JP2002031096A - Clearance regulation mechanism of compressor of gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a clearance regulation mechanism of a compressor of a gas turbine capable of regulating a clearance between an impeller blade of the compressor and a shroud without giving an influence to a clearance between a turbine blade of the turbine and a nozzle shroud. SOLUTION: A shroud part along the impeller blade of the compressor of the gas turbine is constituted of a separate member from a housing of the gas turbine, a fastening means to fasten the shroud part free to regulate a position in the longitudinal direction of an axis of rotation of the compressor against the housing is furnished, and the clearance between the shroud part and the impeller blade is regulated by the fastening means.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an adjusting mechanism for adjusting a clearance between a shroud forming an air passage of a compressor of a gas turbine and a rotating impeller blade.

[0002]

2. Description of the Related Art FIG. 4 is a vertical sectional side view of a conventional gas turbine 200. As shown in FIG. In the gas turbine 200, a rotating part of a compressor 90 and a turbine 91 are connected via a coupling 99, and the compressor 90 and the turbine 91 can rotate integrally about a rotation shaft 92.

[0003] The compressor 90 is provided with impeller blades 86 extending radially outward in the radial direction. A shroud 87 is provided in the housing 85. A clearance 81 is set between the shroud 87 and the impeller blade 86.

On the other hand, a turbine 91 is provided with a turbine blade 93. The nozzle 95 having the nozzle mounting flange and the nozzle shroud 94 are formed integrally, and the nozzle shroud 94 is fixed to the housing 98 by fixing the nozzle mounting flange portion to the housing 98 with bolts and nuts (not shown). Nozzle shroud 94
A clearance 82 is set between the turbine blade 93 and the turbine blade 93.

The order of adjusting the clearances 81 and 82 is as follows. First, the clearance 81 is adjusted and then the clearance 82 is adjusted. A compressor-side shim 96 is provided on the left side of a bearing 88 that supports a rotating part of the compressor 90, and the position of the shaft of the compressor 90 in the longitudinal direction is adjusted by the thickness of the compressor-side shim 96. The clearance 81 is set by adjusting the position of the axis of the compressor 90 in the longitudinal direction. At this time, the position of the turbine 91 integrated with the compressor 90 is also changed.

After setting the clearance 81, a turbine shim 97 is disposed between the nozzle 95 and the housing 98, and the nozzle 95 is fixed to the housing 98. And the clearance 82 between the turbine blade 93 and the nozzle shroud 94 is adjusted.

As described above, conventionally, when adjusting the clearance 81, the compressor 90 and the turbine 91 have a rotating shaft 92.
Since the entire rotating part that rotates around the center moves,
After adjusting the clearance 81, the clearance 82
Had to adjust.

[0008]

According to the present invention, the compressor 9
An object of the present invention is to provide a clearance adjustment mechanism of a compressor of a gas turbine, which can adjust a zero-side clearance 81 without affecting a clearance 82 between a turbine blade 93 and a nozzle shroud 94.

[0009]

According to the present invention, a shroud portion along an impeller blade of a compressor of a gas turbine is formed of a separate member from a housing of the gas turbine. Fixing means is provided for fixing the position of the rotary shaft of the compressor in the longitudinal direction to the housing in an adjustable manner, and the clearance between the shroud portion and the impeller blades can be adjusted by the fixing means.

[0010]

FIG. 1 shows a gas turbine 1 according to the present invention.
FIG. In FIG. 1, the gas turbine 1
Reference numeral 00 includes a turbine 6 that rotates around a rotation shaft 7 and a compressor 5 (rotating part 5 a) connected to the turbine 6 by a coupling 11.

The compressor 5 is provided with a plurality of impeller blades 2 (only one of which is shown in FIG. 1) extending radially outward. Further, a shroud 3 forming an outer peripheral wall of an annular air passage 25 of the compressor 5 is fixed to the housing 1 as described later in detail.

The turbine 6 is provided with a plurality of turbine blades 8 (only one of them is shown in FIG. 1) extending radially outward. A nozzle shroud 9 forming an outer peripheral wall of an annular passage of combustion gas 15 for driving the turbine 6 is integrally fixed to the nozzle 10, and the nozzle 1
The nozzle shroud 9 is fixed to the housing 22 by fixing the 0 mounting flange 10a to the housing 22 with bolts (not shown).

The air flow 13 that has flowed into the compressor 5 from the air passage 25 passes through the diffuser 12 and is compressed to produce compressed air 14, which burns with fuel in a combustor 16. To generate the combustion gas 15. The combustion gas 15 is accelerated by the nozzle 10, and the turbine 6 is driven by the accelerated combustion gas 15.

The clearance 21 between the turbine blade 8 and the nozzle shroud 9 has a great effect on the efficiency of the operation of the turbine 6. The turbine blade 8 collides with the nozzle shroud 9.

Therefore, the nozzle 1 is
Nozzle 10 and mounting flange 10a at the intersection of dimensions such that clearance 21 when 0 is fixed is within an appropriate range.
And the nozzle shroud 9 are integrally formed. Then, just by fixing the nozzle 10 (the mounting flange 10 a) to the housing 22, the clearance 21 is set within an appropriate range.

FIG. 2 is an enlarged view of a portion A in FIG. As shown in FIG. 2, the housing 1 has an annular inward flange 1a. Further, the shroud 3 is provided with a flange 3a which is annularly outward and faces the flange 1a.

The flange 1a has a through hole 1b, and the flange 3a has a screw hole 3b. The bolts 17 are passed through the flange 1a side and screwed into the screw holes 3b to integrally fix the flange 1a and the flange 3a. Such a bolt 17 is, for example,
Provided at zero locations.

A shim 1 is provided between the flange 1a and the flange 3a.
8 is interposed. As the thickness of the shim 18 increases, the fixed position of the shroud 3 with respect to the housing 1 moves to the right as viewed in FIG. 2, and the clearance 20 between the shroud 3 and the impeller blade 2 can be set smaller. Conversely, decreasing the thickness of shim 18 increases clearance 20.

When the clearance 20 is adjusted as described above, the position of the rotating part 5a of the compressor 5 (FIG. 1) does not change, so that the position of the turbine 6 (turbine blade 8) does not change, and the clearance 21 does not change. Does not fluctuate. Therefore, there is no need to adjust the clearance 21 after adjusting the clearance 20 as in the related art.

As shown in FIG. 2, the provision of the shim 18 causes the flange 3a of the shroud 3 to project toward the turbine 6 (FIG. 1). Diffuser wing 12
a of the inner periphery of the inner peripheral end of the impeller blade 2 and the outer periphery of the outer peripheral end of the impeller blade 2).
a can be prevented from interfering with the diffuser blade 12a. The shim 18 has a flange 1a and a flange 3a.
May be formed in an annular shape, or may be divided and arranged at any position on the circumference.

FIG. 3 is an enlarged sectional view of a portion A of FIG. 1 showing a modification of FIG. In FIG. 3, the thickness of either the flange 1a or the flange 3a is smaller than in the case of FIG. Therefore, the shim 18 is connected to the flange 1
Even if it is provided between the flange 3a and the flange 3a, the flange 3a and the diffuser blade 12a do not interfere with each other. Flange 1a
The thickness of both the flange 3a and the flange 3a may be set smaller (thinner) than in the case of FIG.

[0022]

The clearance 20 (impeller blade 2) shown in FIG.
And the shroud 3) are required to have a stricter dimension than the clearance 21 (between the turbine blade 8 and the nozzle shroud 9). In this way, the position of the rotating part of the compressor 5 and the turbine 6 is changed. Since the clearance 20 can be adjusted without performing the above operation, it is not necessary to set the clearance 21 again, and the number of assembling steps of the gas turbine 100 can be reduced.

[Brief description of the drawings]

FIG. 1 is a longitudinal sectional side view of a gas turbine of the present invention.

FIG. 2 is an enlarged sectional view of a portion A in FIG.

FIG. 3 is an enlarged sectional view of a portion A of FIG. 1 showing a modification of FIG. 2;

FIG. 4 is a vertical side view of a conventional gas turbine.

[Explanation of symbols]

 Reference Signs List 1 housing 1a flange 2 impeller blade 3 shroud 3a flange 4 bearing 5 compressor 6 turbine 7 rotating shaft 8 turbine blade 9 nozzle shroud 10 nozzle 11 coupling 12 diffuser 12a diffuser blade 13 air flow 17 bolt (fixing means) 18 shim 18 shim Reference Signs List 20 Clearance (compressor side) 21 Clearance (turbine side) 22 Housing 100 Gas turbine

Claims (1)

[Claims] A shroud portion along an impeller blade of a compressor of a gas turbine is formed of a member separate from a housing of the gas turbine, and the shroud portion is formed with respect to the housing in a longitudinal direction of a rotation axis of the compressor. A clearance adjusting mechanism for a compressor of a gas turbine, comprising: fixing means for fixing a position so as to be adjustable, wherein the fixing means can adjust a clearance between the shroud portion and the impeller blade.