INVENTION The present invention has been made to solve these problems, and an object thereof is to provide an improved technique for turbine blades.

[0005]

The exhaust vane of the exhaust turbine supercharger of the present invention is generally hollow and has a configuration in which a convex wall and a concave wall intersect at the front end and the rear end of the blade, and further, The convex wall has a thicker inner surface extending from the rear end. It is preferable to provide a thin plate-shaped reinforcing member having folds formed therein so as to be substantially parallel to the front end and the rear end.

[0006]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT A preferred embodiment of the present invention will be described below with reference to the accompanying FIG. FIG. 1 shows a sectional shape of a wing shape (wing shape of an aircraft) of a vane 10 of an exhaust turbine supercharger of a large diesel engine.

The vane 10 includes a convex (upper) wall 12, a concave (lower) wall 14, a front end 16 and a rear end 18. The airfoil 10 is manufactured from a material having a thickness determined by the radius of the trailing edge 18. A typical example of such a wing is the front end 1
Straight length from 6 to the rear end 18 is 100mm, thickness is 12mm
The radius of the rear end 18 is 0.5 mm. An undulating elongate member 22 extends the entire length of the blade and is brazed in place to provide strength.

A reinforcing plate 2 is provided on the inner surface of the convex wall 12.
0 is fixed (usually brazing). The reinforcing plate 20 is formed from the rear end 18 on both the convex and concave wall surfaces 1.
The distance between 2 and 14 extends to the farthest position.

The reinforcing plate 20 is a machined reinforcing member and is designed to increase the mechanical strength of the portion where the cleaning material collides. The reinforcing plate 20
Penetrates into the curved portion of the rear end 18 and closes the gap in that portion.

Therefore, the present invention can be applied as a technique of using a thin blade material and partially reinforcing a portion which is easily damaged during cleaning.

[0011]

According to the present invention, the inner surface of the convex wall 12 of the generally hollow stator vane 10 is reinforced by the reinforcing plate 20 from the rear end 18 to the middle of the blade 10, so that regular cleaning is performed. It is possible to effectively carry out the work without causing deformation due to the sizing work. Further, according to the present invention, since the place where damage is likely to occur due to the cleaning operation is partially reinforced, it is possible to use a relatively thin wall material for the blade 10.

[Brief description of drawings]

FIG. 1 is a diagram showing a cross-sectional shape of a blade of an embodiment according to the present invention.

[Explanation of symbols]

 10 stationary blade (turbine blade) 12 convex wall 14 concave wall 16 front end 18 rear end 20 reinforcing plate 22 elongated member

Claims (9)

[Claims] 1. A vane (10) for an exhaust turbine supercharger, the vane (10) being generally hollow and having a convex wall (1).
2) and the concave wall (14) include a front end (16) and a rear end (1
8) and the convex wall (12).
However, a reinforced turbine blade having a thicker inner surface extending from the rear end (18). 2. A reinforcing material (20, 20) is provided inside the blade (10).
22) The reinforced turbine blade of claim 1, comprising 22). 3. The inner stiffener (22) has a front end (1).
6) and a thin plate-shaped reinforcing member having pleats formed so as to be substantially parallel to the rear end (18).
Reinforced turbine blades. 4. The radius of the trailing end (18) is substantially equal to 0.
The reinforcing turbine blade according to any one of claims 1 to 3, which has a size of 5 mm. 5. Reinforcement according to claim 1, wherein a reinforcing plate (20) is fixed to the inner surface of the convex wall (12), the wall (12) being thicker at that part. Turbine blades. 6. Reinforced turbine blade according to claim 5, wherein said reinforcing plate (20) is fixed by brazing. 7. The reinforcing plate (20) is shaped so as to enter even a curved portion of the rear end (18) and close a gap in that portion.
Reinforced turbine blades. 8. The thickened portion extends from the rear end (18),
The reinforced turbine blade according to any one of claims 1 to 7, wherein both the convex and concave wall surfaces (12, 14) extend to the farthest positions. 9. A reinforced turbine blade according to claim 1, wherein the blade (10) is in the shape of a wing of an aircraft.