KR20190127025A - System and method for burning temperature deviation reduction between cans of combustor - Google Patents

Abstract

According to an embodiment of the present invention, provided is a system for reducing a combustion temperature deviation between cans of a combustor. The system for reducing the combustion temperature deviation between cans of the combustor comprises: a combustor comprising a plurality of cans; a turbine for rotating a turbine blade using the combustion gas introduced from the combustor; a diffuser for discharging the combustion gas passing through the turbine; a sensor disposed in the diffuser to measure the data for estimating the temperature of the combustion gas; and a control part for controlling a fuel injected into the plurality of candles on the basis of the data measured by the sensor.

Description

System and method for burning temperature deviation reduction between cans of combustor

The present invention relates to a system and method for reducing combustion temperature variation between cans of a combustor for inferring the temperature of each of the cans composing the combustor to reduce the combustion temperature variation between the candles.

The gas turbine consists of a compressor, a combustor and a turbine. The compressor discharges high temperature and high pressure compressed air by compressing the introduced air. The combustor discharges high-temperature, high-pressure combustion gas by supplying fuel to the compressed air to combust it. The turbine drives the rotor blade (rotating shaft) connected to the generator by driving the turbine blade by the combustion gas provided by the combustor. The combustion gas which drives the turbine is discharged from the exhaust chamber to the atmosphere as exhaust gas.

The combustor comprises a plurality of candles. Each candle is provided with compressed air and uses the provided compressed air and fuel to produce combustion gas. However, when the combustion temperature between the candle is often different from each other, when the variation in the combustion temperature between the candle may be a problem that the efficiency of the gas turbine is lowered. In addition, since the combustion temperature of each candle is a high temperature, it is difficult to directly measure the temperature inside the candle.

SUMMARY OF THE INVENTION The present invention provides a system and method for reducing combustion temperature variation between candles of a combustor that infers the temperature of the candles to reduce the combustion temperature variation between the plurality of candles and controls the fuel provided to the candles based on the inferred temperatures. It is.

According to an embodiment of the present invention, there is provided a system for reducing combustion temperature variation between candles of a combustor. The combustion temperature variation reduction system between the candles of the combustor includes a combustor including a plurality of cans, a turbine for rotating a turbine blade using combustion gas introduced from the combustor, and a diffuser for discharging the combustion gas passing through the turbine. And a sensor disposed on the diffuser to measure data for estimating the temperature of the combustion gas, and a controller configured to control fuel injected into the plurality of candles based on data measured by the sensor.

In an example, the sensor is disposed in the diffuser more than the number of the plurality of cans, each of the plurality of sensors measure data for estimating the temperature of the combustion gas discharged from each of the plurality of cans do.

By way of example, the flue gas discharged from one of the cans flows toward at least one of the sensors, and the at least one sensor is discharged from cans other than the one of the cans. Not affected by

The fuel tank may further include a fuel tank supplying fuel to each of the cans, a plurality of fuel lines connecting the fuel tank and each of the cans, and a plurality of fuel valves disposed on the fuel lines. The control unit controls the opening and closing degree of each of the fuel valves.

For example, the controller estimates the temperature of the candle based on the data measured by the sensor, and the controller controls each of the fuel valves to supply fuel to a can having a lower temperature than a reference temperature among the cans. The amount of fuel is increased and the amount of fuel supplied to the cans having a higher temperature than the reference temperature is increased.

For example, the controller estimates the temperature of the candle based on data measured by the sensor, and the controller controls the fuel tank so that a predetermined fuel temperature value is set in a can having a lower temperature than a reference temperature among the cans. A fuel having a higher temperature is provided, and a fuel having a temperature lower than a preset fuel temperature value is provided to a can having a higher temperature than a reference temperature among the cans.

In one example, the fuel tank adjusts the temperature of the fuel provided for each of the fuel lines.

According to an example, the control unit may include a table matching a plurality of the sensors arranged in plural according to the load condition of the gas turbine and the cans for discharging the combustion gas measured by each of the sensors, and the control unit is the table. The temperature of the cans is estimated by matching the sensors with the cans based on.

By way of example, the diffuser is disposed in an exhaust chamber surrounding the turbine, the diffuser includes an internal diffuser surrounding the rotor of the gas turbine and an external diffuser surrounding the internal diffuser, and the sensor includes the internal diffuser and the external. Disposed on at least one of the diffusers.

In one example, the sensor is a thermocouple sensor in contact with the diffuser to measure the temperature of the diffuser.

In one example, the sensor is a gas sensor for measuring the calorific value of the combustion gas.

In one example, the control unit calculates the Weber index, a variable for defining the energy released per unit time of the fuel based on the calorific value of the combustion gas measured by each of the plurality of sensors arranged, and the Weber index Infer the temperature of each of the candles as a basis.

According to an embodiment of the present invention, there is provided a method of reducing a combustion temperature variation between candles of a combustor. The method of reducing the combustion temperature variation between the candles of the combustor includes measuring data for estimating the temperature of the combustion gas discharged from each of the cans, and arranged at the diffuser connected to the end of the turbine according to the load condition of the gas turbine. Matching the sensors with the cans, inferring a temperature of each of the cans based on data measured by each of the sensors, controlling fuel provided to each of the cans based on a temperature of each of the cans Steps.

By way of example, matching the sensors with the cans specifies which of the sensors the combustion gas discharged from one of the cans reaches according to the load condition of the gas turbine, Match the candle and the sensors according to the load condition of the gas turbine.

In one embodiment, inferring the temperature of each of the cans based on data measured by each of the sensors may be based on the temperature of the combustion gas based on the temperature of the diffuser measured by the sensors or the calorific value of the combustion gas. Inferring, and inferring the temperature of each of the cans matching the sensors through the temperature of the combustion gas.

For example, controlling the fuel provided to each of the cans based on the temperature of each of the cans increases the amount of fuel supplied to the cans having a lower temperature than the reference temperature of the cans, and the reference temperature of the cans. Cans with higher contrast temperatures reduce the amount of fuel supplied.

For example, controlling the fuel provided to each of the cans based on the temperature of each of the cans may provide a fuel having a temperature higher than a predetermined fuel temperature value to a can having a lower temperature than a reference temperature among the cans. Among the cans, a can having a higher temperature than a reference temperature is provided with a fuel having a lower temperature than a preset fuel temperature value.

According to an embodiment of the present invention, it is possible to infer the temperature of the hot combustion gas through the temperature of the diffuser and the calorific value of the combustion gas, through which the combustion temperature of the candle can be inferred.

According to an embodiment of the present invention, the temperature variation of the fuel supplied to the candle or the amount of fuel may be adjusted according to the temperature of the candle to reduce the combustion temperature variation between the candles. As the temperature deviation between the candles is reduced, the operating efficiency of the gas turbine can be improved.

1 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.
2 is a view showing a combustion temperature variation reduction system between the candle of the combustor according to an embodiment of the present invention.
3 is a view showing a combustor according to an embodiment of the present invention.
4 is a view showing an exhaust chamber according to an embodiment of the present invention.
5 is a view showing an exhaust chamber according to another embodiment of the present invention.
6 is a flowchart illustrating a method of reducing a combustion temperature variation between candles of a combustor according to an exemplary embodiment of the present invention.

Advantages and features of the present invention, and methods for achieving them will be apparent with reference to the embodiments described below in detail with reference to the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but may be implemented in various forms, and only the present embodiments are intended to complete the disclosure of the present invention and to provide general knowledge in the technical field to which the present invention pertains. It is provided to fully convey the scope of the invention to those skilled in the art, and the present invention is defined only by the scope of the claims. Like reference numerals refer to like elements throughout the specification.

In addition, the embodiments described herein will be described with reference to cross-sectional views and / or plan views, which are ideal exemplary views of the present invention. In the drawings, the thicknesses of films and regions are exaggerated for effective explanation of technical content. Accordingly, shapes of the exemplary views may be modified by manufacturing techniques and / or tolerances. Therefore, the exemplary embodiments of the present invention are not limited to the specific forms shown, but include changes in forms generated according to manufacturing processes. For example, the etched regions shown at right angles may be rounded or have a predetermined curvature. Accordingly, the regions illustrated in the figures have schematic attributes, and the shape of the regions illustrated in the figures is intended to illustrate a particular form of region of the device and not to limit the scope of the invention.

1 is a cross-sectional view showing a schematic structure of a gas turbine according to an embodiment of the present invention.

Referring to FIG. 1, the gas turbine 1 may include a casing 100, a compressor 200, a combustor 300, and a turbine 400. The casing 100 may be configured to surround the compressor 200, the combustor 300, and the turbine 400. The compressor 200 may suck air and compress the air at high pressure, and supply the compressed air to the combustor 300. The combustor 300 may serve to mix compressed air and fuel and combust it, and supply the high pressure combustion gas generated by the combustion to the turbine 400. The turbine 400 may generate power by rotating a plurality of turbine blades using combustion gas of high temperature and high pressure.

The casing 100 may include a compressor casing 102 in which the compressor 200 is accommodated, a combustor casing 103 in which the combustor 300 is accommodated, and a turbine casing 104 in which the turbine 400 is accommodated. However, the present invention is not limited thereto, and the compressor casing, the combustor casing, and the turbine casing may be integrally formed. The compressor casing 102, combustor casing 103 and turbine casing 104 may be arranged sequentially from the upstream side to the downstream side in the fluid flow direction.

A rotor (center shaft) 50 is rotatably provided inside the casing 100, and a generator (not shown) is interlocked with the rotor 50 for power generation, and a turbine 400 is provided downstream of the casing 100. A diffuser (not shown) for discharging the passing combustion gas may be provided. A diffuser (not shown) may be disposed in the exhaust chamber 450.

The rotor 50 may include a compressor rotor disk 52, a torque tube 53, and a turbine rotor disk 54. Rotor disk 52 may be received in compressor casing 102 and turbine rotor disk 54 may be received in turbine casing 104. The torque tube 53 is accommodated in the combustion key casing 103 to connect the compressor rotor disk 52 and the turbine rotor disk 54. The compressor rotor disk 52, torque tube 53 and turbine rotor disk 54 may be fastened by tie rods 55 and retaining nuts 56.

The compressor rotor disks 52 may be formed in plural (for example, 14 sheets), and the plurality of compressor rotor disks 52 may be arranged along the axial direction of the rotor 50. That is, the compressor rotor disk 52 may be formed in multiple stages. Each of the compressor rotor disks 52 may be formed in a substantially disc shape. The outer peripheral portion of the compressor rotor disk 52 may be formed with a compressor blade coupling slot which is coupled to the compressor blade 220 to be described later.

The turbine rotor disk 54 may be formed similarly to the compressor rotor disk 52. That is, the plurality of turbine rotor disks 54 may be formed, and the plurality of turbine rotor disks 54 may be arranged along the axial direction of the rotor 50. That is, the turbine rotor disk 54 may be formed in multiple stages. Each of the turbine rotor disks 54 may be formed in a substantially disc shape. A turbine blade coupling slot may be formed at an outer circumference of the turbine rotor disk 54 to be coupled to the turbine blade 420 to be described later.

The torque tube 53 is a torque transmission member that transmits the rotational force of the turbine rotor disk 54 to the compressor rotor disk 52. One end of the torque tube 53 is engaged with the compressor rotor disk 52 which is located at the most downstream end in the flow direction of air among the plurality of compressor rotor disks 52, and the other end of the torque tube 53 has a plurality of ends. One of the turbine rotor disks 54 may be engaged with the turbine rotor disk 54 located at the most upstream end in the flow direction of the combustion gas. Protrusions are formed at one end and the other end of the torque tube 53, and grooves are engaged with the protrusions at each of the compressor rotor disk 52 and the turbine rotor disk 54, so that the torque tube 53 is a compressor rotor disk. Relative rotation relative to 52 and turbine rotor disk 54 can be prevented.

In addition, the torque tube 53 may be formed in a hollow cylinder shape so that the air supplied from the compressor 200 may flow through the torque tube 53 to the turbine 400. The torque tube 53 is strongly formed due to the characteristics of the gas turbine continuously operated for a long time, such as deformation and distortion, and can be easily assembled and dismantled for easy maintenance.

The tie rod 55 may be formed to penetrate the plurality of compressor rotor disks 52, the torque tube 53, and the plurality of turbine rotor disks 54. One end of the tie rod 55 may be fastened in the compressor rotor disk 52 located at the most upstream end of the plurality of compressor rotor disks 52 in the flow direction of air. The other end of the tie rod 55 may protrude to the opposite side of the compressor 200 relative to the turbine rotor disk 54 which is located at the most downstream end of the plurality of turbine rotor disks 54 in the flow direction of the combustion gas. have. The other end of the tie rod 55 may be engaged with the fixing nut 56.

The lock nut 56 may press the turbine rotor disk 54 located at the downstream end to the compressor 200 side. As the spacing between the compressor rotor disk 52 located at the most upstream end and the turbine rotor disk 54 located at the downstream end by the fixing nut 56 is reduced, the plurality of compressor rotor disks 52, the torque tube 53 and the plurality of turbine rotor disks 54 may be compressed in the axial direction of the rotor 50. Accordingly, axial movement and relative rotation of the plurality of compressor rotor disks 52, the torque tube 53, and the plurality of turbine rotor disks 54 can be prevented.

Meanwhile, in the present embodiment, one tie rod is formed to penetrate the centers of the plurality of compressor rotor disks, the torque tubes, and the plurality of turbine rotor disks, but is not limited thereto. That is, separate tie rods may be provided on the compressor side and the turbine side, respectively, and a plurality of tie rods may be disposed radially along the circumferential direction, and these may be mixed. Rotor 50 according to this configuration is supported both ends rotatably by a bearing, one end may be connected to the drive shaft of the generator.

The compressor 200 may include a compressor blade 220 that is rotated with the rotor 50 and a compressor vane 240 that is fixedly installed in the casing 100 to align the flow of air flowing into the compressor blade 220. have.

The compressor blades 220 are formed in plural, the plurality of compressor blades 220 are formed in plural stages along the axial direction of the rotor 50, and the plural compressor blades 220 are provided in the rotor 50 at each stage. Can be formed radially along the direction of rotation. Specifically, the root portion 222 of the compressor blade 220 is coupled to the compressor blade coupling slot of the compressor rotor disk 52, and the root portion 222 is a rotor blade 50 from the compressor blade coupling slot to the compressor blade 220. It may be formed in the form of a fir (tree) to prevent the deviation in the radial direction of rotation. At this time, the compressor blade coupling slot may be formed in a fir shape so as to correspond to the root portion 222 of the compressor blade.

In the present embodiment, the compressor blade root portion 222 and the compressor blade coupling slot are formed in a fir shape, but are not limited thereto and may be formed in a dove tail shape or the like. Alternatively, the compressor blade may be fastened to the compressor rotor disk 52 using a fastener other than the above type, for example, a fastener such as a key or a bolt.

Compressor rotor disk 52 and compressor blade 220 are typically combined in a tangential type or an axial type. In the present embodiment, the compressor blade root portion 222 is as described above. Likewise, the compressor blade is formed in a so-called axial type that is inserted along the axial direction of the rotor 50 in the coupling slot. Accordingly, a plurality of compressor blade coupling slots according to the present embodiment may be formed, and the plurality of compressor blade coupling slots may be arranged radially along the circumferential direction of the compressor rotor disk 52.

The compressor vanes 240 may be formed in plural, and the plurality of compressor vanes 240 may be formed in plural stages along the axial direction of the rotor 50. Here, the compressor vanes 240 and the compressor blades 220 may be alternately arranged along the air flow direction.

In addition, the plurality of compressor vanes 240 may be radially formed along the rotation direction of the rotor 50 for each stage.

The combustor 300 may generate high energy, high temperature, high pressure combustion gas by mixing and combusting air introduced from the compressor 200 with fuel. In detail, the combustor 300 may include a plurality of cans, and the plurality of cans may be arranged in the combustor casing 103 along the rotation direction of the rotor 50.

In addition, each candle includes a liner into which the compressed air flows from the compressor 200, a burner for injecting and burning fuel into the air flowing into the liner, and a transition piece for guiding combustion gas generated in the burner to the turbine 400. can do.

The liner may include a flame barrel forming the combustion chamber and a flow sleeve surrounding the flame barrel to form an annular space.

The burner may include a fuel injection nozzle formed at the front end of the liner to inject fuel into the air flowing into the combustion chamber, and a spark plug formed at the wall portion of the liner to ignite the mixed air and fuel in the chamber.

The transition piece may be formed such that the outer wall portion is cooled by the air supplied from the compressor 200. The outer wall portion of the transition piece may not be damaged by the high temperature of the combustion gas by the supplied cooling air. That is, a cooling hole for injecting air into the transition piece is formed, and the air can cool the main body therein through the cooling hole.

On the other hand, air cooled by the transition piece may flow into the annular space of the liner. Cooling air may cool the outer wall of the liner through cooling holes formed in the flow sleeve.

Here, although not separately shown, a dispenser serving as a guide feather may be formed between the compressor 200 and the combustor 300 to adjust the flow angle of the air flowing into the combustor 300 to the design flow angle. have.

The turbine 400 may be formed similarly to the compressor 200. The turbine 400 may include a turbine blade 420 rotated with the rotor 50 and a turbine vane 440 fixedly installed to the casing 100 to align the flow of air flowing into the turbine blade 420. have.

The turbine blades 420 are formed in plural, and the plurality of turbine blades 420 are formed in plural stages along the axial direction of the rotor 50. In the present exemplary embodiment, the turbine blade 420 is configured in four stages, and the first stage turbine blade 424, the second stage turbine blade 425, and the third stage are sequentially moved from the upstream side to the downstream side along the axial direction of the rotor 50. The stage turbine blade 426 and the four stage turbine blade 427 are arrange | positioned. However, the present invention is not limited thereto, and turbine blades of less than four or more stages may be disposed. In addition, the plurality of turbine blades 420 may be formed radially along the rotation direction of the rotor 50 at each stage.

The root portion 422 of the turbine blade 420 is coupled to the turbine blade coupling slot of the turbine rotor disk 54, and the root portion 422 allows the turbine blade 420 of the rotor 50 from its turbine blade coupling slot. It may be formed in the form of a fir-tree to prevent deviation in the radial direction of rotation. In this case, the turbine blade coupling slot may be formed in a fir shape so as to correspond to the root portion 422 of the turbine blade.

In the present embodiment, the turbine blade root portion 422 and the turbine blade coupling slot are formed in a fir shape, but are not limited thereto and may be formed in a dove tail shape or the like. Alternatively, the turbine blade 420 may be fastened to the turbine rotor disk 54 by using a fastener such as a key or bolt other than the above-described configuration.

Here, the turbine rotor disk 54 and the turbine blade 420 are typically combined in a tangential type or an axial type. In the present embodiment, the turbine blade root portion 422 is described above. As described above, the turbine blade coupling slot is formed in a so-called axial type that is inserted along the axial direction of the rotor 50. Accordingly, a plurality of turbine blade coupling slots according to the present embodiment may be formed, and the plurality of turbine blade coupling slots may be arranged radially along the circumferential direction of the turbine rotor disk 54.

The turbine vanes 440 may be formed in plural, and the plurality of turbine vanes 440 may be formed in plural stages along the axial direction of the rotor 50. Here, the turbine vanes 440 and the turbine blades 420 may be alternately arranged along the air flow direction.

In the present embodiment, since the turbine blade 420 is configured in four stages, the turbine vane 440 is also configured in four stages, and the first stage turbine vanes are sequentially moved from the upstream side to the downstream side along the axial direction of the rotor 50. 444, the 2nd stage turbine vane 445, the 3rd stage turbine vane 446, and the 4th stage turbine vane 447 are arrange | positioned at the front end (upstream side) of the turbine blade of each stage. However, the present invention is not limited thereto, and turbine vanes of less than four or more stages may be disposed. The plurality of turbine vanes 440 may be radially formed along the rotation direction of the rotor 50 at each stage.

Here, since the turbine 400 contacts the combustion gas of high temperature and high pressure unlike the compressor 200, the turbine 400 needs cooling means to prevent damage such as deterioration. The gas turbine 1 according to the present exemplary embodiment may add air compressed at a portion of the compressor 200 to the outside of the casing 100, including an external cooling system, and supply the air to the turbine 400.

In the gas turbine 1, the air flowing into the casing 100 is compressed by the compressor 200, and the air compressed by the compressor 200 is mixed with fuel by the combustor 300 and then combusted to produce combustion gas. The combustion gas generated in the combustor 300 flows into the turbine 400. The combustion gas introduced into the turbine 400 is rotated through the turbine blade 420 and then discharged to the atmosphere through the diffuser. The rotor 50 rotated by the combustion gas includes the compressor 200 and the generator. Can be driven. That is, some of the mechanical energy obtained from the turbine 400 may be supplied with energy required to compress air in the compressor 200, and the other may be used to generate electric power with a generator.

2 is a view showing a combustion temperature variation reduction system between the candle of the combustor according to an embodiment of the present invention.

Referring to FIG. 2, a system for reducing a variation in combustion temperature between candles of a combustor may include a compressor 200, a combustor 300, a fuel tank 305, a turbine 400, an exhaust chamber 450, and a controller 500. Can be.

 The compressor 200 may suck air and compress the air at high pressure, and supply the compressed air to the combustor 300. The combustor 300 may serve to mix compressed air and fuel and combust it, and supply the high pressure combustion gas generated by the combustion to the turbine 400. The turbine 400 may generate power by rotating a plurality of turbine blades using combustion gas of high temperature and high pressure. Combustion gas discharged from the turbine 400 may be discharged to the outside through the exhaust chamber 450. Flue gas may be discharged by the diffuser (not shown) disposed in the exhaust chamber 450 may be reduced. The exhaust chamber 450 may be connected to the downstream side of the turbine 400.

The fuel tank 305 may provide fuel to the combustor 300. The fuel tank 305 and the combustor 300 may be connected by a fuel line 310, and a fuel valve 330 may be provided on the fuel line 310. The combustor 300 may include a plurality of cans, and the fuel line 310 and the fuel valve 330 may be provided as many as the number of cans. The fuel tank 305 may adjust the temperature of the fuel provided for each fuel line 310, and the fuel valve 330 may adjust the amount of fuel provided to the combustor 300.

The exhaust chamber 450 may be provided with a sensor 457. The sensor 457 may be disposed in a diffuser (not shown) inside the exhaust chamber 450. The sensor 457 may measure data for estimating the temperature of the combustion gas. Specifically, the sensor 457 may measure the calorific value of the combustion gas discharged from the turbine 400 or the temperature of the diffuser (not shown). That is, the data for estimating the temperature of the combustion gas may include the temperature of the diffuser (not shown) and the calorific value of the combustion gas. For example, the sensor 457 may be a thermocouple sensor that contacts the diffuser (not shown) and measures the temperature of the diffuser (not shown). The thermocouple sensor may be a thermometer using a thermoelectric thermoelectric power, it is possible to obtain the temperature from the value of the thermoelectric power generated as the temperature of the other contact is maintained by bonding two ends of two metal wires to maintain a constant temperature of one contact. . The temperature of the combustion gas may be estimated using the temperature of a diffuser (not shown) in which the temperature rises due to the combustion gas. As another example, the sensor 457 may be a gas sensor that measures the calorific value of the combustion gas. The temperature of the combustion gas may be estimated using the calorific value of the combustion gas.

The controller 500 may estimate the temperature of each candle based on the temperature of the diffuser (not shown) and the calorific value of the combustion gas measured by the sensor 457. In this case, the controller 500 may use matching data between the candle stored in the table 550 and the plurality of sensors 457. The table 550 may store data about which of the sensors 457 the combustion gas discharged from one of the plurality of cans reaches according to the load condition of the gas turbine. Depending on the load condition of the gas turbine, which can is a can for discharging combustion gas that affects each of the sensors 457. The table 550 may store data matching the candle and the sensors 457 according to load conditions of various gas turbines. Accordingly, the controller 500 may obtain matching data between the candle and the sensors 457 in the table 550 in consideration of the load condition of the gas turbine, and based on the matching data and the data obtained by the sensors 457. Can infer the temperature of each candle. For example, the control unit 500 may estimate the temperature of the combustion gas based on the temperature of the diffuser (not shown) measured by any one sensor 457, and any one of the above based on the estimated temperature of the combustion gas. The temperature of the can matched with the sensor 457 may be estimated. As another example, the controller 500 may calculate a web index, which is a variable for defining energy released per unit time of fuel, based on the calorific value of the combustion gas measured by one sensor 457. The controller 500 may estimate the temperature of the combustion gas based on the Weber index, and may estimate the temperature of the can matched with any one sensor 457 based on the estimated temperature of the combustion gas.

The controller 500 may estimate the temperature of each candle based on the data measured by the sensor 457, and control the fuel injected into the plurality of candles according to the temperature of each candle. The controller 500 may control the fuel tank 305 to control the temperature of the fuel injected into each of the cans, and the fuel valve 330 to control the amount of fuel injected into each of the cans. The control unit 457 controls each of the plurality of fuel valves 330 to increase the amount of fuel supplied to the can of which the temperature is lower than the reference temperature among the cans, and The amount can be reduced. The reference temperature may mean a combustion temperature maintained by the can constituting the combustor 300 in the combustion process. In general, temperature variations between the candles can be tolerated up to 55 degrees. The greater the temperature difference between the candles, the less efficient the gas turbine. The combustion temperature variation reduction system between the candles of the combustor according to the embodiment of the present invention can reduce the temperature variation between the candles during the combustion process, the operation efficiency of the gas turbine can be improved as the temperature variation between the candles is reduced. .

3 is a view showing a combustor according to an embodiment of the present invention, Figure 4 is a view showing an exhaust chamber according to an embodiment of the present invention.

2 and 3, the fuel tank 305 includes a plurality of candles constituting the combustor 300 through a plurality of fuel lines 310a, 310b, 310c, 310d, 310e, 310f, 310g, 310h. 300a, 300b, 300c, 300d, 300e, 300f, 300g, and 300h can be provided with fuel. A plurality of fuel valves 330a, 330b, 330c, 330d, 330e, 330f, 330g, and 330h may be disposed in each of the fuel lines 310a, 310b, 310c, 310d, 310e, 310f, 310g, and 310h.

The combustor 300 includes the first can 300a, the second can 300b, the third can 300c, the fourth can 300d, the fifth can 300e, the sixth can 300f, and the seventh can. 300g and the eighth can 300h. The first can 300a may be connected to the first fuel line 310a, and the first fuel valve 330a may be disposed on the first fuel line 310a. The second can 300b may be connected to the second fuel line 310b, and a second fuel valve 330b may be disposed on the second fuel line 310b. The third can 300c may be connected to the third fuel line 310c, and the third fuel valve 330c may be disposed on the third fuel line 310c. The fourth can 300d may be connected to the fourth fuel line 310d, and the fourth fuel valve 330d may be disposed on the fourth fuel line 310d. The fifth can 300e may be connected to the fifth fuel line 310e, and the fifth fuel valve 330e may be disposed on the fifth fuel line 310e. The sixth can 300f may be connected to the sixth fuel line 310f, and the sixth fuel valve 330f may be disposed on the sixth fuel line 310f. The seventh can 300g may be connected to the seventh fuel line 310g, and the seventh fuel valve 330g may be disposed on the seventh fuel line 310g. The eighth can 300h may be connected to the eighth fuel line 310h, and the eighth fuel valve 330h may be disposed on the eighth fuel line 310h.

2 and 4, the combustion gas introduced into the turbine 400 may flow into the exhaust chamber 450. The exhaust chamber 450 may mean a part of the casing connected to the downstream side of the turbine. The exhaust chamber 450 is disposed along the inner circumferential surface of the vehicle wall 451, the outer diffuser 453 disposed along the inner circumferential surface of the vehicle wall 451, and the outer diffuser 453, which surrounds the rotor 55. 455 may be included. The external diffuser 453 may be provided along the inner circumferential surface of the compartment wall 451 in the radial direction of the compartment wall 451, and may have a cylindrical shape surrounding the rotor 55. The inner diffuser 455 is provided along the inner circumferential surface of the outer diffuser 453 in the radial direction of the outer diffuser 453, and may have a cylindrical shape surrounding the rotor 55.

Sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, 457h may be disposed on the internal diffuser 455. The sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, and 457h may be spaced apart from each other at regular intervals. The sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, and 457h include a first sensor 457a, a second sensor 457b, a third sensor 457c, a fourth sensor 457d, and a fifth It may include a sensor 457e, a sixth sensor 457f, a seventh sensor 457g, and an eighth sensor 457h. For example, the sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, and 457h may measure the temperature of the internal diffuser 455 whose temperature is increased by the combustion gas. The sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, and 457h are each spaced apart from each other and the internal diffuser 455 may vary in temperature depending on the combustion gases it contacts. 457b, 457c, 457d, 457e, 457f, 457g, 457h) The temperatures of the internal diffuser 455 respectively measured may be different. As another example, the sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, and 457h may measure the calorific value of the combustion gas.

2 to 4, the candle 300a, 300b, 300c, 300d, 300e, 300f, 300g, 300h and the sensors 457a, 457b, 457c, 457d, 457e, 457f, depending on the load condition of the gas turbine. 457g, 457h) may be different. As the load condition of the gas turbine is changed, the combustion gas discharged from each of the candles 300a, 300b, 300c, 300d, 300e, 300f, 300g, and 300h may flow with different rotational components. In the embodiment of the present invention, the number of candles and the number of sensors are the same, but the number of sensors may be equal to or greater than the number of candles.

For example, when the load condition of the gas turbine is the first condition, the combustion gas discharged from the first can 300a may flow to the first sensor 457a and the combustion gas discharged from the second can 300b. May flow to the second sensor 457b, the combustion gas discharged from the third can 300c may flow to the third sensor 457c, and the combustion gas discharged from the fourth can 300d may be The combustion gas discharged from the fifth can 300e may flow to the fourth sensor 457d, and the combustion gas discharged from the fifth can 300e may flow to the fifth sensor 457e. 457f, the combustion gas discharged from the seventh can 300g may flow to the seventh sensor 457g, and combustion gas discharged from the eighth can 300h is the eighth sensor 457h. Can flow. At this time, the first sensor 457a may not be affected by the combustion gas discharged from the cans other than the first can 300a. That is, the first sensor 457 measures the temperature of the internal diffuser 455 in which the temperature is increased by the combustion gas discharged from the first can 300a or the calorific value of the combustion gas discharged from the first can 300a. Can be measured. In conclusion, the combustion gas discharged from the can of any one of the candles 300a, 300b, 300c, 300d, 300e, 300f, 300g, 300h is the same as the sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, 457h. Flow toward at least one sensor, and the at least one sensor may not be affected by the combustion gases discharged from cans other than the one. The controller 500 may control the temperature of the fuel supplied to the first can 300a and the amount of fuel based on the data measured by the first sensor 457a. When the temperature of the first can 300a is greater than the reference temperature of the can, the controller 500 controls the fuel tank 305 to lower the temperature of the fuel provided to the first can 300a or the first fuel valve ( The amount of fuel provided to the first can 300a may be reduced by controlling the 330a. The controller 500 includes a second sensor 457b, a third sensor 457c, a fourth sensor 457d, a fifth sensor 457e, a sixth sensor 457f, a seventh sensor 457g, and an eighth sensor. The second can 300b, the third can 300c, the fourth can 300d, the fifth can 300e, the sixth can 300f, and the seventh can (457h) based on the measured data. 300g) and the temperature of the fuel supplied to each of the eighth can 300h and the amount of fuel can be controlled. The control unit 500 according to the temperature of the inferred candle (300a, 300b, 300c, 300d, 300e, 300f, 300g, 300h) and the fuel tank 305 and the fuel valve (330a, 330b, 330c, 330d, 330e, 330f, 330g and 330h may be controlled to reduce the temperature deviation between the candles 300a, 300b, 300c, 300d, 300e, 300f, 300g and 300h.

As another example, when the load condition of the gas turbine is the second condition, the combustion gas discharged from the first can 300a may flow to a sensor other than the first sensor 457a. That is, unlike when the load condition of the gas turbine is the first condition, the candle (300a, 300b, 300c, 300d, 300e, 300f, 300g, 300h) and the sensors (457a, 457b, 457c, 457d, 457e, 457f, 457g, 457h) may match. The controller 500 may control the candles 300a, 300b, 300c, 300d, 300e, 300f, 300g, and 300h based on the changed matching relationship.

Unlike the above-described example, the number of candles, fuel lines, fuel valves and sensors may not be particularly limited.

5 is a view showing an exhaust chamber according to another embodiment of the present invention. For simplicity of description, descriptions overlapping with those of FIG. 4 will be omitted.

2, 3, and 5, the sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, 457h may be disposed on an inner circumferential surface of the external diffuser 453. The sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, and 457h are disposed in the circumferential direction with respect to the rotor 55. The first sensor 457a, the second sensor 457b, and the third sensor ( 457c), a fourth sensor 457d, a fifth sensor 457e, a sixth sensor 457f, a seventh sensor 457g, and an eighth sensor 457h. The sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, 457h are each heated up by the combustion gas discharged from each of the candles 300a, 300b, 300c, 300d, 300e, 300f, 300g, 300h. The temperature of the external diffuser 453 may be measured, or the calorific value of the combustion gas discharged from each of the candles 300a, 300b, 300c, 300d, 300e, 300f, 300g, and 300h may be measured. The sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, 457h are each spaced apart from each other and the external diffuser 453 may vary in temperature depending on the combustion gases it contacts. 457b, 457c, 457d, 457e, 457f, 457g, 457h) The temperature of the external diffuser 453 measured by each may be different.

The controller 500 controls the candles 300a, 300b, 300c, 300d, 300e, and 300f according to the temperature of the external diffuser 453 measured by the sensors 457a, 457b, 457c, 457d, 457e, 457f, 457g, and 457h. , 300g, 300h) can be inferred for each temperature. In addition, the control unit 500 according to the calorific value of the combustion gas measured by each of the sensors (457a, 457b, 457c, 457d, 457e, 457f, 457g, 457h) the candle (300a, 300b, 300c, 300d, 300e, 300f, 300 g, 300 h) can be inferred for each temperature. The controller 500 controls the fuel tank 305 and the fuel valve 330 according to the temperatures of the inferred candles 300a, 300b, 300c, 300d, 300e, 300f, 300g, and 300h to detect the candles 300a, 300b, and 300c. , 300d, 300e, 300f, 300g, 300h) can reduce the temperature deviation.

6 is a flowchart illustrating a method of reducing a combustion temperature variation between candles of a combustor according to an exemplary embodiment of the present invention.

Referring to FIG. 6, the method for reducing the combustion temperature deviation between the candles of the combustor controls the fuel provided to each of the cans by inferring the temperatures of each of the plurality of cans constituting the combustor, thereby reducing the combustion temperature variation between the candles. have.

Sensors can measure data to estimate the temperature of the flue gas emitted from each candle. Here, the data for estimating the temperature of the combustion gas may include the temperature of the diffuser to which the sensors are attached and the calorific value of the combustion gas. Each of the sensors may be spaced apart from each other, and the sensors may measure a state of the combustion gas discharged from different candles (S100).

The controller may match the candle with sensors measuring the combustion gas emitted from each of the candles. Depending on the load condition of the gas turbine, the direction in which the combustion gas discharged from one can flows may be changed. Accordingly, the matching relationship between the candle and the sensors may be stored in the table in advance according to the load condition of the gas turbine (S200).

The controller may infer the temperature of each of the cans matching each of the sensors based on the data measured by each of the sensors. The controller may determine which can is associated with data measured by each of the sensors based on a matching relationship between the candles stored in the table and the sensors. The controller may estimate the temperature of the combustion gas based on the temperature of the diffuser measured by one of the sensors, and estimate the temperature of the can matching the one of the sensors based on the estimated temperature of the combustion gas. . In addition, the control unit may calculate the web index, which is a variable for defining the energy released per unit time of the fuel based on the calorific value of the combustion gas measured by any one sensor. The control unit may estimate the temperature of the combustion gas based on the Weber index, and may estimate the temperature of the can matching any one sensor based on the estimated temperature of the combustion gas (S300).

The controller may compare the temperature of each of the inferred cans with a reference temperature of the cans. The plurality of cans may each have a different combustion temperature. The controller may determine whether the temperature of each candle is above or below a reference temperature in order to reduce the combustion temperature variation between the candles (S400).

The controller may lower the temperature of the fuel provided to the can or reduce the amount of fuel when the temperature of one can is equal to or higher than the reference temperature of the can. The controller may increase the temperature of the fuel provided to the can or increase the amount of fuel when the temperature of any one can is equal to or lower than the reference temperature of the can. Through this, the combustion temperature variation between the candles can be reduced, the efficiency of the gas turbine can be increased (S500).

Although the embodiments of the present invention have been described above with reference to the accompanying drawings, those skilled in the art may implement the present invention in other specific forms without changing the technical spirit or essential features thereof. You will understand that. Therefore, it should be understood that the embodiments described above are exemplary in all respects and not restrictive.

Claims (17)

A combustor comprising a plurality of cans;
A turbine for rotating the turbine blade using the combustion gas introduced from the combustor;
A diffuser for discharging the combustion gas passing through the turbine;
A sensor disposed in the diffuser to measure data for estimating the temperature of the combustion gas; And
And a control unit controlling fuel injected into the plurality of candles based on data measured by the sensor.
Reduction system of combustion temperature deviation between candles of the combustor. According to claim 1,
The sensor is disposed in the diffuser more than the number of the plurality of candles,
Each of the plurality of sensors measures data for estimating the temperature of the combustion gas discharged from each of the plurality of cans,
Reduction system of combustion temperature deviation between candles of the combustor. The method of claim 2,
Combustion gas discharged from one of the cans flows toward at least one of the sensors,
The at least one sensor is not affected by the combustion gases emitted from the cans other than the one can,
Reduction system of combustion temperature deviation between candles of the combustor. According to claim 1,
A fuel tank for supplying fuel to each of the candles;
A plurality of fuel lines connecting the fuel tank and each of the cans; And
Further comprising a plurality of fuel valves disposed on the fuel lines,
The control unit controls the opening and closing degree of each of the fuel valves,
Reduction system of combustion temperature deviation between candles of the combustor. The method of claim 4, wherein
The controller estimates the temperature of the candle based on the data measured by the sensor,
The control unit controls each of the fuel valves to increase the amount of fuel supplied to a can of which the temperature is lower than the reference temperature among the cans, and to reduce the amount of fuel to supply a can of which the temperature is higher than the reference temperature of the cans. ,
Reduction system of combustion temperature deviation between candles of the combustor. The method of claim 4, wherein
The controller estimates the temperature of the candle based on the data measured by the sensor,
The control unit controls the fuel tank to provide a fuel having a higher temperature than a preset fuel temperature value in a can of which the temperature is lower than a reference temperature among the cans, and a preset fuel temperature value in a can of which the temperature is higher than a reference temperature of the cans. To provide cooler fuel,
Reduction system of combustion temperature deviation between candles of the combustor. The method of claim 4, wherein
The fuel tank adjusts the temperature of the fuel provided for each of the fuel lines,
Reduction system of combustion temperature deviation between candles of the combustor. According to claim 1,
The control unit includes a table matching the plurality of sensors arranged in accordance with a load condition of the gas turbine and the cans for discharging the combustion gas measured by each of the sensors,
The controller estimates the temperature of the cans by matching the sensors and the cans based on the table.
Reduction system of combustion temperature deviation between candles of the combustor. According to claim 1,
The diffuser is disposed in an exhaust chamber surrounding the turbine,
The diffuser includes an inner diffuser surrounding the rotor of the gas turbine and an outer diffuser surrounding the inner diffuser,
The sensor is disposed in at least one of the internal diffuser and the external diffuser,
Reduction system of combustion temperature deviation between candles of the combustor. According to claim 1,
The sensor is a thermocouple sensor in contact with the diffuser to measure the temperature of the diffuser,
Reduction system of combustion temperature deviation between candles of the combustor. According to claim 1,
The sensor is a gas sensor for measuring the calorific value of the combustion gas,
Reduction system of combustion temperature deviation between candles of the combustor. The method of claim 11, wherein
The control unit,
Calculating the web index which is a variable for defining the energy released per unit time of fuel based on the calorific value of the combustion gas measured by each of the plurality of sensors,
Inferring the temperature of each of the candles based on the Weber exponent,
Reduction system of combustion temperature deviation between candles of the combustor. In the method of reducing the combustion temperature variation for each can of the combustor for inferring the temperature of each of the plurality of cans constituting the combustor,
Sensors measuring data to estimate the temperature of the flue gas exiting each of the cans;
Matching the cans with the sensors disposed in a diffuser connected to an end of a turbine according to a load condition of a gas turbine;
Inferring a temperature of each of the candles based on data measured by each of the sensors;
Controlling fuel provided to each of the cans based on a temperature of each of the cans,
A method of reducing the variation in combustion temperature between the candles of the combustor. The method of claim 13,
Matching the sensors with the candles,
Specifying which of the sensors the combustion gas discharged from one of the cans reaches according to the load condition of the gas turbine,
Matching the candle and the sensors according to the load condition of the gas turbine,
A method of reducing the variation in combustion temperature between the candles of the combustor. The method of claim 13,
Inferring the temperature of each of the candles based on the data measured by each of the sensors,
Inferring the temperature of the combustion gas based on the temperature of the diffuser or the calorific value of the combustion gas measured by the sensors,
Inferring the temperature of each of the cans matching the sensors through the temperature of the combustion gas,
A method of reducing the variation in combustion temperature between the candles of the combustor. The method of claim 13,
Controlling fuel provided to each of the cans based on a temperature of each of the cans,
Increasing the amount of fuel supplied to a can of which the temperature is lower than a reference temperature among the cans, and reducing the amount of fuel to supply a can of which the temperature is higher than the reference temperature of the cans,
A method of reducing the variation in combustion temperature between the candles of the combustor. The method of claim 13,
Controlling fuel provided to each of the cans based on a temperature of each of the cans,
The one of the cans having a lower temperature than the reference temperature is provided with a fuel having a higher temperature than the predetermined fuel temperature value, The one of the cans with a higher temperature than the reference temperature is provided a fuel having a temperature lower than the predetermined fuel temperature value,
A method of reducing the variation in combustion temperature between the candles of the combustor.

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