KR101608130B1 - Gas turbine having blade tip clerance control means and controlling method for the same - Google Patents

Abstract

The present invention is configured such that the rotor shaft is movable in the direction of the rotational axis for adjusting the clearance between the front end of the turbine blade and the blade vane carrier is movable in the direction of the rotational axis in order to adjust the clearance of the front end of the compressor blade when the rotor shaft is moved, To a gas turbine capable of adjusting the tip clearance and a control method thereof.

Description

TECHNICAL FIELD [0001] The present invention relates to a gas turbine having blade tip gap adjusting means, and a control method thereof. [0002]

The present invention relates to a gas turbine and a control method thereof, and more particularly, to a gas turbine in which a rotor shaft is horizontally movable in the direction of a rotary shaft for adjusting the clearance of a turbine blade tip, The present invention relates to a gas turbine and a control method thereof, in which a blade vane carrier is configured to be movable in a rotational axis direction.

 BACKGROUND ART Generally, a gas turbine is an internal combustion engine that converts heat energy into mechanical energy by rotating a turbine portion by injecting high-temperature, high-pressure combustion gas generated by mixing fuel into air compressed at a high pressure in a compressor section and turbine blades of a turbine section, .

Generally, the compressor unit is constituted by arranging a plurality of compressor rotor disks having a plurality of compressor blades arranged on the outer circumferential surface in a plurality of stages, and the turbine unit comprises a plurality of turbine rotor disks having a plurality of turbine blades arranged on the outer circumferential surface, Respectively.

At this time, a front end portion of the compressor blade and a front end portion of the turbine blade are disposed so as to surround a stop member such as a housing to constitute a flow path of compressed air and a flow path of the combustion gas, and a gap between the tip end portion of the compressor blade and the stop member, It is known that leakage through the gap between the leading end of the gas turbine and the stationary member has a significant effect on the efficiency of the entire gas turbine.

In order to improve the efficiency of the gas turbine by reducing the amount of leakage of the compressed air and the combustion gas by reducing the gap, there have been proposed various methods for improving the efficiency of the gas turbine. Especially, the tip of the turbine blade exposed to the high- A method for solving the problem of efficiency reduction caused by the gap between them exceeding the initially set gap range has been proposed.

In this connection, U.S. Patent Publication No. 20100247283A1 discloses a compressor having a compressor 1, a combustor 2, and a plurality of turbine blades 3a each having a plurality of compressor blades 1a as shown in Fig. 1 The compressor blade (1a) and the turbine blade (3a) are arranged on the outer circumferential surface of a rotor shaft (4) extending from the compressor section (1) to the turbine section (3) The rotor shaft 4 is horizontally moved in the rotational axis direction 6 using a separate actuator not shown in order to adjust the clearance between the front end of the turbine blade 3a and the housing 5 during operation A gas turbine 10 has been proposed.

2 (a), a clearance Dt1 between the tip end of the turbine blade 3a and the inner circumferential surface 5a of the housing 5 during operation of the gas turbine 1, The rotor shaft 4 is forcibly moved in the rotational axis direction 6 so that the tip end of the turbine blade 3a and the inner circumferential surface 5a of the housing 5 are adjusted to be the optimum gap Dt2, The efficiency of the fuel cell 1 can be improved.

However, as the rotor shaft 4 is moved in the direction of the rotational axis 6, the compressor blade 1a, which is likewise forcedly connected to the rotor shaft 4, also rotates in the rotational axis direction 6 as much as the turbine blade 3a is moved .

The clearance Dc1 between the tip end of the compressor blade 1a and the inner circumferential surface 5a of the housing 5 which has been previously set optimally is widened to a wider gap Dc2 with the movement of the rotor shaft 4 The compressed air leaks into the enlarged clearance Dc2, and the efficiency of the compressor 1 is lowered. Further, the efficiency of the entire gas turbine 1 is reduced.

Such problems are caused by the shape of the inner circumferential surface of the housing or the stationary member constituting the flow path of the compressed air or the combustion gas, the shape of the turbine blade tip, and the shape of the tip of the compressor blade.

That is, the compressor unit is configured such that the cross-sectional area of the air flow path to be compressed in order to compress the inflow air flows in the flow direction of the air and is reduced in blinking. The turbine unit is configured to reduce the energy generated by the expansion of the high- In order to convert the combustion gas, the cross-sectional area of the flow path gradually increases as the combustion gas proceeds in the flow direction.

Accordingly, the shape of the inner circumferential surface of the housing or the stop member of the compressor portion constituting the compressed air passage is configured such that the inner diameter thereof gradually decreases while proceeding in the direction of air flow, and the housing of the turbine portion constituting the flow path of the combustion gas, The shape of the inner circumferential surface of the member is generally formed in such a shape that the inner diameter gradually increases in the flow direction of the combustion gas.

 Therefore, as described in the above-mentioned prior art, a configuration in which the entire rotor shaft is moved in order to adjust the clearance of the turbine blade tip can not avoid the problem that the clearance at the tip of the compressor blade becomes wider.

US Patent Publication No. US20020247283A1

SUMMARY OF THE INVENTION The present invention has been made in order to solve the above-mentioned problems, and it is an object of the present invention to provide a turbine blade having a means for forcibly moving a rotor shaft for adjusting a clearance of a turbine blade, And a control method thereof.

It is still another object of the present invention to provide a gas turbine capable of optimally adjusting the clearance of the tip of a compressor blade by using a tip timing sensor capable of measuring and sensing the gap between the tip of the compressor blade and the stop member .

A gas turbine according to the present invention includes: a compressor rotor portion in which a plurality of compressor blades are arranged in multiple stages and arranged to be movable in a rotation axis direction; A housing for receiving the compressor rotor portion; A vane carrier disposed between the housing and the compressor blades, the vane carrier having a plurality of compressor vanes arranged in an inner peripheral surface in a plurality of stages; A carrier shift actuator connected to the housing and horizontally moving at least a part of the vane carrier in the direction of the rotation axis; At least one tip timing sensor attached to the vane carrier for measuring a gap between a leading end of the compressor blade and an inner circumferential surface of the vane carrier; And a control unit for controlling operation of the carrier shift actuator, wherein the at least one tip timing sensor includes a first tip timing sensor and a second tip timing sensor disposed apart from each other in the direction of the rotation axis, Wherein the first tip timing sensor is disposed further upstream than the second tip timing sensor in the flow direction of the air to be compressed by the blade, and the control unit controls the first tip timing sensor after at least a portion of the vane carrier is moved A signal for the first measurement gap measured by the first tip timing sensor and a signal for the second measurement gap measured by the two tip timing sensor are received.
At least a part of the vane carrier horizontally moved by the carrier shift actuator may have a shape in which the inner diameter of the inner circumferential surface progressively decreases in the direction of the rotation axis.
An inclination angle between the inner peripheral surface of the second vane carrier and the rotation axis at a position where the first tip timing sensor is disposed and an inclination angle between the inner peripheral surface of the second vane carrier and the rotation axis at a position where the second tip timing sensor is disposed, Are different from each other.
And a rotor shift actuator for horizontally moving the compressor rotor section in the direction of the rotational axis, and the control section can control the operation of the rotor shift actuator.
Wherein the control unit controls the rotor shift actuator to horizontally move the compressor rotor unit in accordance with a predetermined axial movement amount and controls the carrier shift actuator to horizontally move at least a part of the vane carrier in accordance with the set axial movement amount Can be controlled.
And the control unit determines whether the first measurement gap and the second measurement gap fall within a predetermined allowable range.
The control unit may control the carrier shift actuator to operate when at least one of the first measurement clearance and the second measurement clearance does not fall within the predetermined allowable range.
(S1) horizontally moving the compressor rotor portion in which a plurality of compressor blades are arranged in multiple stages in the rotational axis direction; Setting (S2) an axial movement amount of at least a part of a vane carrier arranged between the housing for accommodating the compressor rotor portion and the compressor blades and having a plurality of compressor vanes arranged in a multi-stage on an inner peripheral surface thereof; Horizontally moving at least a part of the vane carrier in the direction of the rotation axis (S3); (S4) measuring a gap between a leading end of the compressor blade and an inner circumferential surface of at least a part of the vane carrier using a first tip timing sensor attached to the vane carrier; Measuring a gap between the tip of the compressor blade and the inner circumferential surface of at least a portion of the vane carrier using a second tip timing sensor disposed further upstream from the first tip timing sensor, S5); And determining (S6) whether or not the first measurement gap measured by the first tip timing sensor and the second measurement gap measured by the second tip timing sensor in the step S5 are within a preset allowable range, . ≪ / RTI >
Resetting an axial movement amount of at least a portion of the vane carrier if at least one of the first measurement gap and the second measurement gap does not fall within the predetermined allowable range; In the direction of the rotation axis.

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The gas turbine and the control method thereof according to the present invention can actively control the gap between the front end of the compressor blade and the front end of the compressor blade due to the movement of the rotor shaft, thereby increasing the efficiency of the entire gas turbine.

Further, by using a tip timing sensor capable of measuring and detecting the gap between the tip of the compressor blade and the stop member, the gap of the tip of the compressor blade can be actively controlled in an optimal state by the gas turbine and the control method thereof according to the present invention .

1 is a schematic diagram of a gas turbine with a turbine blade clearance configuration in accordance with the prior art.
Fig. 2 (a) is a schematic view for explaining a configuration in which the gap of the turbine blade tip is adjusted according to the gap adjustment structure shown in Fig. 1, and Fig. 2 (b) Is a schematic view for explaining a phenomenon in which the gap of the tip portion is widened.
3 is a cross-sectional view of a gas turbine including a gap adjustment configuration of a compressor blade tip according to an embodiment of the present invention.
Fig. 4 and Fig. 5 are partial enlarged views of the gas turbine shown in Fig. 3 for explaining a state in which a clearance at the tip of the compressor blade is open. Fig.
Figs. 6 and 7 are partial enlarged views of the gas turbine shown in Fig. 3, which illustrate a state in which the gap adjustment of the compressor blade front end is completed.
FIG. 8 is a functional block diagram for explaining a gap control system for a front end of a turbine blade and a front end of a compressor blade according to an embodiment of the present invention.
9 is a flowchart for explaining a method of adjusting the gap between the tip of the turbine blade and the tip of the compressor blade according to an embodiment of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings.

While the invention is susceptible to various modifications and alternative forms, specific embodiments thereof are shown by way of example in the drawings and will herein be described in detail. It is to be understood that the present invention is not intended to be limited to the specific embodiments but includes all changes, equivalents, and alternatives included in the spirit and scope of the present invention.

In describing the present invention, the terms first, second, etc. may be used to describe various components, but the components may not be limited by the terms. The terms are only for the purpose of distinguishing one component from another. For example, without departing from the scope of the present invention, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component.

It is to be understood that when an element is referred to as being connected or connected to another element, it may be directly connected or connected to the other element, but it may be understood that other elements may be present in between . On the other hand, when it is mentioned that an element is directly connected to or directly connected to another element, it can be understood that there is no other element in between.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The singular expressions may include plural expressions unless the context clearly dictates otherwise.

It is to be understood that the term " comprising, " or " comprising " as used herein is intended to specify the presence of stated features, integers, But do not preclude the presence or addition of steps, operations, elements, components, or combinations thereof.

Also, unless otherwise defined, all terms used herein, including technical or scientific terms, may have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs . Terms such as those defined in commonly used dictionaries can be interpreted as having a meaning consistent with the meaning in the context of the related art and, unless explicitly defined herein, are interpreted in an ideal or overly formal sense .

In addition, the following embodiments are provided so as to explain the invention more clearly to those skilled in the art. The shapes and sizes of the elements in the drawings may be exaggerated for clarity.

3 is a cross-sectional view of a gas turbine 100 including a gap adjustment configuration of the tip of a compressor blade 11 according to an embodiment of the present invention.

3, a gas turbine 100 according to an exemplary embodiment of the present invention includes a plurality of compressor blades 11 arranged in a plurality of stages in a plurality of compressor rotor discs 12, A plurality of compressor vanes 13 are disposed in the inner circumferential surface of the housing 20 and a plurality of compressor vanes 13 are disposed in a multi- A carrier shift actuator 30 connected to the housing 20 for horizontally moving at least a part of the vane carrier 14 in the direction of the rotation axis X-X ', and a carrier- And at least one tip timing sensor for measuring the gap between the tip of the compressor blade (11) and the inner circumferential surface of the vane carrier (14).

The gas turbine according to the present invention is configured such that the rotor shaft is horizontally moved in the direction of the rotational axis for the purpose of adjusting the clearance of the leading end of the turbine blade, similar to the configuration of the prior art described above.

The present invention relates to a turbine rotor portion having a turbine rotor disk on which turbine blades are arranged, a configuration relating to a rotor shaft including the turbine rotor portion, and a detailed configuration relating to a rotor shift actuator for horizontally moving the rotor shaft in the direction of the axis of rotation May be applied to the present invention without any limitations, and a description of portions overlapping with those of the prior art will be omitted.

In order to solve the problem that the gap between the ends of the compressor blades 11 is further increased by moving the entire portion of the rotor shaft in order to adjust the clearance between the ends of the turbine blades, At least a part of the vane carrier (14) in which a clearance is formed between the front ends of the compressor blades (11) is configured to be movable in the direction in which the compressor rotor section is horizontally moved. That is, the vane carrier 14 according to the present invention may be configured to be horizontally movable as a whole, or may be configured to be horizontally movable only at a portion thereof.

3 shows an embodiment in which a part of the vane carrier 14 is horizontally movable as described above. Hereinafter, an embodiment in which only a part of the vane carrier 14 is configured to be horizontally movable will be described . It should be understood, however, that the entire configuration of the vane carrier 14 as described above can be horizontally moved also belongs to the scope of the present invention.

3, the vane carrier 14 includes a first vane carrier 14a fixed to the housing 20, and a second vane carrier 14b fixed to the housing 20, The first vane carrier 14a and the second vane carrier 14b are configured to include a second vane carrier 14b as at least a portion configured to be movable by the carrier shift actuator 30 so that the first vane carrier 14a and the second vane carrier 14b are separated from each other The second vane carrier 14b is horizontally moved by the carrier shift actuator 30 in the direction of the rotation axis X-X ', that is, in the direction in which the compressor rotor portion is horizontally moved.

That is, the vane carrier 14 according to the present invention is illustratively provided on the upstream side in the flow direction so as to constitute the vane carrier 14 such that the cross-sectional area of the flow passage is gradually reduced while progressing in the flow direction while forming a flow path of air to be compressed, A first vane carrier 14a having an inner circumferential surface extending in the direction of the rotation axis X-X 'and kept substantially constant in the circumferential direction, an inner diameter of a cylindrical inner circumferential surface provided on the downstream side in the flow direction, And a second vane carrier 14b having a shape that progressively decreases in the X 'direction.

At this time, as shown in FIG. 3, a second vane carrier (hereinafter, referred to as a " second vane ") which is subjected to a greater influence on the gap (11a in Fig. 4) of the compressor blade 11 by the movement of the compressor rotor portion in the direction of the rotation axis 14b can be formed as a part that is moved in the direction of the rotation axis X-X 'by the carrier shift actuator 30 to reduce the size of the carrier shift actuator 30 and the movement of the second vane carrier 14b The load capacity of the necessary carrier shift actuator 30 can be reduced.

The carrier-shift actuator 30 is rigidly fixed and connected to the housing 20 and rotatably supports the second vane carrier 14b in the direction of the axis of rotation X-X ', more specifically, horizontally .

The carrier shift actuator 30 can be applied without limitation as long as it can horizontally move the second vane carrier 14b in the direction of the rotation axis X-X 'in accordance with a control signal of a control unit described later in detail , Preferably a hydraulic actuator, an electric actuator, or the like may be applied.

Fig. 3 shows an embodiment in which a hydraulically operated carrier shift actuator 30 is applied. The connecting portion 14b-1 of the second vane carrier 14b extending in the direction perpendicular to the rotation axis X-X ' And the second vane carrier 14b is advanced and retracted in the direction of the rotation axis X-X '(the direction of the arrow in Fig. 3) by pressurizing both side surfaces of the second vane carrier 14b using two pistons that hydraulically drive both sides.

At least one tip timing sensor 40 for measuring the clearance between the leading end of the compressor blade 11 and the inner circumferential surface of the vane carrier 14, more specifically the inner circumferential surface of the second vane carrier 14b, (14b).

The at least one tip timing sensor 40 measures the clearance of the tip of the compressor blade 11 after the second vane carrier 14b is moved in the direction of the rotation axis X-X ' It is a role to deliver.

The tip timing sensor 40 according to the present invention is not particularly limited as long as it can measure the clearance between the tip end of the compressor blade 11 and the inner peripheral surface of the second vane carrier 14b And may be provided as at least a first tip timing sensor 41 and a second tip timing sensor 42 disposed apart from each other in the direction of the rotation axis X-X ', and the compressor blade The first tip timing sensor 41 is disposed further upstream than the second tip timing sensor 42 in the flow direction of the air to be compressed by the first tip timing sensor 11.

More specifically, the position in the direction of the rotation axis (X-X ') where the first tip timing sensor 41 is disposed and the position in the direction of the rotation axis (X-X') where the second tip timing sensor 42 is disposed are different from each other (See FIG. 4 and FIG. 6 (a)) between the inner peripheral surface of the second vane carrier 14b and the rotation axis X-X 'at a position where the first tip timing sensor 41 is disposed, (A2 in Fig. 5 and Fig. 7) between the inner peripheral surface of the second vane carrier 14b and the rotation axis X-X 'at a position where the second tip timing sensor 42 is disposed, Are different from each other.

The horizontal movement of the second vane carrier 14b in the direction of the rotation axis X-X 'causes the gap between the front end of the compressor blade 11 and the inner peripheral surface of the second vane carrier 14b to be different from each other By arranging the first tip timing sensor 41 and the second tip timing sensor 42 respectively, more accurate gap adjustment and control are possible.

Fig. 4 is an enlarged view of the position where the first tip timing sensor 41 is disposed, Fig. 5 is an enlarged view of the second tip timing sensor 42 And is a view for explaining a state in which the gap between the tip 11a of the compressor blade 11 is open.

4 and 5, a rotor shift actuator (not shown) is operated so that the rotor shaft is horizontally moved in the direction of the rotational axis, specifically in the left direction in the figure, so that the rear end is forced to the compressor rotor disk The connected compressor blades 11 are also moved in the left direction of the drawing.

The inner peripheral surface 14b-2 of the second vane carrier 14b to which the rear end portion 13b of the compressor vane 13 is fixed and connected is configured to have constant inclination angles a1 and a2 with respect to the rotation axis direction, The tip 11a of the compressor 11 is configured to have a shape corresponding to the shape of the inner circumferential surface 14b-2 of the second vane carrier 14b. Therefore, the compressor blade 11, The gap between the front end portion 11a and the inner circumferential surface 14b-2 of the second vane carrier 14b is gradually widened in proportion to the amount of movement of the compressor rotor disk, The maximum gaps Da1 and Db1 are formed in the gaps D1 and Db1 and the compressed air leaks to the gaps Da1 and Db1.

In this case, the inclination angle a1 of the inner peripheral surface 14b-2 of the second vane carrier 14b and the position of the second tip timing sensor 42 at the position where the first tip timing sensor 41 is disposed Since the inclination angles a2 of the inner peripheral surface 14b-2 of the second vane carrier 14b are different from each other, the maximum gap Da1 at the position where the first tip timing sensor 41 is disposed and the maximum gap Da1 at the second tip timing sensor 42 may be different from each other.

On the other hand, since the front end portion 13a of the compressor vane 13 having the seal portion for preventing the leakage of the compressed air is configured to be substantially parallel to the rotation axis similarly to the shape of the outer peripheral surface of the adjacent compressor rotor , The clearance between them is hardly affected by the movement of the rotor shaft in the direction of the rotation axis.

4 is an enlarged view of the position where the first tip timing sensor 41 is disposed, and FIG. 5 is an enlarged view of the second tip timing sensor 42 In which the gap adjustment of the tip 11a of the compressor blade 11 is completed. As shown in Fig.

Referring to Figs. 6 and 7, in order to reduce the gap between the tip 11a of the compressor blade 11 that is maximally formed, the above-described carrier shift actuator is operated in accordance with a control signal of a control section described later.

More specifically, the control unit controls the rotor shift actuator to horizontally move the compressor rotor unit according to a preset rotational axis direction movement amount, and controls the rotor shift actuator to move the second vane carrier 14b horizontally And is configured to control the carrier shift actuator.

At this time, the first tip timing sensor 41 and the second tip timing sensor 42 are located at the positions respectively disposed in real time from the point of time when the second vane carrier 14b starts to move, 11a and measures the gap between the measurement gaps and transmits the measurement gaps to the control unit.

The control unit determines whether the first measurement gap transmitted from the first tip timing sensor 41 and the second measurement gap transmitted from the second tip timing sensor belong to a preset allowable range, In particular, it is determined whether the first measurement gap and the second measurement gap fall within the allowable range after the movement of the second vane carrier 14b is completed in accordance with the rotational movement amount.

If at least one of the first measurement gap and the second measurement gap does not fall within the predetermined allowable range according to the determination result, the control unit transmits a control signal for reactivating the carrier shift actuator to the carrier shift actuator So that the gas turbine according to the present invention is automatically controlled so that the predetermined optimum gap Da2, Db2 is formed at the tip of the compressor blade 11.

FIG. 8 is a functional block diagram for explaining a gap control system of a front end of a turbine blade and a front end portion 11a of a compressor blade 11 according to an embodiment of the present invention, and FIG. 9 is a functional block diagram of a turbine And a method for adjusting the gap between the tip of the blade and the tip 11a of the compressor blade 11 is described.

8 and 9, the user inputs a control command to the controller 50 through the terminal device 200 electrically connected to the controller 50 to horizontally move the lips in the direction of the rotational axis by the rotor including the compressor rotor And the control unit 50 transmits a control signal for driving the rotor shift actuator 60 to the rotor shift actuator 60 in accordance with the control command.

Accordingly, step (S1) of horizontally moving the compressor rotor part in the direction of the rotation axis proceeds.

Next, the control unit 50 sets the amount of movement of the second vane carrier 14b in the direction of the rotation axis in accordance with the horizontal movement of the compressor rotor unit (S2), and controls to horizontally move the second vane carrier 14b in the direction of the rotation axis The movement of the second vane carrier 14b in the direction of the rotation axis is started (S3) by passing a signal to the carrier shift actuator 30 so that the gap between the tip 11a of the compressor blade 11 opened by the horizontal movement of the compressor rotor portion is gradually narrowed .

Next, the gap between the tip 11a of the compressor blade 11 and the inner circumferential surface of the second vane carrier 14b is measured (S4) using the first tip timing sensor 41, and the gap between the compressor blade 11 The gap between the tip 11a of the first vane carrier 14b and the inner circumferential surface of the second vane carrier 14b is measured using the second tip timing sensor 42 and acquired using the first tip timing sensor 41 And the second measurement gap obtained using the second tip timing sensor 42 are transmitted to the control unit 50. [

Next, the control unit 50 determines whether the first measurement gap and the second measurement gap fall within a preset allowable range (S6), and if the first measurement gap and the second measurement gap are within the predetermined allowable range , And if the at least one of the first measurement clearance and the second measurement clearance does not fall within the preset allowable range, then the step of setting the movement amount of the second vane carrier (14b) in the rotation axis direction (S2), and transmits a control signal to the carrier shift actuator (30) for horizontally moving the second vane carrier (14b) in the direction of the rotational axis according to the reset moving amount to return the second vane carrier The carrier 14b is further moved in the direction of the rotation axis (S3).

After the further moving step, the gap of the tip 11a of the compressor blade 11 is measured using the first tip timing sensor 41, the step (S4) of measuring the gap of the tip 11a of the compressor blade 11, (S5) of measuring a gap using the second tip timing sensor (42), and a step (S6) of determining whether or not the first measurement gap and the second measurement gap fall within a preset allowable range are repeated do.

As described above, it is to be understood that the technical structure of the present invention can be embodied in other specific forms without departing from the spirit and essential characteristics of the present invention.

It should be understood, therefore, that the embodiments described above are to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than the foregoing description, And all changes or modifications derived from the equivalents thereof should be construed as being included within the scope of the present invention.

Claims (17)

A plurality of compressor blades are arranged in multiple stages and are arranged movably in the direction of the axis of rotation;
A housing for receiving the compressor rotor portion;
A vane carrier disposed between the housing and the compressor blades, the vane carrier having a plurality of compressor vanes arranged in an inner peripheral surface in a plurality of stages;
A carrier shift actuator connected to the housing and horizontally moving at least a part of the vane carrier in the direction of the rotation axis;
At least one tip timing sensor attached to the vane carrier for measuring a gap between a leading end of the compressor blade and an inner circumferential surface of the vane carrier; And
And a control unit for controlling operation of the carrier shift actuator,
Wherein the at least one tip timing sensor comprises:
Wherein the first tip timing sensor and the second tip timing sensor are spaced apart from each other in the direction of the rotation axis, and wherein the first tip timing sensor is disposed in the flow direction of the air to be compressed by the compressor blade More upstream,
Wherein the controller is configured to control the first tip gap and the second tip gap in such a manner that at least a portion of the vane carrier is moved in accordance with the rotational movement amount, Gt; a < / RTI > signal is received. The method according to claim 1,
Wherein at least a part of the vane carrier horizontally moved by the carrier shift actuator is configured to have a shape in which an inner diameter of an inner circumferential surface gradually decreases in a direction of the rotational axis. delete delete The method according to claim 1,
Wherein the vane carrier includes a first vane carrier fixed to the housing and a second vane carrier at least a portion configured to be movable by the carrier shift actuator,
An inclination angle between the inner peripheral surface of the second vane carrier and the rotation axis at a position where the first tip timing sensor is disposed,
Wherein an inclination angle between an inner circumferential surface of the second vane carrier and the rotation axis is different at a position where the second tip timing sensor is disposed. delete The method according to claim 1,
Further comprising a rotor shift actuator for horizontally moving the compressor rotor portion in the rotational axis direction,
And the control unit controls operation of the rotor shift actuator. 8. The method of claim 7,
Wherein the control unit controls the rotor shift actuator to horizontally move the compressor rotor unit in accordance with a predetermined axial movement amount and controls the carrier shift actuator to horizontally move at least a part of the vane carrier in accordance with the set axial movement amount Wherein the gas turbine is a gas turbine. delete The method according to claim 1,
Wherein the control unit determines whether the first measurement gap and the second measurement gap fall within a preset allowable range. 11. The method of claim 10,
Wherein the control unit controls the carrier shift actuator to operate when at least one of the first measurement clearance and the second measurement clearance does not fall within the predetermined allowable range. (S1) horizontally moving the compressor rotor portion in which a plurality of compressor blades are arranged in multiple stages in the rotational axis direction;
Setting (S2) an axial movement amount of at least a part of a vane carrier arranged between the housing for accommodating the compressor rotor part and the compressor blade and having a plurality of compressor vanes arranged in a multi-stage on an inner peripheral surface thereof;
Horizontally moving at least a part of the vane carrier in the direction of the rotation axis (S3);
(S4) measuring a gap between a leading end of the compressor blade and an inner circumferential surface of at least a part of the vane carrier using a first tip timing sensor attached to the vane carrier;
Measuring a gap between the tip of the compressor blade and the inner circumferential surface of at least a portion of the vane carrier using a second tip timing sensor disposed further upstream from the first tip timing sensor, S5); And
Determining (S6) whether or not the first measurement gap measured by the first tip timing sensor and the second measurement gap measured by the second tip timing sensor in the step S5 are within a predetermined allowable range And controlling the flow of the gas turbine. delete delete delete delete 13. The method of claim 12,
Resetting an axial movement amount of at least a portion of the vane carrier if at least one of the first measurement gap and the second measurement gap does not fall within the predetermined allowable range; And moving the gas turbine horizontally in the direction of the axis of rotation according to the rotational direction of the gas turbine.

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