KR102056918B1 - Blade gap measurement and position correction system for gas turbine and blade gap measurement and correction method using the same - Google Patents

Abstract

The present invention relates to a blade gap measurement and correction system of a gas turbine, and a blade gap measurement and correction method using the same. The absolute value of the casing and the absolute displacement of the bearing are measured and compared to simply calculate the blade gap value and the blade gap. There is an effect that can be adjusted.

Description

Blade gap measurement and position correction system for gas turbine and blade gap measurement and correction method using the same}

The present invention relates to a blade gap measurement and correction system of a gas turbine and a blade gap measurement and correction method using the same, and more specifically, to calculate a blade gap value by measuring and comparing the absolute displacement of the casing and the absolute displacement of the bearing. It relates to a system and method that can adjust the gap of the.

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

Here, the gas turbine comprises a compressor section, a combustor and a turbine section, the outside air is sucked in and compressed by the rotation of the compressor section, and then is sent to the combustor, where combustion occurs by mixing compressed air and fuel in the combustor. The hot, high pressure gas generated by the combustor passes through the turbine section and rotates the rotor of the turbine to drive the generator.

In operation of the gas turbine, it is important to maintain a gap between the end of the blade tip and the inner surface of the casing. If the gap is not maintained properly, the tip of the blade tip may contact the inner surface of the casing, causing wear and damage. This acts as a cause of lowering the power efficiency of the gas turbine. In addition, if the gap is not maintained, vibrations occur and the gas turbine must be stopped temporarily, resulting in loss in power generation.

In order to prevent such a problem, a tip of the blade 5 of the bucket and the casing 2 which are conventionally drilled in the casing 2, the sensor 6 is built in, and mounted on the outer circumferential surface of the rotor disk 3, as shown in FIG. The gap with the inner surface of the) was measured. In the gas turbine the blades 5 of the bucket and the vanes of the diaphragms are alternately arranged.

Referring to FIG. 2, in order to measure the gap D of the blade, first, the distance C between the center of the rotor disk 3 and the inner surface of the casing 2, the radius R of the rotor disk 3, and the blades are measured. A numerical value for the length B of (5) is required.

Except for the radius R of the rotor disk 3 and the length B of the blade 5 in the interval C, the gap D of the blade 5 is calculated. The sensor 6 measures the real-time gap value, and the control unit 7 compares the real-time measured gap value with a predetermined gap value, and determines whether or not it is within a gap allowable range for operation of the gas turbine.

However, this method has a limitation in that a hole for installing the sensor 6 in the casing 2 must be made.

United States Patent Publication Number: 2017-0067360

The present invention has been made to solve the problems in the related art as described above, an object of the present invention is to calculate the gap value of the blade and to adjust the blade gap by measuring the absolute displacement of the casing and the absolute displacement of the bearing To provide a system and method.

The present invention for achieving the above object relates to a blade gap measurement and correction system of the gas turbine, and is connected to the casing, the displacement measurement sensor for measuring the absolute displacement of the casing; and is connected to the bearing, A bearing displacement measuring sensor for measuring an absolute displacement of the bearing; And a control unit connected to the casing displacement measuring sensor and the bearing displacement measuring sensor and measuring and correcting a gap of the blade by comparing the absolute displacement of the casing with the absolute displacement of the bearing.

Further, in the embodiment of the present invention, the casing displacement measuring sensor may be disposed in the compressor section of the casing.

In addition, in the embodiment of the present invention, the casing displacement measuring sensor is a multi-directional position sensor, it is possible to measure the longitudinal and radial displacement values of the casing.

In addition, in the embodiment of the present invention, the bearing is a journal thrust bearing disposed at the end of the rotor, and the bearing displacement measuring sensor may measure the axial and radial displacement values of the rotor.

In addition, in the embodiment of the present invention, the control unit, the displacement measuring unit for measuring the absolute displacement of the casing and the absolute displacement of the bearing; And a comparison conversion unit for calculating a displacement difference by comparing the absolute displacement value of the casing measured by the displacement measuring unit with the absolute displacement value of the bearing, and converting the displacement difference into a gap value of the blade. Can be.

In addition, in the embodiment of the present invention, the displacement measuring unit is connected to the casing displacement measuring sensor, the casing displacement measuring module for measuring the absolute displacement value of the casing; And a bearing displacement measuring module connected to the bearing displacement measuring sensor and measuring an absolute displacement value of the bearing.

In addition, in the embodiment of the present invention, the comparison conversion unit, displacement value comparison module for comparing the absolute displacement of the casing and the absolute displacement of the bearing, and calculates the displacement difference; And a gap value conversion module for converting the displacement difference calculated by the displacement value comparison module into a gap value of the blade.

In addition, the embodiment of the present invention may further include a positioning unit for adjusting the position of the casing, in order to adjust the gap of the blade.

In addition, in the embodiment of the present invention, the control unit may calculate a position adjustment value of the casing, the position adjustment unit for operating the position adjustment unit; may further include a.

In addition, in the embodiment of the present invention, the position adjusting portion is disposed on the device frame for supporting the casing, the first hydraulic device for adjusting the horizontal position of the casing; And a second hydraulic device disposed on an apparatus frame for supporting the casing, and configured to adjust a vertical position of the casing.

In addition, in the embodiment of the present invention, the position adjustment unit may include an adjustment value determination module for calculating the gap value of the blade converted in the gap value conversion module as the position adjustment value of the casing.

In addition, in the embodiment of the present invention, the position adjusting unit may further include a driving module for driving the position adjusting unit based on the position adjusting value calculated by the adjusting value determining module.

The present invention relates to a blade clearance measurement and correction method, comprising: measuring an absolute displacement value of a casing; and measuring an absolute displacement value of a bearing; and the measured absolute displacement value of the casing and an absolute value of the bearing. Comparing the displacement values; And converting the compared displacement difference into a gap value of a blade.

In addition, the exemplary embodiment of the present invention may further include comparing the gap value of the converted blade with the gap allowance of the preset blade.

In addition, the exemplary embodiment of the present invention may further include an alarm step of notifying whether or not the gap value of the converted blade exceeds the preset tolerance range of the blade.

In addition, in the embodiment of the present invention, after the alarm step, the step of stopping the operation of the gas turbine; may further include.

The method may further include comparing a gap value of the converted blade with a gap zero value of a predetermined blade, and calculating a position adjustment value of the casing.

In addition, the embodiment of the present invention may further include adjusting the position of the casing on the basis of the calculated position adjustment value.

According to the present invention, by comparing the absolute displacement of the casing and the absolute displacement of the bearing, it is possible to calculate the gap value of the blade through the displacement difference.

When the clearance allowance range of the predetermined blade is exceeded, the clearance gap of the blade can be corrected by repositioning the casing by utilizing a positioning device such as a hydraulic device. At this time, the adjustment value is calculated by converting the gap value.

This ultimately allows the blade gap to be maintained within a certain range to prevent wear and damage to the gas turbine and to increase power efficiency.

1 is a view showing a method of measuring the gap value of a conventional blade.
2 is a view showing a basic value for measuring the gap value of a conventional blade.
Figure 3 is a view showing the structure of the gas turbine to which the present invention is applied.
Figure 4 is a control block diagram for the present invention.
5 is a control flowchart for the present invention.
6 is a view showing the basic value and the sensor position for measuring the gap value of the blade according to the present invention.
7 is a view showing a position adjustment method of the casing according to the present invention.

Hereinafter, with reference to the accompanying drawings will be described in detail preferred embodiments of the blade gap measurement and correction system and the blade gap measurement and correction method of the gas turbine according to the present invention.

Prior to the description of the present invention, the configuration of the gas turbine 10 will be described with reference to the drawings.

Referring to FIG. 1, the gas turbine basically includes a casing 20 for forming an appearance, a compressor section 40 for compressing air, a combustor 50 for combusting air, and a combustor. A turbine section 60 generating power using gas, a diffuser 70 exhausting exhaust gas, and a rotor connecting the compressor section 40 and the turbine section 60 to transmit rotational power; 30).

Thermodynamically, the compressor section corresponding to the upstream side of the gas turbine receives external air and undergoes adiabatic compression. Compressed air enters the combustor section, mixes with fuel and undergoes isothermal combustion, and combustion gas flows into the turbine section, downstream of the gas turbine, and undergoes adiabatic expansion. .

Referring to the flow direction of the air, the compressor section 40 is located in front of the casing 20, the turbine section 60 is provided at the rear.

Between the compressor section 40 and the turbine section 60 is provided with a torque tube 30b for transmitting the rotational torque generated in the turbine section 60 to the compressor section 40.

The compressor section 40 is provided with a plurality (for example 14) of compressor rotor disks 40a, and each of the compressor rotor disks 40a is fastened so as not to be spaced in the axial direction by the tie rods 30a. do.

The centers of the respective compressor rotor disks 40a are aligned in the axial direction with each other while the tie rods 30a penetrate. In the vicinity of the outer circumference of the compressor rotor disk 40a, a flange (not shown) coupled to a neighboring rotor disk to prevent relative rotation is formed to protrude in the axial direction.

A plurality of blades 40b (or buckets) are radially coupled to the outer circumferential surface of the compressor rotor disk 40a. Each blade 40b has a dove tail portion (not shown) to be fastened to the compressor rotor disk 40a.

The dovetail part may be of a tangential type and an axial type. This may be selected according to the required structure of a commercially available gas turbine. In some cases, the compressor blade 40b may be fastened to the compressor rotor disk 40a using a fastening device other than the dovetail.

At this time, the inner circumferential surface of the compressor section 40 of the casing 20 has a vane (or nozzle) for the relative rotational movement of the compressor blade 40b to be mounted on the diaphragm (not shown). Can be.

The tie rod 30a is disposed to penetrate through the centers of the plurality of compressor rotor disks 40a, one end of which is fastened in the compressor rotor disk 40a positioned at the most upstream side, and the other end of the torque tube 30b. It is fixed to).

The tie rod 30a may be formed in various structures according to gas turbines, and is not necessarily limited to the form shown in the drawings.

One tie rod 30a may have a form penetrating the central portion of the compressor rotor disk 40a, and a plurality of tie rods 30a may be arranged in a circumferential shape, and a mixture thereof may be used. .

Although not shown, the compressor of the gas turbine may be provided with a vane serving as a guide vane at the next position of the diffuser to increase the pressure of the fluid and then adjust the flow angle of the fluid entering the combustor to the design flow angle. It is called a desworler.

The combustor 50 mixes and combusts the introduced compressed air with fuel to produce a high-temperature, high-pressure combustion gas with high energy, and heat resistance that the components of the combustor 50 and the turbine section 60 can withstand during the isostatic combustion process. The combustion gas temperature is raised to the limit.

The combustor 50 constituting the combustion system of the gas turbine may be arranged in the casing 20 formed in the form of a cell.

On the other hand, in the turbine section 60, the high-temperature, high-pressure combustion gas from the combustor 50 expands and imparts impulse and reaction force to the rotor blades of the turbine section 60 to convert it into mechanical energy.

The mechanical energy obtained in the turbine section 60 is supplied with the energy required to compress the air in the compressor section 40 and the rest is used to drive the generator to produce power.

The turbine section 60 is configured by alternately arranging a plurality of vanes and rotor blades in a vehicle compartment, and rotationally driving an output shaft to which a generator is connected by driving the rotor blades by combustion gas.

To this end, the turbine section 60 is provided with a plurality of turbine rotor disks 60a. Each turbine rotor disk 60a basically has a form similar to the compressor rotor disk 40a.

The turbine rotor disk 60a also has a provided flange (not shown) for coupling with a neighboring turbine rotor disk 60a and includes a plurality of radially disposed turbine blades 60b (or buckets). do. The turbine blade 60b may also be coupled to the turbine rotor disk 60a in a dovetail manner.

At this time, the inner circumferential surface of the turbine section 60 of the casing 20 is a vane (not shown) (or nozzle) for the relative rotational movement of the turbine blade 60b is mounted on the diaphragm (not shown) Can be.

In the gas turbine having the structure as described above, the inlet air is compressed in the compressor section 40, combusted in the combustor 50, and then moved to the turbine section 60 to generate and drive the diffuser 70. Through the atmosphere.

Here, the torque tube 30b, the compressor rotor disk 40a, the compressor blade 60b, the turbine rotor disk 60a, the turbine blade 60b, the tie rod 30a, and the like are integrally formed as a rotating component. 30) or a rotating body. The casing 20, vanes (not shown), diaphragms (not shown), and the like may be referred to as stators or fixtures as a non-rotating component.

One general structure of a gas turbine is as described above, and the following describes the present invention applied to such a gas turbine.

Figure 3 is a view showing the structure of the gas turbine to which the present invention is applied, Figure 4 is a control block diagram for the present invention, Figure 5 is a control flow chart for the present invention, Figure 6 is a gap value of the blade according to the present invention Figure is a view showing the basic value and the sensor position for measuring, Figure 7 is a view showing a position adjustment method of the casing according to the present invention.

3 to 7, in the embodiment of the blade gap measurement and correction system 100 of the present inventors gas turbine casing displacement measuring sensor 111, bearing displacement measuring sensor 113 and the position adjusting unit 120 and It may be configured to include a controller 150.

First, the casing displacement measuring sensor 111 may be connected to the casing 20 and perform a function of measuring the absolute displacement of the casing 20. Here, the absolute displacement of the casing 20 is a position of the fixed state (zero) of the casing 20 due to vibration, shock, etc. generated during operation, the fixed state of the casing 20 installed in the power generation facility as a zero point. The change state can be defined as the absolute displacement.

That is, the casing displacement measuring sensor 111 measures the displacement difference of the casing 20 as much as the position changed during operation in preparation for the initial fixed state.

The casing displacement measuring sensor 111 may be disposed in the compressor section 40 of the casing 20. This is because the compressor section 40 of the gas turbine is the key to determining power efficiency. Although the turbine section 60 is much more efficient than the compressor section 40 itself, it is initially affected by the power efficiency in the turbine section 60 depending on the compression efficiency in the compressor section 40.

Therefore, measuring the clearance of the blades 40b of the buckets disposed in the compressor section 40 takes precedence over measuring the clearance of the blades 40b of the buckets disposed in the turbine section 60. Measuring and correcting the blade 40b clearance in the compressor section 40 makes a greater contribution to increasing the power efficiency of the gas turbine.

The casing displacement measuring sensor 111 may be a multi-directional position sensor, and may be provided to measure longitudinal and radial displacement values of the casing 20. That is, the displacement of the casing 20 in three dimensions can be measured. The casing displacement measuring sensor 111 may be, for example, a 3D position measuring sensor, but is not necessarily limited thereto.

Next, the bearing displacement measuring sensor 113 may be connected to the bearing 33 and perform a function of measuring the absolute displacement of the bearing 33. In this case, the absolute displacement of the bearing 33 is a fixed state of the bearing 33 as a zero point, and the position change state with respect to the fixed state (zero point) of the bearing 33 due to vibration, shock, etc. generated during operation. It can be defined as the displacement difference.

That is, the bearing displacement measuring sensor 113 measures the displacement difference of the bearing 33 as much as the position changed during operation in preparation for the initial fixed state. The displacement difference of the bearing 33 means the displacement difference of the rotor 30.

In this case, the bearing displacement measuring sensor 113 may be selected to be disposed in the compressor section 40 of the casing 20. This is to be associated with the casing displacement measuring sensor 111.

The bearing 33 may be a journal thrust bearing 33 disposed at an end of the rotor 30, and the bearing displacement measuring sensor 113 measures the axial and radial displacement values of the rotor 30. It may be provided to. The bearing displacement measuring sensor 113 may be, for example, a position measuring sensor, but is not limited thereto.

Next, the position adjusting unit 120 may perform a function of adjusting the position of the casing 20 to adjust the gap of the blade 40b. The position adjusting unit 120 may be selected from a variety of mechanical devices that can adjust the position of the casing 20, in the embodiment of the present invention, as shown in Figure 7, supporting the casing 20 Arranged in the device frame 11, it may be composed of a first hydraulic device 123 for adjusting the casing 20 in the horizontal direction and a second hydraulic device 124 for adjusting the casing 20 in the vertical direction. have.

Next, the control unit 150 is connected to the casing displacement measuring sensor 111 and the bearing displacement measuring sensor 113, and compares the absolute displacement of the casing 20 with the absolute displacement of the bearing 33, and thus, a blade. A function of measuring and correcting the gap of 40b is performed. The control unit 150 may include a displacement measuring unit 151, a comparative conversion unit 154 and a position adjusting unit 157.

First, the displacement measuring unit 151 may be a module for measuring the absolute displacement of the casing 20 and the absolute displacement of the bearing 33. The displacement measuring unit 151 may include a casing displacement measuring module 152 and a bearing displacement measuring module 153.

The casing displacement measuring module 152 may be connected to the casing displacement measuring sensor 111 and may perform a function of determining an absolute displacement value of the casing. The position of the casing 20 is changed by vibration or external shock during operation of the gas turbine, and the displacement information is transmitted from the casing displacement measuring sensor 111 to the casing displacement measuring module 152.

In addition, the bearing displacement measuring module 153 may be connected to the bearing displacement measuring sensor 113 and may perform a function of determining an absolute displacement value of the bearing 33. When the position of the central axis of the rotor 30 is changed by vibration or external shock during operation of the gas turbine, the bearing displacement measuring sensor 113 detects the displacement generated in the bearing 33 according to the displacement of the rotor 30. Then, the displacement information is sent to the bearing displacement measurement module 153.

Next, the comparison conversion unit 154 may perform a function of comparing the absolute displacement value measured by the displacement measuring unit 151 and converting it to the gap value of the blade 40b. The comparison conversion unit 154 may include a displacement value comparison module 155 and a gap value conversion module 156.

First, the displacement value comparison module 155 compares the absolute displacement of the casing 20 with the absolute displacement of the bearing 33, and calculates a displacement difference. The gap value conversion module 156 converts the displacement difference calculated by the displacement value comparison module 155 into the gap value of the blade 40b.

Here, the gap value of the blade 40b, referring to FIG. 6, subtracts the radius R of the rotor 30 and the radial length B of the bucket blade 40b from the radius C of the casing 20. Can be defined as a formula. The clearance allowance is abutment between the end of the blade 40b and the inner circumferential surface of the casing 20 when displacement of the casing 20 and the rotor 30 occurs due to vibration or external shock generated during operation of the gas turbine. It can be defined as the minimum interval in which no collision occurs.

The clearance allowance may be set differently according to the type of gas turbine, and its value may be determined within a range that minimizes the influence on the operation of the gas turbine.

 Next, the position adjusting unit 157 may calculate a position adjustment value of the casing 20 and perform a function of operating the position adjusting unit 120. The position adjusting unit 157 may include an adjustment value determining module 158 and a driving module 159.

First, the adjustment value determination module 158 calculates the gap value of the blade 40b converted by the gap value conversion module 156 as the position adjustment value of the casing 20.

In the embodiment of the present invention, since the position adjusting unit 120 is composed of the first and second hydraulic devices 123 and 124, the adjustment value is the hydraulic driving amount. Of course, when the position adjusting unit 120 is composed of different driving devices, for example, a step motor and a gearbox structure, the position adjusting unit 120 may be calculated as the rotation amount of the step motor.

The drive module 159 drives the position adjustment unit 120 based on the position adjustment value calculated by the adjustment value determination module 158. In the embodiment of the present invention, the drive module 159 may be an operation switch of the hydraulic device.

The configuration of the present invention is as described above, with reference to Figure 5 below, to look at the operating method of the present invention.

Referring to Figure 5, in the embodiment of the blade gap measurement correction method of the present invention gas turbine casing displacement value measurement step (S1), bearing displacement value measurement step (S2), displacement value comparison step (S3), blade gap value conversion Step S4, clearance allowance determination step S5, alarm step S6, operation stop step S7, casing position adjustment value calculation step S8 and casing position adjustment step S9. have.

First, the casing displacement value measuring step S1 may be a step of measuring the absolute displacement value of the casing 20 by the casing displacement measuring module 152. As described above, the absolute displacement value of the casing 20 is a fixed state of the casing 20 installed in the power generation facility as zero, and a fixed state of the casing 20 due to vibration, shock, etc. generated during operation ( The position change state for the zero point is defined as the absolute displacement difference.

Next, the bearing displacement measuring step S2 may be a step of measuring the absolute displacement value of the bearing 33 by the bearing displacement measuring module 153. As described above, the absolute displacement value of the bearing 33 is a fixed state of the bearing 33 as a zero point, and is related to a fixed state (zero point) of the bearing 33 due to vibration, shock, etc. generated during operation. The position change state can be defined as the absolute displacement difference. This means the absolute displacement difference of the rotor 30.

Next, the displacement value comparing step S3 may be a step of comparing the absolute displacement value of the casing 20 and the absolute displacement value of the bearing 33 measured by the displacement value comparison module 155. The blade gap value conversion step S4 may be a step of converting the compared displacement difference by the gap value conversion module 156 into the gap value of the blade 40b.

Next, the clearance allowance determining step S5 may be a step of comparing the clearance value of the converted blade 40b with the clearance allowance range of the preset blade 40b.

Here, the clearance allowance range of the predetermined blade 40b is, as described above, when the displacement of the casing 20 and the rotor 30 occurs due to the vibration generated during the operation of the gas turbine, the external shock, the blade 40b of the blade 40b. It may be defined as the minimum distance range between the end and the inner circumferential surface of the casing 20 does not occur abutment or collision. The clearance allowance may be set differently according to the type of gas turbine, and its value may be determined within a range that minimizes the influence on the operation of the gas turbine.

When the gap value of the blade 40b converted and compared in the gap allowable range determination step S5 is determined to be within a preset gap allowable range, it is classified as Yes and the gap measurement of the blade 40b is finished.

If it is determined that the gap value of the blade 40b converted in comparison exceeds the preset gap allowable range, it is classified as abnormal.

If the gap value of the blade 40b is classified as abnormal, the next alarm step S6 and the operation stop step S7 are triggered. The alarm step S6 is a step in which the control unit 150 notifies the manager that the gap value of the blade 40b is abnormal through a display screen, a bell, a siren, and the like. The operation stop step S7 automatically operates the gas turbine. It may be a step of stopping. Of course, the administrator can manually operate the shutdown.

After the operation of the gas turbine is stopped, the casing position adjustment value calculation step S8 and the casing position adjustment step S9 are activated.

The casing position adjustment value calculation step (S8) is a step of calculating the gap value of the blade 40b by the adjustment value determination module 158 as the adjustment value of the position adjustment unit 120, in the present invention, the first 2 can be calculated as the amount of hydraulic pressure driving the hydraulic apparatus (123, 124). Of course, in the case of using another driving device, it may be calculated as another driving value.

Next, the casing position adjusting step S9 may be a step of adjusting the position of the casing 20 by operating the driving module 159 based on the calculated adjustment value. Horizontal adjustment of the casing 20 is performed by the first hydraulic device 123, and vertical adjustment of the casing 20 is performed by the second hydraulic device 124.

After the position adjustment of the casing 20 is completed, the displacement values of the casing 20 and the bearing 33 are again measured, and it is determined whether the gap value of the blade 40b is within a preset gap tolerance range. Repeat the procedure.

If the gap value of the blade 40b after the position adjustment of the casing 20 is determined to be within a predetermined gap allowance range, the gap measurement procedure of the blade 40b is terminated.

The present invention is to enable the stable and efficient operation of the gas turbine through the process of measuring the gap value of the blade 40b, and thereby adjust the position of the casing 20.

The foregoing merely illustrates specific embodiments of the blade gap measurement and correction system of the gas turbine and the method of measuring and correcting the blade gap using the same.

Therefore, it will be apparent to those skilled in the art that the present invention may be substituted and modified in various forms without departing from the spirit of the present invention as set forth in the claims below. do.

100: blade gap measurement and correction system
111: Casing displacement sensor
113: bearing displacement sensor
120: position adjustment unit
123.124: First and second hydraulics
150: control unit
151: displacement measurement unit
152: casing displacement measuring module
153: bearing displacement measuring module
154: non-exchange mother
155: displacement comparison module
156: gap value conversion module
157: position adjustment unit
158: adjustment value judgment module
159: drive module

Claims (18)

A casing displacement sensor connected to the casing and measuring an absolute displacement of the casing;
A bearing displacement sensor connected to a bearing and measuring an absolute displacement of the bearing;
A control unit connected to the casing displacement measuring sensor and the bearing displacement measuring sensor, the gap of the blade being measured and corrected by comparing the absolute displacement of the casing with the absolute displacement of the bearing; And
To adjust the gap of the blade, the positioning unit for adjusting the position of the casing; including,
The casing displacement measuring sensor is arranged in the compressor section of the casing,
The casing displacement measuring sensor is a multi-directional position sensor, and measures the longitudinal and radial displacement values of the casing,
The bearing is a journal thrust bearing disposed at the end of the rotor, the bearing displacement sensor measures the axial and radial displacement values of the rotor,
The control unit,
A displacement measuring unit measuring an absolute displacement value of the casing and an absolute displacement value of the bearing;
A comparison conversion unit for calculating a displacement difference by comparing the absolute displacement value of the casing measured by the displacement measuring unit with the absolute displacement value of the bearing, and converting the displacement difference into a gap value of the blade;
A position adjusting unit for calculating a position adjusting value of the casing and operating the position adjusting unit;
The displacement measuring unit,
A casing displacement measuring module connected to the casing displacement measuring sensor and measuring an absolute displacement value of the casing; And
And a bearing displacement measuring module connected to the bearing displacement measuring sensor and measuring an absolute displacement value of the bearing.
The comparative conversion unit,
A displacement value comparison module comparing the absolute displacement value of the casing with the absolute displacement value of the bearing and calculating a displacement difference; And
And a gap value conversion module that converts the displacement difference calculated by the displacement value comparison module into a gap value of the blade.
The position adjusting unit,
An adjustment value determination module for calculating a gap value of a blade converted by the gap value conversion module as a position adjustment value of the casing; And
Blade gap measurement and correction system comprising a; drive module for driving the position adjustment unit on the basis of the position adjustment value calculated by the adjustment value determination module
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The position adjusting unit,
A first hydraulic device disposed on an apparatus frame for supporting the casing, and adapted to adjust a horizontal position of the casing; And
A second hydraulic device disposed on an apparatus frame for supporting the casing, and configured to adjust a vertical position of the casing;
Blade gap measurement and compensation system comprising a
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