JP3160484B2 - Gas turbine blade cooling system - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a cooling device for a gas turbine blade.

[0002]

2. Description of the Related Art FIG. 2 is a longitudinal sectional view of a main part of a conventional gas turbine. In the figure, 11 is a cooling air pipe, 12 is an intermediate shaft cover (stationary portion), 13 is an air separator, 14 is a rotor, 15 is a disk, 16 is a moving blade, and 17 is a shank portion of the same moving blade.

In this device, the cooling air cools a part of the air discharged from the compressor of the gas turbine, and the cooling air is supplied to a cooling air pipe 11.
To the gas turbine, and the intermediate shaft cover 12 (stationary part)
Is released to the part A. This cooling air is supplied to the intermediate shaft cover 1
2, a cylindrical air flow path D between the air separator 13 and the rotor 14 and a ring between the air separator 13 and the disc 15 through a hole C formed in the air separator 13 through a gap B provided in The air passes through the air flow path E from the shank portion 17 of the moving blade to the moving blade 16, where the blade and the platform are cooled, merges with the main gas, and escapes to the atmosphere on the exhaust side. A part cools the rotor 14 and the disk 15 and escapes to the air on the exhaust side.

[0004]

In a gas turbine, atmospheric air is sucked and compressed by a compressor, a part of which is cooled through a cooler, and then used as cooling air. However, fine dust passing through the filter at the time of intake is carried by the cooling air and enters the gas turbine. Therefore, dust enters the hollow cooling blades of the gas turbine and adheres to the projections of the turbulator and the bent portions of the serpentine flow path, thereby lowering the cooling performance of the blades.

The present invention solves the above-mentioned drawbacks of the prior art, removes dust before the cooling air reaches the blade, prevents dust from entering the hollow portion of the blade, and reduces the cooling performance of the blade. We are trying to prevent it.

[0006]

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and comprises a series of cylindrical air flow passages formed between an air separator and a rotor and between an air separator and a disk. In a gas turbine blade cooling device that introduces blade cooling air via the air flow path,
An annular convex portion provided on the outer surface of the rotor or the disk that constitutes the inner wall of the flow path so as to protrude radially outward, and air at a position facing the annular convex portion of the inner surface of the air separator that constitutes the outer wall of the flow path. An annular concave portion provided to cover the annular convex portion through a gap serving as a flow path, and a plurality of through holes having one end connected to the inner bottom portion of the annular concave portion and the other end connected to the outer peripheral side space of the air separator. The present invention relates to a cooling device for a gas turbine rotor blade provided with the cooling device.

[0007]

In the curved air flow path formed between the annular convex portion and the annular concave portion, dust is blown to the inner bottom portion of the annular concave portion by centrifugal force. Further, the cooling air containing dust is discharged to the outside by centrifugal force through a through hole connecting the inner bottom portion and the outer peripheral space of the air separator, so that the dust does not reach the rotor blades. Cooling air containing dust discharged to the outside of the air separator is carried to the main gas passage and discharged to the outside.

[0008]

FIG. 1 is a longitudinal sectional view of a main part of a gas turbine according to an embodiment of the present invention. In the figure, 1 is the disk 15
Are formed on the side of the ring-shaped portion, and the direction of the projection is radially outward. Numeral 2 is an annular concave portion formed so as to cover the annular convex portion at a position on the inner surface of the air separator 13 facing the annular convex portion via a gap serving as an air flow path. Reference numeral 3 denotes a gas passage formed between the intermediate shaft cover 12 and the air separator 13. Reference numeral 4 denotes a plurality of dust discharge holes communicating the annular recess 2 with the gas passage 3.
The configuration of other parts is the same as that of the related art.

In the present apparatus, the cooling air containing dust flowing into the cylindrical air flow path D between the air separator 13 and the rotor 14 flows in the flow path between the annular convex portion 1 and the annular concave portion 2. Is bent, is blown to the inner bottom portion of the annular concave portion by centrifugal force, and is discharged to the gas passage 3 by centrifugal force from a dust discharge hole 4 provided in the inner bottom portion. The cooling air containing dust discharged into the gas passage is carried to the main gas passage,
It is discharged to the exhaust side. On the other hand, the cooling air from which dust has been removed flows in the radial direction on the side of the disk 15, flows into the shank portion 17 of the moving blade, passes through the moving blade 16, cools the blade and the platform, and is discharged to the mainstream. .

[0010]

In the cooling device for a gas turbine rotor blade according to the present invention, an annular projection is provided on the outer surface of a rotor or a disk constituting the inner wall of the rotor blade cooling air introduction passage so as to protrude radially outward. An annular concave portion provided to cover the annular convex portion through a gap serving as an air flow passage at a position facing the annular convex portion on the inner surface of the air separator forming the outer wall of the flow channel; Since there are multiple through-holes connected to the inner bottom of the recess and the other end connected to the outer space of the air separator, dust can be prevented from entering the hollow part of the moving blade, preventing the cooling performance of the moving blade from deteriorating. can do.

[Brief description of the drawings]

FIG. 1 is a longitudinal sectional view of a main part of a gas turbine according to an embodiment of the present invention.

FIG. 2 is a longitudinal sectional view of a main part of a conventional gas turbine.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Annular convex part 2 Annular concave part 3 Gas passage 4 Dust discharge hole 11 Cooling air pipe 12 Intermediate shaft cover (stationary part) 13 Air separator 14 Rotor 15 Disk 16 Moving blade 17 Shank part

──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int.Cl. ⁷ , DB name) F02C 7/18 F01D 5/08-5/18

Claims (1)

(57) [Claims] A series of cylindrical air passages formed between an air separator and a rotor and between an air separator and a disk, and air for cooling a moving blade is introduced through the air passages. In the cooling device for a gas turbine rotor blade, an annular convex portion provided to protrude radially outward on an outer surface of a rotor or a disk constituting an inner wall of the flow path, an inner surface of an air separator constituting an outer wall of the flow path. An annular concave portion provided so as to cover the annular convex portion through a gap serving as an air flow path at a position facing the annular convex portion, and one end connected to the inner bottom portion of the annular concave portion and the other end on the outer side of the air separator A cooling device for a gas turbine blade comprising a plurality of through holes connected to a space.