JPS6149102A - Blade of gas turbine - Google Patents

Abstract

PURPOSE:To enhance strength of a gas turbine blade comprising a sheath and insertions by connecting the sheath and the insertions by means of a reinforcement. CONSTITUTION:In a void enclosed by a sheath 1, insertions 2, 4 are introduced from outside, with the result that a cooling duct is thereby formed. At least one point along the length side of the sheath, a reinforcement 3 is fixed and linked with insertions 2, 4. Accordingly, deformation of the sheath 1 can be curbed to the minimum even when difference in the pressure between inside and outside the housing is large, and strength of the blade can be augmented.

Description

TECHNICAL FIELD OF THE INVENTION The present invention relates to a gas turbine blade having a skin and at least one insert.

[Technical background of the invention and its problems]

For example, in the case of a blade that is constructed by fully inserting the insert into the jacket, as shown in Japanese Patent Application Laid-open No. 51-69707, under certain conditions, i.e., the thickness of the jacket is extremely low. If the blade is made too thin, the pressure difference between the inside and outside of the blade will cause large deformation of the outer sheath of the blade, which may result in problems such as breakage. Further, when the pressure of the cooling air used to cool the blades is high, a similar problem may occur, and for this reason, the thickness of the blade outer cover must be increased to a certain extent.

In addition, since the thickness of the outer cover was increased, a large amount of cooling air was required to achieve sufficient cooling.

[Purpose of the invention]

The present invention has been made in view of the above-mentioned circumstances, and its purpose is to easily provide a reinforcing material inside the blade.
The purpose is to provide a gas turbine blade that can have sufficient strength.

[Summary of the invention]

In a gas turbine blade having a jacket and at least one insert, in order to reduce deformation of the jacket, a reinforcement is provided in at least one longitudinal position of the jacket, internally connecting the jacket. The blades of a gas turbine equipped with

〔Effect of the invention〕

In other words, since the gas turbine blade according to the present invention connects the outer sheath internally, it is not only effective as a reinforcing material to reduce the deformation of the outer sheath, but also allows the thickness of the outer sheath to be made extremely thin. Therefore, the cooling efficiency can be increased, sufficient cooling can be achieved with a small amount of cooling air, and the output efficiency of the turbine can be improved.

[Embodiments of the invention]

Examples of the present invention will be described below. FIG. 1 is a structural diagram showing an embodiment of a gas turbine blade according to the present invention.

The jacket l, which has the stable shape required for the blade, is wrapped around the inner cavity, inside which are also hollow inserts 2,
4 is introduced from outside. The inserts 2, 4 abut chord-like projections present on the inner wall of the nuclear envelope 1, between which cooling ducts are formed. In addition, as shown by the arrow, the cooling air passes through the inside of the insert 2.4 from the outside, blows out from the tip of the insert, passes through the cold air duct between the outer jacket l and the insert 2.4, and then flows toward the rear. A passageway for blowing air is formed. A reinforcing material 3 is provided at at least one location in the longitudinal direction of the outer sheath 1 so that the outer sheath 1 of the blade does not undergo large deformation due to high pressure differences or the like. This reinforcing material 3 is the second
As shown in the figure, it is joined to a chord-like protrusion existing on the inner wall of the outer sheath 1, thereby integrally connecting and reinforcing the inside of the outer sheath 1. Note that this reinforcing material has holes so that the spaces in the upper insert 2 and the lower insert 4 communicate with each other.
Cooling air is allowed to flow from the upper insert 2 to the lower insert 4. Furthermore, the reinforcing member 3 and the inserts 2 and 4 are joined by diffusion bonding or the like to prevent leakage of cooling air.

FIG. 2 shows a cross section taken along line A-A in FIG. 1.

Moreover, FIG. 3 shows a conventional structural diagram.

As described above, according to this embodiment, since the reinforcing member 3 that integrally connects the inside of the outer sheath 1 is provided, the deformation of the outer sheath 1 can be easily suppressed to a small level even when the pressure difference between the inside and outside of the outer sheath 1 is large. In addition to this, the thickness of the outer cover 1 can be made extremely thin as a result of providing the reinforcing material, making it possible to achieve sufficient cooling with a small amount of cooling air, thereby skillfully improving the output efficiency of the turbine. I can do it.

[Brief explanation of the drawing]

Figure i1 is a perspective view of an embodiment of the blade according to the present invention, Figure 2 is a cross-sectional view taken along line AA in Figure 1, and Figure 3 is a perspective view of a conventional blade. 1... Outer cover 2... Upper insert 3... Reinforcement material 4 - Lower insert 5 - Insert agent agent Patent attorney Norichika Kensuke (and 1 other person) Figure 1 Figure 2

Claims (1)

[Claims] 1. A gas turbine blade having a jacket and at least one insert, characterized in that the blade is provided with a reinforcing member connecting the inside of the jacket at at least one location in the longitudinal direction.