KR20190113028A - Control method of gas turbine and gas turbine - Google Patents

Abstract

A gas turbine and a control method thereof are disclosed. According to an embodiment of the present invention, the gas turbine can be stably operated by detecting vibration generated in a compressor blade provided in a compressor and controlling vibration before or after generation of a stall.

Description

Gas turbine and its control method {Control method of gas turbine and gas turbine}

The present invention relates to controlling a vibration generated in a compressor blade provided in a compressor of a gas turbine, and more particularly, to a gas turbine for controlling stall generation of a compressor blade and a control method thereof.

In general, a turbine is a power generating device that converts thermal energy of a fluid such as gas or steam into rotational force, which is mechanical energy, and includes a rotor including a plurality of buckets to be axially rotated by the fluid. It includes a rotor and a casing installed around the rotor and provided with a plurality of diaphragms.

The gas turbine comprises a compressor section, a combustor and a turbine section, the outside air is sucked and compressed by the rotation of the compressor section and then sent to the combustor, where combustion occurs by mixing compressed air and fuel in the combustor.

The combustion state generated in the combustor is an isothermal heating process, the combustion gas temperature is raised to a temperature that the turbine metal can withstand. The gas turbine combustor corresponds to a part that serves to drive the turbine by reacting the high temperature and high pressure air from the compressor with the fuel to have high energy and transferring the same to the turbine.

The combustor installed in the gas turbine burns the high pressure air supplied from the compressor to generate a high temperature and high pressure combustion gas and supplies it to the turbine.

The compressor has a plurality of stages. Recently, the blades constituting the initial stage of the compressor are gradually increasing in size. In addition, the blade is thin in thickness and the attack angle (attack angle) of each blade is configured differently, the vibration is generated while the Mach number generated at the tip exceeds one.

For example, since the vibration of the initial stage of the above-mentioned compressor increases as the moving speed of the fluid moving through the blade increases, it is important to monitor the stability of the stable operation and long-term use.

In addition, the gas turbine is compressed in multiple stages in a plurality of compressor stages constituting the compressor when starting. In this case, when one of the initial compressors constituting the compressor stage maintains an abnormal state of the pressure ratio, surge due to a stall is generated, which may cause shock and abnormal sounds in the gas turbine.

The stall occurs due to improper engine control in the engine acceleration section or load operating region of the gas turbine or as the gap of the tip decreases due to long term operation.

In this case, the compressor blade is damaged or damaged by repeated loads. For example, plastic deformation is accompanied when the maximum value of the stress applied to the compressor blade is greater than the yield point of the material constituting the compressor blade.

In addition, when the stress of the compressor blade is repeatedly repeated at the yield point or more, the compressor blade eventually breaks, and thus, a necessity for actively controlling breakage by actively detecting breakage caused by vibration is required.

Republic of Korea Patent Publication No. 10-2018-000214

Embodiments of the present invention provide a gas turbine and a control method thereof for preventing a compressor blade from being damaged due to vibration or from damage to a component of a gas turbine due to the vibration.

Gas turbine according to an embodiment of the present invention comprises a casing (2) constituting the appearance; A compressor 20 located inside the casing 2 and provided with a plurality of compressor blades 24 along an axial direction; And a turbine 30 provided at a rear end of the combustor 10 to which the fluid compressed by the compressor 20 is supplied, and a tip at the root portion 24a to detect the vibration generated by the compressor blade 24. A sensing unit (100) provided with a plurality of sections (24c); A data transmitter 200 for transmitting a data signal sensed by the detector 100; A data receiver 300 positioned outside the casing 2 and receiving vibration data transmitted from the data transmitter 200; And a controller 400 for reducing vibration by calculating vibration data received by the data receiver 300.

The sensing unit 100 is installed at an initial stage or a first stage and a middle stage, respectively, among a plurality of stages constituting the compressor 20.

The detection unit 100 is installed on the pressure surface 24P of the compressor blade 24, the first detection unit 110 located in the root portion (24a); A second sensing unit (120) located in the mid span (MS) of the compressor blade (24); And a third sensing unit 130 positioned at the tip 24c of the compressor blade 24.

The controller 400 controls the amount of fuel supplied to the compressor 20.

The controller 400 variably controls the amount of bleed valve air connected to the compressor 20.

The controller 400 controls the angle of the inlet guide vane (IGV) provided in the compressor 20.

Control method of the gas turbine according to an embodiment of the present invention includes a vibration detection step (ST100) for detecting in real time the presence of vibration generated in the compressor of the gas turbine; And determining whether the vibration is continuously generated abnormal vibration or one-time vibration, and in the case of abnormal vibration, controlling the vibration generated by the compressor by controlling the abnormal vibration section in which the abnormal vibration is generated (ST200).

The vibration detecting step ST100 detects the presence or absence of vibration generated at the first stage or the first stage and the middle stage of the compressor.

Controlling the vibration generated in the compressor (ST200) includes a first control step (ST210) for adjusting the load of the gas turbine.

The controlling of the vibration generated by the compressor (ST200) includes a second control step (ST220) of variably controlling the amount of bleed valve air connected to the compressor.

The controlling of the vibration generated by the compressor (ST200) includes a third control step (ST230) of controlling the angle of the inlet guide vane (IGV) provided in the compressor.

If the vibration is maintained after controlling the vibration generated in the compressor (ST200), an alarm warning is generated.

Embodiments of the present invention can stably control the generation of stall due to vibration generated in the compressor blades of the gas turbine, thereby preventing or preventing durability improvement and damage of the compressor blades in advance.

Embodiments of the present invention to maintain a constant discharge pressure of the compressor to stabilize the power generation of the gas turbine, it is possible to maintain the optimized operation of the gas turbine.

1 is a cross-sectional view showing a gas turbine according to an embodiment of the present invention.
2 is a view briefly showing a configuration for measuring the vibration generated from the compressor blade and the compressor blade according to an embodiment of the present invention.
3 is a perspective view showing a compressor blade according to an embodiment of the present invention.
4 is a flowchart illustrating a gas turbine control method according to an embodiment of the present invention.

A gas turbine according to an embodiment of the present invention will be described with reference to the drawings. In addition, terms to be described below are terms defined in consideration of functions in the present invention, which may vary according to intentions or customs of users or operators, and the following embodiments do not limit the scope of the present invention. It is merely illustrative of the components set forth in the claims.

In order to clearly describe the present invention, parts irrelevant to the description are omitted, and like reference numerals designate like elements throughout the specification. Throughout the specification, when a part is said to "include" a certain component, it means that it may further include other components, without excluding the other components unless otherwise stated.

1 is a cross-sectional view showing a gas turbine according to an embodiment of the present invention, the gas turbine 1 according to an embodiment of the present invention is a compressor 20 for compressing a high pressure to intake air, and the compressor Turbine 30 for producing electric power by rotating the turbine blades by using a combustor 10 for mixing and combusting the air compressed by 20 with the fuel and the high-temperature, high-pressure combustion gas discharged from the combustor 10. It can be made, including).

Specifically, the gas turbine (1) is provided with a casing (2), and when described with reference to the flow direction of air, the compressor 20 is located on the upstream side of the casing (2), the turbine 30 on the downstream side Is placed. And between the compressor 20 and the turbine 30 is disposed a rotational force transmission unit 40 as a torque transmission member for transmitting the rotational torque generated in the turbine 30 to the compressor 20.

In addition, the rear side of the casing (2) is provided with a diffuser (50) through which the combustion gas passing through the turbine (30) is discharged, and a combustor for supplying compressed air to the front of the diffuser (50) for combustion. 10 is disposed. For reference, the combustor housing 10a is positioned to completely surround the combustor 10 from the outside.

The compressor 20 is provided with a plurality of compressor rotor disks 22, and each of the compressor rotor disks 22 is fastened so as not to be spaced in the axial direction by the tie rods 60.

The tie rod 60 is disposed to penetrate through the center of the plurality of compressor rotor disks 22, one end of which is fastened in the compressor rotor disk 22 located at the most upstream side, and the other end of the plurality of compressor rotor disks 22. It is fixed to 40.

The shape of the tie rod 60 may be formed in various structures according to the gas turbine, and is not necessarily limited to the form shown in FIG. 1. That is, as shown, one tie rod may have a form penetrating the central portion of the rotor disk, a plurality of tie rods may be arranged in a circumferential shape, and they may be mixed.

Each of the compressor rotor disks 22 is aligned in the axial direction with each other with the tie rod 60 penetrating the center thereof. Here, each of the neighboring compressor rotor disks 22 are disposed such that their opposite surfaces are compressed by the tie rods 60, so that relative rotation is impossible.

A plurality of compressor blades 24 are radially coupled to the outer circumferential surface of the compressor rotor disk 22. Each compressor blade 24 has a root portion 24a and is fastened to the compressor rotor disk 22.

The fastening method of the root portion 24a includes a tangential type and an axial type. It may be selected according to the required structure of a commercially available gas turbine, and may have a commonly known dovetail or fir-tree.

In some cases, the blade can be fastened to the rotor disk using a fastener other than the above-described form, for example, a key or bolt.

In addition, vanes (not shown) which are fixedly disposed on the casing 2 are located between the respective compressor rotor disks 22. The vane is fixed so as not to rotate unlike the compressor rotor disk 22, and the compressor of the rotor disk positioned downstream by aligning the flow of compressed air passing through the compressor blade 24 of the compressor rotor disk 22 It serves to guide the air to the blade.

As such, after the outside air is sucked into the inside through the compressor 20, passes through the plurality of the compressor blades 24 and the vanes, and is compressed in multiple stages, the air is supplied to the turbine 30 via the combustor 10. Can be.

The combustor 10 mixes and combusts the compressed air introduced from the compressor 20 with fuel to produce a high energy high temperature, high pressure combustion gas. The combustion gas temperature is increased.

The combustor 10 constituting a combustion system of a gas turbine is of a can type, and a plurality of combustors 10 are installed along the circumferential direction of the gas turbine 1.

The combustor 10 includes a burner including a fuel injection nozzle, a combustor liner forming a combustion chamber, and a transition piece that is a connection part between the combustor 10 and the turbine 30. It may be made, including.

Specifically, the liner provides a combustion space in which fuel injected by the fuel injection nozzle is mixed with the compressed air of the compressor 20 and combusted. Such a liner may include a flame barrel providing a combustion space in which fuel mixed with air is combusted, and a flow sleeve surrounding the flame barrel to form an annular space. In addition, the fuel injection nozzle is coupled to the front end of the liner, the spark plug may be coupled to the side wall.

On the other hand, the transition piece is connected to the rear end of the liner to send the combustion gas burned by the spark plug to the turbine 30 side. The transition piece is cooled by the compressed air supplied from the compressor 20 so that the outer wall is prevented from being damaged by the high temperature of the combustion gas.

The turbine 30 is basically similar to the structure of the compressor 20. That is, the turbine 30 is also provided with a plurality of turbine rotor disks 32 similar to the compressor rotor disk 22 of the compressor. It also includes a plurality of turbine blades 34 disposed radially on the outer circumferential surface of the turbine rotor disk 32. In this case, the turbine blade 34 may be coupled to the turbine rotor disk 32 in a dovetail or the like manner.

In the gas turbine having the structure as described above, the introduced air is compressed in the compressor 20, combusted in the combustor 10, and then sent to the turbine 30 to drive the turbine, and the diffuser 50. Through the air to the atmosphere.

Here, the gas turbine is only one embodiment of the present invention, the combustion apparatus of the present invention to be described in detail below can be applied to all the general gas turbine.

2 is a view schematically showing a compressor blade and a configuration for measuring vibration generated in the compressor blade according to an embodiment of the present invention, Figure 3 is a perspective view showing a compressor blade according to an embodiment of the present invention to be.

2 to 3, a gas turbine according to an embodiment of the present invention is a casing (2) constituting an outer appearance, and located inside the casing (2), a plurality of compressors along the axial direction Compressor 20 is provided with a blade 24, and a turbine 30 provided at the rear end of the combustor 10 to which the fluid compressed by the compressor 20 is supplied.

In addition, a plurality of detectors 100 are installed in a section from the root portion 24a to the tip 24c to detect the vibration generated by the compressor blade 24 and the data signal detected by the detector 100. A data transmission unit 200 for transmitting the data, and a data reception unit 300 and a data reception unit 300 that are located outside the casing 2 and receive the vibration data transmitted from the data transmission unit 200. And a controller 400 for reducing the vibration by calculating the vibration data.

The sensing unit 100 is installed at an initial stage or a first stage and a middle stage, respectively, among a plurality of stages constituting the compressor 20.

The compressor 20 is composed of all 14 stages or 15 stages, for example, the sensing unit 100 is installed at the initial stage.

At the initial stage, the root portion 26 (see FIG. 1) is coupled to the rotor disk 22 (see FIG. 1) coupled to the tie rod 60, and the compressor blade 24 is moved outward of the root portion 26. ) Is provided.

Compressor blade 24 installed in the initial stage is increased in size while the thickness is reduced to improve the efficiency of the compressor 20, in order to increase the compression efficiency of the air flowing into the compressor 20 at the tip (24C) Attack angles are made differently.

The compressor blade 24 installed at the initial stage is a shock wave due to collision with the air introduced into the compressor 20 with the Mach number exceeding 1 at the tip 24C position at the same time as the gas turbine is operated for power generation. (Shock wave) is generated.

The shock wave may cause vibration in the compressor blade 24 having an increased thickness and size, and may cause a stall when repeated repeatedly. When the stall is generated in the gas turbine, it causes a surge phenomenon and generates vibration in a component such as a bearing.

In this case, the gas turbine can be stopped or lead to breakage of the compressor blade. Therefore, when the vibration is generated, the correct cause and measures must be accompanied at the same time to ensure stable operation of the gas turbine.

The present embodiment detects a stall that may be generated at the initial stage of the compressor blade 24 in advance, and controls the operation of the gas turbine to minimize vibration.

To this end, in the present embodiment, the sensing unit 100 is installed to detect the vibration generated from the compressor blade 24.

For example, a strain gauge sensor is used to detect the centrifugal force and the load generated when the compressor blade 24 is rotated. However, another sensor capable of detecting the aforementioned centrifugal force and the load may be used. It may be possible.

The sensing unit 100 is installed on the pressure surface 24P of the compressor blade 24, the first sensing unit 110 located in the root portion 26, and the mid span of the compressor blade 24. And a second detector 120 located at the MS) and a third detector 130 located at the tip 24c of the compressor blade 24.

The sensing unit 100 is installed on the pressure side of the compressor blade 24 and is fixed with an adhesive for stable attachment, but may also be fixed in other ways.

The compressor blade 24 generates bending and torsion when the gas turbine is operated, and the bending and torsion cause vibration in the rotating compressor blade 24.

Preferably, the bending and torsion are generated as little as possible, but the size of the compressor blade 24 is increased, and as the thickness of the compressor blade 24 becomes thinner, the vibration increases due to breakage or tremor.

The compressor blade 24 is the root portion 26 is fixed to the rotor disk 22, since the first detection unit 110 is installed to detect the vibration in the root portion 26, the root portion ( 26) can accurately detect the vibration generated.

The second sensing unit 120 is installed in the mid span MS of the compressor blade 24 and spaced apart from the first sensing unit 110 at a predetermined distance in a diagonal direction. The reason why the second sensing unit 120 is disposed in the diagonal direction with the first sensing unit 110 is to accurately detect the presence and the intensity of vibration caused by the torsion generated in the compressor blade 24.

If the second sensing unit 120 is located in the up and down direction instead of the diagonal direction with the first sensing unit 110, it may be difficult to accurately detect the presence and intensity of vibration due to the torsion, and thus the above-described arrangement relationship is maintained. .

The third sensing unit 130 is installed at the tip 24c of the compressor blade 24. The reason why the third sensing unit 130 is installed at the position is that the probability of vibration is increased when the Mach number measured at the tip 24c position is 1 or more. This, in turn, provides a condition in which the compressor blade 24 may break.

In the present embodiment, the compressor blade 24 uses the above-described detection unit 100 to accurately detect the occurrence of vibration due to bending and torsion in the section extending from the root portion 16 to the tip 24c when the compressor blade 24 rotates. The presence or absence of vibration of 24 can be accurately detected.

Although the present embodiment has been described with respect to the initial stage of the above-described compressor blade, the sensing unit is installed in each of the initial stage and the mid-terminal stage to sense the vibration generated in the compressor blade, it can be used as data for determining the presence of stall.

The data transmitter 200 transmits a wireless signal to the data receiver 300, and receives the data transmitted from the data transmitter 200 from the data receiver 300.

The controller 400 controls the amount of fuel supplied to the compressor 20 when vibration occurs in the compressor blade 24. Gas turbines, when used for power generation, operate for a long time on a specific ALP, producing the necessary power.

For example, when a stall is generated due to vibration in the compressor blade 24, the fuel is supplied to a fuel amount that is reduced than the amount of fuel supplied at a predetermined set value so as to minimize vibration generated in the compressor blade 24.

In this case, since the compressor blade 24 is rotated in a state before vibration is generated, unnecessary vibration is minimized.

In addition to the above-described embodiment, the controller 400 controls the generation of vibration due to the stall by variably controlling the amount of bleed valve air connected to the compressor 20.

The compressor 20 can be reliably solved to unstable the flow instability of the compressed air by discharging it to the outside when the flow of air inside the compressor is generated through a piping line (not shown) provided separately from the outside of the casing (2). have.

In this embodiment, the control unit 400 selectively controls the bleeve valve air amount according to the vibration generated by the compressor blade 24 to stably achieve an ideal air flow in the compressor blade 24. Can be.

In the present embodiment, the control unit 400 controls the generation of vibration due to stall through the angle control of the inlet guide vane (IGV) provided in the compressor 20.

The IGV adjusts the angle of attack of the first stage blade constituting the compressor 20 or adjusts the flow path area of the compressor inlet, which is more precisely controlled according to the data generated by the controller 100 by the controller 400. do. For example, the controller 400 performs IGV control according to the strength of the vibration data received by the data receiver 300.

Since the control unit 400 controls the opening amount more precisely within the operating range set when the IGV is designed, surge or vibration due to stall is prevented.

In this case, the gas turbine is operated stably, so the power generation amount is not reduced and is normally operated.

A control method of a gas turbine according to an embodiment of the present invention will be described with reference to the drawings.

The present embodiment prevents damage to the compressor blades by detecting in advance that a stall is generated when vibration is generated in the compressor blades provided in the compressor during operation of the gas turbine, and enables the operation of the optimized gas turbine.

Referring to FIG. 4, the control method of the gas turbine according to the present embodiment includes a vibration detection step (ST100) for detecting in real time the presence or absence of vibration generated in the compressor of the gas turbine and whether the vibration is an abnormal vibration continuously generated. It is determined whether the one-time vibration, if the abnormal vibration comprises the step of controlling the vibration generated in the compressor through the abnormal vibration section control in which the abnormal vibration is generated (ST200).

The vibration detecting step ST100 detects the presence or absence of vibration generated at the first stage or the first stage and the middle stage of the compressor.

As the compressor blade rotates, vibration occurs due to bending and torsion, but if the vibration causes damage to the compressor blade or causes vibrations in the entire gas turbine and affects durability of other components, it is detected in advance and vibration is minimized. It is preferable to control as much as possible.

This embodiment detects the presence or absence of vibration occurring at the initial stage or the presence of the vibration occurring at the initial stage to detect the vibration of the compressor blades provided in the compressor among the various vibrations generated in the gas turbine in real time. .

When the vibration generated in the compressor blade causes a surge due to stall, it may affect the safety of the gas turbine or cause damage to the compressor blade. Therefore, it is preferable to detect the vibration in advance and control the vibration generation.

This embodiment is provided with a detection unit for detecting the vibration generated in any one of the plurality of compressor blades provided in the compressor, and detects the vibration generated when the compressor blade is rotated.

For example, when vibration occurs within a preset vibration range in the compressor, it is determined that normal operation is performed. If the vibration generated by the compressor is out of the preset vibration range, it is determined whether it is a temporary one-time vibration or an abnormal vibration continuously.

In other words, by analyzing the vibration data sensed by the sensing unit installed in the compressor blade to control the vibration generated in the compressor before the degree of vibration due to the bending and torsion applied to the compressor blade exceeds the tolerance required by the design value (ST200). .

For example, the first control (ST210) for adjusting the load amount of the gas turbine is implemented to adjust the amount of fuel currently supplied to the gas turbine to prevent stall generation in advance.

In particular, the compressor is composed of a plurality of stages, if the stall is generated in the initial stage or the middle stage can be generated in the stall (all stage) constituting the compressor, so that the load of the gas turbine is controlled not to increase.

For reference, the sensing unit may be installed on any one of the plurality of compressor blades, but a plurality of the detection blades may be installed.

Unlike the above-described embodiment, in order to control the vibration generated by the compressor (ST200), a second control (ST220) for variably controlling the amount of bleed valve air connected to the compressor is performed.

The bleed valve air amount controls the generation of the stall by controlling the pressure fluctuation of the compressor blade currently located in a specific stage through the pressure control inside the compressor.

The compressor is provided with a separate pipe line to discharge the air in the compressor flow path to the outside at the start of the gas turbine to eliminate the flow of the compressor. In addition, the cooling air is supplied to the vane of the turbine during output operation for stable operation.

Controlling the vibration generated in the compressor (ST200) in conjunction with the above-described embodiment by controlling the angle of the inlet guide vane (IGV) of the inlet guide vane (IGV) provided in the compressor (ST230) can minimize the generation of stall.

The IGV controls the generation of the stall by adjusting the angle of attack of the compressor blade provided in the compressor or by adjusting the passage area of the compressor inlet. Since the compressor blade is angled within 100 degrees, even when the load is concentrated due to vibration due to bending or torsion in the compressor blade, it is possible to stably control the generation of vibration due to the generation of stall, thereby promoting the normal operation of the gas turbine. have.

If the vibration is not reduced or maintained even in the above-described step control to control the vibration generated in the compressor (ST200), an alarm warning is generated.

In this case, both the operator and the manager can recognize and stop the operation of the gas turbine and immediately identify and cope with the cause of the vibration, so that the damage caused by the vibration generated by the compressor can be prevented. have.

As mentioned above, although an embodiment of the present invention has been described, those skilled in the art may add, change, delete, or add components within the scope not departing from the spirit of the present invention described in the claims. The present invention may be modified and changed in various ways, etc., which will also be included within the scope of the present invention.

2: casing
10: combustor
20: compressor
24: Compressor Blade
30: turbine
100: detector
110, 120, 130: first, second, third detection unit
200: data transmission unit
300: data receiving unit
400: control unit

Claims (12)

A casing 2 constituting an appearance;
A compressor 20 located inside the casing 2 and provided with a plurality of compressor blades 24 along an axial direction;
Including a turbine 30 provided at the rear end of the combustor 10 to which the fluid compressed by the compressor 20 is supplied,
A sensing unit (100) installed in plural in a section from the root portion (24a) to the tip (24c) in order to detect the vibration generated by the compressor blade (24);
A data transmitter 200 for transmitting a data signal sensed by the detector 100;
A data receiver 300 positioned outside the casing 2 and receiving vibration data transmitted from the data transmitter 200; And
Gas turbine comprising a control unit 400 for reducing the vibration by calculating the vibration data received from the data receiving unit (300). The method of claim 1,
The sensing unit 100 is a gas turbine installed in the first stage (First stage) or the first stage (First stage) and the middle stage (Middle stage) of the plurality of stages (Stage) constituting the compressor (20). The method of claim 1,
The detection unit 100 is installed on the pressure surface 24P of the compressor blade 24, the first detection unit 110 located in the root portion (24a);
A second sensing unit (120) located in the mid span (MS) of the compressor blade (24);
Gas turbine comprising a third sensing unit (130) located at the tip (24c) of the compressor blade (24). The method of claim 1,
The control unit 400 is a gas turbine for controlling the amount of fuel supplied to the compressor (20). The method of claim 1,
The control unit 400 is a gas turbine for variably controlling the amount of bleed valve air connected to the compressor (20). The method of claim 1,
The control unit 400 is a gas turbine for controlling the angle of the inlet guide vane (IGV) provided in the compressor (20). Vibration detection step (ST100) for detecting in real time the presence of vibration generated in the compressor of the gas turbine; And
Determining whether the vibration is a continuous abnormal vibration or a one-time vibration, if the abnormal vibration gas turbine comprising the step of controlling the vibration generated by the compressor through the abnormal vibration section control the abnormal vibration is generated (ST200) Control method. The method of claim 7, wherein
The vibration detection step (ST100) is a control method of a gas turbine for detecting the presence or absence of vibration generated in the first stage (First stage) or the first stage (First stage) and the middle stage (Middle stage) constituting the compressor. The method of claim 7, wherein
The controlling of the vibration generated by the compressor (ST200) comprises a first control step (ST210) for adjusting the load of the gas turbine control method of the gas turbine. The method of claim 7, wherein
The controlling of the vibration generated by the compressor (ST200) comprises a second control step (ST220) of controlling the amount of air bleed valve connected to the compressor control method of the gas turbine. The method of claim 7, wherein
The controlling of the vibration generated in the compressor (ST200) comprises a third control step (ST230) for controlling the angle of the inlet guide vane (IGV) provided in the compressor. The method of claim 7, wherein
If the vibration is maintained after the step of controlling the vibration generated in the compressor (ST200) control method of the gas turbine is generated.

Images