KR101752110B1 - Gas turbine plant, control device thereof, and gas turbine operation method - Google Patents

Gas turbine plant, control device thereof, and gas turbine operation method Download PDF

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KR101752110B1
KR101752110B1 KR1020167002453A KR20167002453A KR101752110B1 KR 101752110 B1 KR101752110 B1 KR 101752110B1 KR 1020167002453 A KR1020167002453 A KR 1020167002453A KR 20167002453 A KR20167002453 A KR 20167002453A KR 101752110 B1 KR101752110 B1 KR 101752110B1
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amount
intake air
unit
gas turbine
air amount
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KR1020167002453A
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Korean (ko)
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KR20160027073A (en
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요스케 에토
준 사사하라
요스케 기타우치
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미츠비시 히타치 파워 시스템즈 가부시키가이샤
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Turbines (AREA)

Abstract

The control device 50 includes a temperature regulation control section 51 for controlling the valve opening degree of the fuel flow rate control valve 47 so that the inlet temperature of the turbine 21 into which the combustion gas flows is kept constant, To control the intake air amount adjuster 15 so as to change the intake air amount in the air compressor 11 to the positive correlation with the change in the unit calorie amount by taking the unit heat amount of the fuel supplied from the calorimeter 55, (52).

Figure R1020167002453

Description

TECHNICAL FIELD [0001] The present invention relates to a gas turbine plant, a control device thereof, and a method of operating the gas turbine,

The present invention relates to a gas turbine plant having a gas turbine, a control device thereof, and a method of operating the gas turbine. The present application claims priority based on Japanese Patent Application No. 2013-185230, filed on September 6, 2013, the contents of which are incorporated herein by reference.

The gas turbine includes a compressor for compressing the air, a combustor for combusting the fuel in the air compressed by the compressor to generate the combustion gas, and a turbine driven by the combustion gas. The combustor is connected to a fuel line for supplying fuel from the outside to the combustor. The fuel line is provided with a fuel flow rate regulating valve for regulating the flow rate of fuel supplied to the combustor. The gas turbine is connected to, for example, a generator that generates electricity by driving the gas turbine.

As a method of operating this gas turbine, for example, there is a method disclosed in Patent Document 1 below. This method is a method called a temperature control method in which the valve opening degree of the fuel flow rate control valve is adjusted so that the temperature of the turbine inlet through which the combustion gas flows is maintained at a predetermined upper limit temperature.

Japanese Patent Application Laid-Open No. 8-42360

In the case of a gas turbine, if the amount of heat per unit volume of fuel supplied to the combustor is large, the inlet temperature of the turbine rises if the fuel flow rate and the intake air amount remain constant. In this case, in the temperature control method, the valve opening degree of the fuel flow rate control valve is reduced to reduce the flow rate of the fuel supplied to the combustor so that the inlet temperature of the turbine becomes a predetermined upper limit value.

Thus, in the temperature control method, the amount of heat input to the turbine is maintained with respect to an increase in the unit calorific value, but the gas flow rate through the turbine decreases, and the gas turbine output decreases.

Therefore, it is an object of the present invention to provide a gas turbine plant, a control device thereof, and a method of operating a gas turbine that can suppress variations in gas turbine output while maintaining the inlet temperature of the turbine at a constant level.

According to an aspect of the present invention for achieving the above object, there is provided a control apparatus for a gas turbine plant,

A combustor for combusting fuel in the air compressed by the compressor to generate a combustion gas; a turbine driven by the combustion gas; and a control unit for controlling the flow rate of the fuel supplied to the combustor, A control unit for controlling the valve opening degree of the fuel flow rate control valve so that an inlet temperature of the turbine into which the combustion gas flows is kept constant; And an intake air amount control unit for controlling the intake air amount adjuster so that the intake air amount of the compressor is changed in a positive correlation with a change in the amount of the unit calorie by receiving the unit heat amount as a heat amount per unit amount of the fuel supplied to the combustor from outside, .

In this control device, the valve opening degree of the fuel flow rate control valve is controlled by the temperature regulation control section so that the inlet temperature of the turbine is kept constant. That is, the temperature adjustment control is performed by the temperature adjustment control unit. During this temperature control, if the unit heat quantity becomes large, the inlet temperature of the turbine becomes high, so that the valve opening degree of the fuel flow rate valve becomes small, and the flow rate of the fuel supplied to the combustor becomes small. As a result, the inlet temperature of the turbine returns to its original temperature. At the time when the inlet temperature of the turbine returns to the original temperature by the temperature regulation control, the flow rate of the gas flowing into the turbine is reduced because the fuel flow rate is reduced. Therefore, at the time when the inlet temperature of the turbine returns to the original temperature by the temperature control, the output of the gas turbine is decreasing.

Therefore, the intake air amount control section of the control apparatus controls the intake air amount adjuster so that the intake air amount is changed with positive correlation with the change in the unit calorific value of the fuel. That is, the intake air amount control unit increases the intake air amount by the air compressor when the unit heat amount of the fuel becomes large. As a result, the flow rate of the gas flowing into the turbine increases, and the output of the gas turbine also increases. Therefore, in this control device, even if the unit calorific value of the fuel changes during the temperature control, the output fluctuation of the gas turbine can be suppressed.

According to another aspect of the present invention for achieving the above object, there is provided a control apparatus for a gas turbine plant,

A combustor for combusting fuel in the air compressed by the compressor to generate a combustion gas; a turbine driven by the combustion gas; and a control unit for controlling the flow rate of the fuel supplied to the combustor, A control unit for controlling the valve opening degree of the fuel flow rate control valve so that an inlet temperature of the turbine into which the combustion gas flows is kept constant; And an intake air amount control unit for controlling the intake air amount adjuster so that the intake air amount of the compressor is changed in negative correlation with the output fluctuation of the compressor, the combustor, and the gas turbine having the turbine.

The intake air amount control section of the control device controls the intake air amount adjuster so that the intake air amount is changed with negative correlation with the output fluctuation of the gas turbine under the temperature control. That is, the intake air amount control unit increases the intake air amount by the air compressor when the output of the gas turbine decreases during the temperature control. As a result, the flow rate of the gas flowing into the turbine increases, and the output of the gas turbine also increases. Therefore, in this control device, the output fluctuation of the gas turbine during the temperature regulation control can be suppressed.

Here, in the control apparatus for a gas turbine plant according to another aspect of the present invention, the intake air amount control unit may be configured to receive, from outside, a unit heat amount that is a heat amount per unit amount of the fuel supplied to the combustor, The intake air amount controller may be controlled so that the intake air amount is changed.

In the control device for any one of the gas turbine plants that receives the unit calorific value of fuel from the outside, the intake air amount control unit sets the intake air amount after the change so that the output of the gas turbine before the change of the unit heat amount is maintained .

This control device can further suppress the output fluctuation of the gas turbine during the temperature regulation control.

Further, in the control device for any one of the gas turbine plants that receives the unit calorific value of the fuel from the outside, the intake air amount adjuster is provided on the intake port side of the casing of the compressor and changes the intake air amount Wherein the intake air amount control unit controls the amount of change of the amount of heat of the fuel and the amount of change of the opening degree with respect to the reference opening degree of the inlet guide vanes, Determining a degree of opening degree change with respect to a variation amount of the quantity of heat of the fuel received from the outside by using a predetermined relationship and adding the standard degree of opening to the degree of opening degree change to determine a command degree of opening, And outputs the calculated intake air amount as a command value to the intake air amount regulator, With respect to the reference units obtained by subtracting the amount of heat becomes the variation in the opening or may be related to have a positive correlation between the amount of change.

In the control device for the gas turbine plant that outputs the command opening degree of the inlet guide vane to the intake air amount adjuster as a command value, the relationship is set such that the output of the gas turbine before the change of the unit calorie amount can be maintained The degree of opening degree change may be obtained.

In the control device for any one of the gas turbine plants that receives the unit calorific value of the fuel from the outside, the intake air amount control unit receives the unit calorie amount from the outside and indicates the amount of change in the intake air amount by the intake air amount adjuster And an output timing control unit for controlling the output timing of the command value to the intake air amount adjuster so that the command value arithmetic unit changes the intake air amount after a set time since the command value calculation unit receives the calorific value, The set time may be determined on the basis of the arrival time from when the intake air amount control unit receives the unit calorie from the outside until the fuel of the unit calorie amount reaches the combustor.

In this case, the output timing control section may receive the flow rate of the fuel from the outside, and determine the arrival time using the flow rate.

In the control apparatus for any one of the gas turbine plants having the output timing control section, the set time may be equal to the arrival time.

The intake air amount control unit of the control apparatus changes the intake air amount of the compressor at the time when the fuel having the unit heat amount changed reaches the combustor. Thus, in the control device, even when the unit calorific value of the fuel gas changes during the temperature regulation control, the change of the inlet temperature of the turbine can be suppressed.

In the control device for any one of the gas turbine plants having the output timing control section, the set time is shorter than the arrival time when the unit calorie amount received from the outside is large, May be longer than the arrival time.

The intake air amount control section of the control device changes the intake air amount of the compressor before the fuel reaches the combustor when the unit heat quantity of the fuel becomes large. Further, the intake air amount control unit of the control apparatus changes the intake air amount of the compressor after the fuel reaches the combustor when the unit heat amount of the fuel is reduced. Thus, in the control device, even when the unit calorific value of the fuel gas changes during the temperature regulation control, the change of the inlet temperature of the turbine can be suppressed.

According to an aspect of the present invention, there is provided a gas turbine plant,

And a control device for controlling the fuel flow rate of the gas turbine.

Since the gas turbine plant also includes any one of the control devices described above, fluctuations in the output of the gas turbine during temperature control can be suppressed.

According to an aspect of the present invention, there is provided a method of operating a gas turbine,

A method of operating a gas turbine including a compressor for compressing air, a combustor for generating a combustion gas by burning fuel in the air compressed by the compressor, and a turbine driven by the combustion gas, A temperature regulation control step of controlling the flow rate of the fuel supplied to the combustor so that the inlet temperature of the incoming turbine is kept constant; And an intake air amount control step of changing the intake air amount of the compressor with a positive correlation with the change in the unit calorie amount is executed.

According to another aspect of the present invention, there is provided a method of operating a gas turbine,

A method of operating a gas turbine including a compressor for compressing air, a combustor for generating a combustion gas by burning fuel in the air compressed by the compressor, and a turbine driven by the combustion gas, A temperature control step of controlling a flow rate of the fuel supplied to the combustor so that an inlet temperature of the inlet turbine is kept constant; and a control step of controlling a flow rate of the fuel, And executes the intake air amount control process for changing the intake air amount.

Here, in the operation method of the gas turbine according to another aspect of the present invention, in the intake air amount control step, the unit heat amount, which is the heat amount per unit amount of the fuel supplied to the combustor, is received from the outside, So that the intake air amount may be changed.

In the operation method of any one of the above gas turbines which receives the unit calorific value of the fuel from the outside, the intake air amount control step changes the intake air amount after the change so that the output of the gas turbine before the change of the unit heat amount is maintained It may be decided.

In the operation method of any one of the gas turbines that receives the unit calorific value of fuel from the outside, the intake air amount control step includes a command for obtaining the command value indicating the amount of change in the intake air amount, And a timing control step of receiving the unit calorie amount from the command value calculation step and changing the intake air amount after a set time after the intake air amount is received by the command value calculation step, And may be determined based on the arrival time until the fuel reaches the combustor.

In this case, in the timing control step, the flow rate of the fuel may be received from the outside, and the arrival time may be determined using the flow rate.

In the operating method of any one of the gas turbines for executing the timing control step, the set time may be equal to the arrival time. The set time may be shorter than the arrival time when the unit heat amount received from the outside is larger and longer than the arrival time when the unit heat amount received from the outside is smaller.

According to one aspect of the present invention, it is possible to suppress the output fluctuation of the gas turbine during the temperature control.

1 is a flow diagram of a gas turbine plant according to a first embodiment of the present invention.
Fig. 2 is an explanatory view showing the relationship between temperature control curves of gas turbines and respective state points in the first embodiment of the present invention. Fig.
3 is an explanatory diagram showing the relationship between the amount of change in the amount of heat per unit of time and the amount of change in opening degree of the inlet guide vane in the first embodiment of the present invention.
4 is a flow diagram of a gas turbine plant according to a second embodiment of the present invention.
5 is a timing chart showing the timing of the opening degree change of the inlet guide vane according to the change of the unit calorific value of the fuel gas in the second embodiment of the present invention.

Hereinafter, various embodiments of the gas turbine plant according to the present invention will be described in detail with reference to the drawings.

"First embodiment"

A gas turbine plant according to a first embodiment of the present invention will be described with reference to Figs. 1 to 3. Fig.

1, a gas turbine plant according to the present embodiment includes a gas turbine 10, a generator 31 that generates electricity by driving the gas turbine 10, A gas compressor 35 for compressing the gas turbine 10, and a control device 50 for controlling the state of the gas turbine 10 and the like.

The gas turbine (10) includes an air compressor (11) for compressing air (A) to generate compressed air, a combustor (19) for combusting the fuel gas in the compressed air to generate a high temperature combustion gas, And a turbine 21 driven by the turbine.

The air compressor 11 has a compressor rotor 12, a compressor casing 13 rotatably covering the compressor rotor 12, and an intake air amount adjuster 15 for adjusting the intake air amount of the air A. The intake air amount adjuster 15 has an inlet guide vane 16 provided on the suction port side of the compressor casing 13 and a guide vane driver 17 for changing the opening degree of the inlet guide vane 16. [ A pressure gauge 56 for detecting the pressure in the compressed air passage is provided in the compressed air passage through which the compressed air flows between the discharge port of the air compressor 11 and the compressed air inlet of the combustor 19. [

The turbine 21 has a turbine rotor 22 that rotates by the combustion gas and a turbine casing 23 that rotatably covers the turbine rotor 22. The exhaust port of the turbine 21 is provided with a thermometer 57 for detecting the temperature of the exhaust gas, which is a combustion gas exhausted from the turbine 21. The compressor rotor 12 and the turbine rotor 22 are connected to each other and integrally constitute a gas turbine rotor 28.

The generator 31 has a generator rotor 32 and a generator casing 33 for rotatably covering the generator rotor 32. [ The generator rotor 32 is connected to the gas turbine rotor 28. As a result, when the gas turbine rotor 28 rotates, the generator rotor 32 also rotates integrally. The generator 31 is provided with an output system 58 for detecting the amount of power generated by the generator 31.

The gas compressor 35 has a compressor rotor 36 and a compressor casing 37 rotatably covering the compressor rotor. The compressor rotor 36 of the gas compressor 35 is mechanically connected to the generator rotor 32 or the gas turbine rotor 28 via the speed reducer 38. The discharge port of the gas compressor (35) and the combustor (19) are connected by a high-pressure fuel gas line (44). The high-pressure fuel gas line 44 is provided with a fuel flow rate regulating valve 47 for regulating the flow rate of the fuel gas passing through the high-pressure fuel gas line 44.

This gas turbine plant is supplied with fuel gas from a steelworks (61) and a coke plant (62). The steelworks 61 generates BFG (Blast Furnace Gas) as a low-calorie fuel gas from the blast furnace of the steelworks 61. In this furnace, a BFG line 41 through which BFG flows is connected. The BFG line 41 is provided with a BFG flow control valve 45 for controlling the flow rate of the BFG. The coke plant 62 generates COG (Coke Oven Gas) as a high-calorie fuel gas from the coke oven of the coke plant 62. A COG line 42 through which COG flows is connected to the coke oven. The COG line 42 is provided with a COG flow control valve 46 for controlling the flow rate of COG. The BFG line 41 and the COG line 42 join together to form a low-pressure fuel gas line 43. The low-pressure fuel gas line 43 is connected to the suction port of the gas compressor 35. The low-pressure fuel gas line 43 is provided with a calorimeter 55 for measuring the unit calorific value, which is the calorific value per unit amount (unit volume or unit weight) of gas passing through the gas.

In the following, in the case where only BFG flows, only COG flows in the low-pressure fuel gas line 43 and the high-pressure fuel gas line 44, and the case where BFG and COG are mixed with each other, The gas flowing in the gas line 43 and the high-pressure fuel gas line 44 is referred to as a fuel gas.

The control device 50 includes a temperature control unit 51 for controlling the valve opening degree of the fuel flow rate control valve 47 and an intake air amount control unit for controlling the opening degree of the inlet guide vane 16 of the intake air amount adjuster 15 52).

The temperature control section 51 controls the valve opening degree of the fuel flow rate regulating valve 47 so that the inlet temperature of the turbine 21 into which the combustion gas flows from the combustor 19 of the gas turbine 10 is maintained at a predetermined upper limit value. . For this reason, the temperature control section 51 needs to recognize the inlet temperature of the turbine 21. However, since the inlet temperature of the turbine 21 is extremely high at several hundreds of degrees Celsius, it is difficult to detect the inlet temperature of the turbine 21 with a thermometer such as a thermocouple. Therefore, in the present embodiment, the pressure in the compressed air passage between the discharge port of the air compressor 11 and the compressed air inlet of the combustor 19 and the temperature of the exhaust gas exhausted from the turbine 21 Substantially estimates the inlet temperature.

In the turbine 21, it can be considered that the gas adiabatically expands between the gas inlet of the turbine 21 and the gas outlet. The inlet temperature of the turbine 21 can be estimated if it is possible to grasp the turbine pressure ratio which is the ratio of the inlet pressure of the turbine 21 and the outlet pressure of the turbine 21 and the outlet temperature of the turbine 21. [

Incidentally, the inlet pressure of the turbine 21 is lower than the pressure at the gas inlet of the combustor 19, as much as the pressure loss when the gas passes through the combustor 19. However, it can be considered that this pressure loss is almost constant. Since the outlet pressure of the turbine 21 is substantially constant at approximately the atmospheric pressure, it can be handled as a substantially fixed value. Therefore, the pressure at the gas inlet of the combustor 19, which is lower than the inlet pressure of the turbine 21 by a certain pressure loss, can be replaced by the turbine pressure ratio. Therefore, if the pressure at the gas inlet of the combustor 19 and the outlet temperature of the turbine 21 can be grasped, the inlet temperature of the turbine 21 can be estimated.

In this embodiment, from the above viewpoint, the inlet temperature of the turbine 21 is substantially estimated from the pressure in the compressed air flow passage and the temperature of the exhaust gas exhausted from the turbine 21. Thus, in the present embodiment, the pressure in the compressed air flow path is detected by the pressure gauge 56, and the temperature of the exhaust gas exhausted from the turbine 21 is detected by the thermometer 57.

2, when the inlet temperature Tin of the turbine 21 is made constant, the pressure Pcs in the compressed air flow path, the temperature Tex of the exhaust gas, and the inlet temperature Tin of the turbine 21, The temperature Tex of the exhaust gas is lowered. The curve showing the relationship between the pressure Pcs in the compressed air flow path and the temperature Tex of the exhaust gas when the inlet temperature Tin of the turbine 21 is made constant is generally referred to as a temperature control curve H. [ The temperature adjustment control section 51 of the present embodiment stores a temperature adjustment curve H when the inlet temperature Tin of the turbine 21 is a predetermined upper limit value. The pressure Pcs in the compressed air passage detected by the pressure gauge 56 and the temperature Tex of the exhaust gas detected by the thermometer 57 are input to the temperature regulation control unit 51. [ The temperature control section 51 substantially estimates the inlet temperature of the turbine 21 as described above, but does not estimate the inlet temperature itself. That is, the temperature adjustment control unit 51 recognizes whether the inlet temperature of the turbine 21 is the upper limit value or higher or lower than the upper limit value by using the temperature control curve H when the inlet temperature is the upper limit value.

If the current state point S1 determined by the pressure Pcs1 in the current compressed air passage and the temperature Tex1 of the exhaust gas is on the temperature control curve H, In this case, the temperature adjustment control unit 51 recognizes that the current inlet temperature is the target upper limit value. Then, let it be assumed that the unit calorific value of the fuel gas becomes large while the flow rate of the compressed air supplied to the turbine 21 is constant. In this case, since the inlet pressure and the inlet temperature of the turbine 21 are increased, the pressure Pcs in the compressed air flow path becomes higher and becomes the pressure Pcs2, and the temperature Tex of the exhaust gas becomes higher and becomes the temperature Tex2. At the state point S2 defined by the pressure Pcs2 and the temperature Tex2, since the temperature Tex of the exhaust gas is higher than the temperature control curve H, the temperature regulation control unit 51 recognizes that the inlet temperature of the turbine 21 has become higher than the upper limit value. When it is recognized that the inlet temperature of the turbine 21 is higher than the upper limit value, the temperature regulation control section 51 instructs the fuel flow rate regulating valve 47 to reduce the valve opening degree. As a result, the valve opening degree of the fuel flow rate regulating valve 47 is reduced, and the flow rate of the fuel gas supplied to the combustor 19 is reduced. When the flow rate of the fuel gas is decreased, the temperature Tex of the exhaust gas is lowered and the pressure Pcs in the compressed air flow path is also lowered. Finally, the state point S3 (Pcs3, Tex3) is positioned on the temperature control curve H. That is, the inlet temperature of the turbine 21 returns to the upper limit value of the target.

As described above, the temperature adjustment control unit 51 first recognizes whether the inlet temperature of the turbine 21 is the upper limit value or higher or lower than the upper limit value, from the pressure Pcs1 in the compressed air flow path and the exhaust gas temperature Tex1. The temperature regulating control section 51 controls the valve opening degree of the fuel flow regulating valve 47 so that the inlet temperature of the turbine 21 is maintained at the upper limit value based on the recognition. That is, the temperature adjustment control unit 51 executes the temperature adjustment control process.

However, at the state point S3 after the temperature regulation control by the temperature regulation control unit 51, the inlet temperature of the turbine 21 is the same as that before the increase in the unit heat quantity of the fuel gas, but the flow rate of the fuel gas is decreased, The flow rate of the combustion gas flowing into the turbine 21 is also reduced. As a result, at the state point S3, the inlet pressure of the turbine 21 is lower and the turbine pressure ratio is smaller than that before the increase in the unit heat quantity of the fuel gas. The output of the gas turbine 10 and the output of the entire gas turbine 10 are reduced at the state point S3 after the temperature regulation control by the temperature regulation control section 51 as compared with before the increase of the unit calorific value of the fuel gas .

Contrary to the above, when the flow rate of the compressed air supplied to the turbine 21 is constant and the unit calorific value of the fuel gas becomes small, the pressure Pcs in the compressed air flow path decreases and the temperature Tex of the exhaust gas . In this case, since the exhaust gas Tex at the state point S is lower than the temperature control curve H, the temperature adjustment control unit 51 recognizes that the inlet temperature of the turbine 21 has become lower than the upper limit value. When it is recognized that the inlet temperature of the turbine 21 has become lower than the upper limit value, the temperature regulation control section 51 gives an instruction to the fuel flow control valve 47 to increase the valve opening degree. As a result, the valve opening degree of the fuel flow rate regulating valve 47 becomes large, and the flow rate of the fuel gas supplied to the combustor 19 increases. When the flow rate of the fuel gas increases, the temperature Tex of the exhaust gas increases and the pressure Pcs in the compressed air flow path also increases, and finally the state point S returns to the temperature control curve H phase. At this state point S, the flow rate of the combustion gas flowing into the turbine 21 is also equal to the flow rate of the combustion gas flowing into the turbine 21 because the inlet temperature of the turbine 21 is the same as that before the unit heat quantity of the fuel gas is smaller, Respectively. As a result, at this state point S, the inlet pressure of the turbine 21 is higher and the turbine pressure ratio is larger than that before the unit heat quantity of the fuel gas is reduced. Therefore, at the state point S after the temperature regulation control by the temperature regulation control section 51, the output of the gas turbine 10 is increased as compared with before the unit heat quantity of the fuel gas is reduced.

As described above, when the unit calorific value of the fuel gas changes during the temperature control, the gas turbine output is also changed in accordance with the change. More specifically, the change in the gas turbine output is negatively correlated with the change in the unit calorific value of the fuel gas during the temperature regulation control.

Therefore, in this embodiment, in order to suppress the change of the gas turbine output in accordance with the change of the unit calorific value of the fuel gas during the temperature regulation control, the intake air amount control unit 52 controls the intake guide vane 16 of the intake air amount adjuster 15, As shown in FIG. That is, the intake air amount control unit 52 executes the intake air amount control step.

The intake air amount control unit 52 receives the unit calorific value of the fuel gas from the calorimeter 55 at any time. The intake air amount control unit 52 recognizes the change in the unit heat amount based on the received unit heat amount and controls the intake air amount adjusting unit 15 so that the intake air amount of the air compressor 11 is changed in positive correlation with the change in the unit heat amount. . In other words, the intake flow rate control section outputs a command value to the intake air amount adjuster 15 of the air compressor 11 so that the degree of opening of the inlet guide vane 16 changes with a positive correlation with a change in the unit calorie amount. That is, the intake air amount control unit 52 outputs a command value to the intake air amount adjuster 15 so that the opening degree of the inlet guide vane 16 becomes larger when the unit heat amount becomes larger.

As described above with reference to FIG. 2, when the unit calorific value of the fuel gas becomes large and the temperature adjustment control is executed, it is assumed that the state point S3 is located on the temperature control curve H. In this case, the intake air amount control unit 52 outputs a command value to the intake air amount adjuster 15 so that the opening degree of the inlet guide vane 16 becomes larger, based on the increase in the amount of heat of the unit.

When the opening degree of the inlet guide vane 16 is increased and the amount of intake air of the air compressor 11 is increased, the pressure Pcs in the compressed air flow path becomes higher and becomes the pressure Pcs4, while the temperature Tex of the exhaust gas is lowered to the temperature Tex4. At the state point S4 determined by the pressure Pcs4 and the temperature Tex4, since the temperature Tex of the exhaust gas is lower than the temperature control curve H, the temperature regulation control unit 51 recognizes that the inlet temperature of the turbine 21 has become lower than the upper limit value . Then, the temperature regulation control section 51 instructs the fuel flow rate regulating valve 47 to increase the valve opening degree. As a result, the valve opening degree of the fuel flow rate regulating valve 47 becomes large, and the flow rate of the fuel gas supplied to the combustor 19 increases. As the flow rate of the fuel gas increases, the temperature Tex of the exhaust gas increases and the pressure Pcs in the compressed air flow path almost equal to the inlet pressure of the turbine 21 increases. Finally, the state point S5 (Pcs5, Tex5) And is placed on the adjustment curve H. That is, the inlet temperature of the turbine 21 returns to the upper limit value of the target.

In this state point S5, the inlet temperature of the turbine 21 is the same as that at the state point S3 before the opening degree of the inlet guide vane 16 is increased. However, since the flow rate of the fuel gas is increased, 21 are increased. Therefore, at this state point S5, the turbine pressure ratio is higher than that at the state point S3 before the opening degree of the inlet guide vane 16 is increased. In addition, at this state point S5, the flow rate of the combustion gas flowing into the turbine 21 is increased as compared with the state point S3 before the opening degree of the inlet guide vane 16 is increased. Therefore, at this state point S5, the output of the gas turbine 10 is increased as compared with the state point S3 before the opening degree of the inlet guide vane 16 is increased.

Therefore, in this embodiment, even when the unit calorific value of the fuel gas changes during the temperature control, the fluctuation of the gas turbine output can be suppressed.

Here, the amount of change in opening degree of the inlet guide vane 16 when the unit heat quantity of the fuel gas is changed may be a predetermined unit change amount or a change amount corresponding to the change amount of the unit heat amount. Even if the opening degree of the inlet guide vanes 16 is changed in accordance with the change in the unit calorific value of the fuel gas when the change amount of the opening degree of the inlet guide vane 16 is changed as the unit change amount, (The output of the gas turbine 10) detected by the pressure sensor 58 is smaller than that before the change in the unit heat quantity, the opening degree of the inlet guide vane 16 is changed again as shown in Fig. 2 do.

In the case where the change amount of the opening degree of the inlet guide vanes 16 is a change amount corresponding to the change amount of the unit heat quantity, the intake air amount control section 52 stores in advance the relationship between the change amount of the unit heat quantity and the opening degree change amount. This relationship is a relationship in which the amount of opening degree change with respect to an increase in the amount of change in the unit calorie amount and the output of the gas turbine 10 can be substantially maintained. The intake air amount control unit 52 obtains the opening degree change amount corresponding to the variation amount of the unit heat amount by using this relationship.

When the change amount of the opening degree of the inlet guide vanes 16 is a change amount corresponding to the change amount of the unit heat quantity, the amount of change with respect to the reference unit heat quantity is adopted as the variation amount of the unit heat quantity, As the opening degree change amount, a change amount with respect to the reference opening degree of the inlet guide vane 16 may be adopted. In this case, as shown in Fig. 3, the intake air amount control unit 52 is supplied with the change amount Cd-Cs obtained by subtracting the reference unit heat amount Cs from the unit heat amount Cd measured by the calorimeter 55, (F) of the opening degree change amount Ac with respect to the reference opening degree As is previously stored in advance. This relationship (f) is also such that the opening degree change amount Ac increases with the increase of the amount of change of the unit calorific value Cd-Cs, and the output of the gas turbine 10 can be maintained. 3, the relationship (f) can hold the output of the gas turbine 10 by properly setting the slope of the line representing the relationship (f). The intake air amount control section 52 may store the relationship f as a function or may be stored as a map of the opening degree change amount for each change amount of the unit heat amount.

The intake air amount control unit 52 obtains the change amount Cd-Cs by subtracting the reference unit heat amount Cs from the unit heat amount Cd when the unit heat amount Cd is received from the calorimeter 55. [ Next, the intake air amount control unit 52 obtains the opening degree change amount Ac with respect to the change amount Cd-Cs using the relationship (f). Then, as shown in the following equation, the reference opening degree As is added to the opening degree change amount Ac with respect to the variation amount Cd-Cs to obtain the command opening degree Ai, and the command opening degree Ai is used as the command value, (15).

Ai = As + f (Cd-Cs) = As + Ac

In the above description, the unit calorific value of the fuel gas is measured at any time, and when the unit calorific value of the fuel gas changes during the temperature regulating control, the opening degree of the inlet guide vane 16, And controls the air intake amount of the air compressor 11 to be referred to. However, for example, when the gas turbine output indicated by the power generation amount of the generator 31 or the like is measured at any time and the gas turbine output changes due to the change in the unit calorific value of the fuel gas during the temperature regulation control, The degree of opening of the inlet guide vane 16, or the intake air amount of the air compressor 11 may be controlled.

"Second Embodiment &

Next, a gas turbine plant according to a second embodiment of the present invention will be described with reference to Figs. 4 and 5. Fig.

The gas turbine plant of the present embodiment is basically the same as the gas turbine plant of the first embodiment except for the configuration of the control device. Therefore, the control device 50a of the gas turbine plant of the present embodiment will be mainly described below.

The control device 50a of the present embodiment has a temperature regulation control section 51 and an intake quantity control section 52a in the same manner as the control device 50 of the first embodiment. However, the intake air amount control section 52a in the control device 50a of the present embodiment differs from the intake air amount control section 52 of the first embodiment.

The intake air amount control unit 52a of the present embodiment includes a command value calculation unit 53 for calculating a command opening degree (command value) based on the unit calorific value of the combustion gas measured by the calorimeter 55, a command to the intake air amount adjustor 15 And an output timing control section 54 for controlling the output timing of the opening degree (command value).

The command value computing unit 53 obtains the command opening degree (command value) by any of the methods exemplified in the first embodiment.

5, the output timing control unit 54 controls the intake air amount adjusting unit 53 such that the command value computing unit 53 receives the unit calorie from the calorimeter 55 (t2) and changes the intake air amount after the set time Ts 15) of the command value. The set time Ts is set such that the command value calculation unit 53 receives the unit calorie amount from the calorimeter 55 (t2) and then calculates the arrival time Tr until the fuel gas of the unit calorie amount reaches the combustor 19 . ≪ / RTI > In the present embodiment, when the unit heat quantity is large, the set time Ts is set to a time slightly shorter than the arrival time Tr, and when the unit heat quantity becomes small, the set time Ts is set to the arrival time Tr, Is set to a slightly longer time.

The low-pressure fuel gas line 43 or the high-pressure fuel gas line 44 of the present embodiment is provided with a flow meter 59 for detecting the flow rate of the fuel gas passing through the line. The output timing control unit 54 calculates the flow rate of the combustion gas by using the flow rate detected by the flow rate meter 59 and the line distance from the position where the calorimeter 55 samples the combustion gas to the fuel gas inlet of the combustor 19, And a reaching time Tr is obtained. The output timing control section 54 sets the set time Ts shorter than the arrival time Tr by a predetermined time based on the arrival time Tr. Instead of using the flow rate detected by the flow meter 59, the above-described arrival time Tr may be a flow rate estimated from the valve opening degree of the fuel flow rate regulating valve 47, for example.

Next, the change in the opening degree of the inlet guide vanes 16 of the air compressor 11 according to the change in the unit calorific value of the fuel gas will be described with reference to Fig.

It is assumed that the unit calorie Ca at the gas sampling position of the calorimeter 55 becomes large at time t1. The first predetermined time T1 is taken until the calorimeter 55 samples the fuel gas and then obtains the unit calorific value of the fuel gas and the command value calculation unit 53 of the control unit 50a receives the calorific value . The unit calorie amount Cb received by the command value calculation unit 53 of the control device 50a from the calorimeter 55 is changed from the time t1 to the time t2 after the first predetermined time T1.

The fuel gas at the gas sampling position of the calorimeter 55 is sampled in part by the calorimeter 55 and the remainder is sampled by the low pressure fuel gas line 43, the gas compressor 35, And reaches the combustor 19 via the exhaust pipe 19a. The time from the gas sampling position of the calorimeter 55 until the fuel gas reaches the combustor 19 is the second predetermined time T2 which is longer than the first predetermined time T1. Therefore, the unit calorific value Cc of the fuel gas flowing into the combustor 19 increases from the time t1 to the time t4 after the second predetermined time T2, in other words, from the time t2 to the time t4 after the arrival time Tr described above . Therefore, the relationship between the first predetermined time T1 and the arrival time Tr and the second predetermined time T2 has a relationship expressed by the following expression.

T1 + Tr = T2

Due to this, when the arrival time Tr is obtained, the first predetermined time T1 is measured in advance and the first predetermined time T1 is stored in the output timing control unit 54. [ The output timing control section 54 first calculates the flow rate of the fuel gas by using the flow rate detected by the flow meter 59 and the line distance from the position where the calorimeter 55 samples the combustion gas to the fuel gas inlet of the combustor 19, 2 < / RTI > The output timing control unit 54 then subtracts the first predetermined time T1 from the second predetermined time T2 to obtain the arrival time Tr.

As described above, the set time Ts handled by the output timing control unit 54 is a time slightly shorter than the arrival time Tr when the unit calorie amount Ca is large. The opening degree of the inlet guide vane 16 of the air compressor 11 becomes larger at the time t3 before the time t4 when the unit quantity Cc of the fuel gas flowing into the combustor 19 becomes larger. That is, in the present embodiment, the opening degree of the inlet guide vane 16 of the air compressor 11 is controlled in advance with respect to the change in the unit calorific value of the fuel gas flowing into the combustor 19.

When the opening degree of the inlet guide vane 16 of the air compressor 11 becomes larger at the time t3 before the time t4 when the unit quantity Cc of the fuel gas becomes larger as described above, the inlet temperature of the turbine 21 does not exceed the upper limit value The inlet temperature of the turbine 21 is returned to the upper limit value by the increase of the intake air quantity and the temperature regulation control before the temperature of the inlet of the turbine 21 increases.

As described above, the set time Ts handled by the output timing control unit 54 is a time slightly longer than the arrival time Tr when the unit calorie amount Ca becomes small. The opening degree of the inlet guide vane 16 of the air compressor 11 becomes smaller at a later time than the time at which the unit quantity Cc of the fuel gas flowing into the combustor 19 becomes smaller.

When the opening degree of the inlet guide vane 16 of the air compressor 11 becomes smaller at the time later than the time at which the unit calorie amount Ca of the fuel gas becomes smaller as described above, when the inlet temperature of the turbine 21 becomes lower than the upper limit value The inlet temperature of the turbine 21 is returned to the upper limit value by the decrease of the intake air amount and the temperature adjustment control.

Thus, in the present embodiment, even when the unit calorific value of the fuel gas changes during the temperature control, the change in the inlet temperature of the turbine 21 can be suppressed. Therefore, in this embodiment, the durability of the combustor 19 and the turbine 21 can be enhanced.

In this embodiment, when the unit heat quantity is large, the set time Ts is set to a time slightly shorter than the arrival time Tr, and when the unit heat quantity is small, the set time Ts is set to the arrival time Tr ) Is set to a slightly longer time. However, even when the set time Ts is equal to the arrival time Tr, it is possible to suppress the change of the inlet temperature of the turbine 21 with respect to the change of the unit calorific value of the fuel gas during the temperature control have.

However, in the case where the preceding control described above is not executed, as described in the column of the "first embodiment ", controlling the opening degree of the inlet guide vane 16 based on the variation amount of the gas turbine output obtained by the measurement It is possible. However, when executing the preceding control described above, the opening degree of the inlet guide vane 16 can not be controlled based on the amount of change in the gas turbine output obtained by the measurement. That is, the opening degree of the inlet guide vane 16 of the air compressor 11 can not be changed before or when the unit calorific value of the fuel gas flowing into the combustor 19 is changed or changed. Therefore, when executing the preceding control described above, it is necessary to measure the unit calorific value of the fuel gas.

In the above embodiment, the temperature of the turbine 21 is controlled by using the pressure in the compressed air flow path detected by the pressure gauge 56 and the temperature of the exhaust gas from the turbine 21 detected by the thermometer 57, Lt; RTI ID = 0.0 > temperature. ≪ / RTI > Alternatively, the inlet temperature of the turbine 21 may be estimated, or the temperature of the inlet of the turbine 21 may be detected using a thermometer.

The fuel of the gas turbine plant of each of the above embodiments is any one of a BFG single unit, a COG unit, and a mixture of BFG and COG. However, the fuel of the gas turbine plant may be BFG alone or COG only. Further, the fuel of the gas turbine 10 may be another fuel gas, for example, natural gas, biogas or the like.

In one aspect of the present invention, the output fluctuation of the gas turbine during the temperature control can be suppressed.

10: Gas Turbine
11: Air compressor
15: Intake regulator
16: Entry guide wing
19: Combustor
21: Turbine
31: generator
35: Gas compressor
43: Low pressure fuel gas line
44: High pressure fuel gas line
47: Fuel flow control valve
50, 50a: Control device
51: Temperature control unit
52, 52a:
53: Command value calculating section
54: Output timing control section
55: calorimeter
56: Pressure gauge
57: Thermometer
58: Output system
59: Flowmeter

Claims (19)

A combustor for combusting fuel in the air compressed by the compressor to generate a combustion gas; a turbine driven by the combustion gas; and a control unit for controlling the flow rate of the fuel supplied to the combustor, 1. A control device for a gas turbine plant, comprising:
A temperature regulation control unit for controlling a valve opening degree of the fuel flow rate control valve so that an inlet temperature of the turbine into which the combustion gas flows is kept constant;
And an intake air amount control unit for controlling the intake air amount adjusting unit so that the intake air amount of the compressor is changed in positive correlation with the change in the amount of the heat of the unit by receiving the unit heat amount of the fuel supplied to the combustor from the outside
Control device for gas turbine plant. A combustor for combusting fuel in the air compressed by the compressor to generate a combustion gas; a turbine driven by the combustion gas; and a control unit for controlling the flow rate of the fuel supplied to the combustor, 1. A control device for a gas turbine plant, comprising:
A temperature regulation control unit for controlling a valve opening degree of the fuel flow rate control valve so that an inlet temperature of the turbine into which the combustion gas flows is kept constant;
Wherein the temperature control unit controls the valve opening degree of the fuel flow rate control valve so that the inlet temperature of the turbine is kept constant by controlling the temperature of the gas turbine having the compressor, And an intake air amount control unit for controlling the intake air amount adjuster so that the intake air amount of the compressor is changed with negative correlation with respect to the output fluctuation
Control device for gas turbine plant. 3. The method of claim 2,
The intake air amount control unit controls the intake air amount adjusting unit so as to receive the unit heat amount that is the amount of heat per unit amount of the fuel supplied to the combustor from the outside and change the intake air amount with positive correlation with the change in the unit heat amount
Control device for gas turbine plant. The method according to claim 1 or 3,
Wherein the intake air amount control unit sets the intake air amount after the change so that the output of the gas turbine before the change in the unit calorific value is maintained
Control device for gas turbine plant. The method according to claim 1 or 3,
The intake air amount adjuster includes an inlet guide vane provided on the intake port side of the casing of the compressor for changing the intake air quantity in accordance with the opening degree change and a vane driver for changing the opening degree of the inlet guide vane,
Wherein the intake air amount control unit calculates an opening degree with respect to a variation amount of the unit heat quantity of the fuel received from the outside by using a predetermined relationship between the amount of change in the amount of heat of the fuel and the reference opening degree of the inlet guide vane, Determines the command opening degree by adding the standard opening degree to the opening degree change amount, outputs the command opening degree to the intake air amount adjuster as a command value,
Wherein the relationship is set such that the relationship between the amount of change in the degree of opening degree and the amount of change in the degree of opening degree
Control device for gas turbine plant. 6. The method of claim 5,
Wherein the relationship is a relationship in which an opening degree change amount capable of maintaining the output of the gas turbine before the change of the unit heat quantity is obtained
Control device for gas turbine plant. The method according to claim 1 or 3,
Wherein the intake air amount control unit includes: a command value calculation unit that receives the unit calorie from the outside and obtains a command value indicating a change amount of the intake air amount by the intake air amount controller; and the command value calculation unit calculates the intake air amount An output timing control unit for controlling an output timing of the command value to the intake air amount adjuster so that the intake air amount is changed,
The set time is determined based on the arrival time of the intake quantity control unit from the outside after receiving the unit calorie quantity until the fuel of the unit calorie quantity reaches the combustor
Control device for gas turbine plant. 8. The method of claim 7,
Wherein the output timing control unit receives the flow rate of the fuel from the outside and determines the arrival time using the flow rate
Control device for gas turbine plant. 8. The method of claim 7,
The set time is the same as the arrival time
Control device for gas turbine plant. 8. The method of claim 7,
Wherein the set time is shorter than the arrival time when the amount of the unit heat received from the outside is larger and is shorter than the arrival time when the amount of the unit heat received from the outside is smaller
Control device for gas turbine plant. A control device according to claim 1 or 3,
A gas turbine having the compressor, the combustor, and the turbine;
And the fuel flow control valve
Gas turbine plant. A method of operating a gas turbine including a compressor for compressing air, a combustor for combusting fuel in the air compressed by the compressor to generate a combustion gas, and a turbine driven by the combustion gas,
A temperature regulation control step of controlling a flow rate of the fuel supplied to the combustor so that an inlet temperature of the turbine into which the combustion gas flows is kept constant;
An intake air amount control step of receiving the unit heat amount which is a heat amount per unit amount of the fuel supplied to the combustor from the outside and having a positive correlation with the change of the unit heat amount to change the intake air amount of the compressor
A method of operating a gas turbine. A method of operating a gas turbine including a compressor for compressing air, a combustor for combusting fuel in the air compressed by the compressor to generate a combustion gas, and a turbine driven by the combustion gas,
A temperature regulation control step of controlling a flow rate of the fuel supplied to the combustor so that an inlet temperature of the turbine into which the combustion gas flows is kept constant;
An intake air amount control step of changing the intake air amount of the compressor with negative correlation with the output fluctuation of the gas turbine during the temperature control process is executed
A method of operating a gas turbine. 14. The method of claim 13,
In the intake air amount control step, the unit calorific value, which is the calorific value per unit amount of the fuel supplied to the combustor, is received from the outside, and the intake air amount is changed by making the positive correlation with the change in the calorific value
A method of operating a gas turbine. 15. The method according to claim 12 or 14,
In the intake air amount control step, the intake air amount after change is determined so that the output of the gas turbine before the change in the unit calorific value is maintained
A method of operating a gas turbine. 15. The method according to claim 12 or 14,
A command value calculation step of calculating the command value indicating the amount of change in the intake air amount by taking the unit calorie amount from the outside in the intake air amount control step; A timing control process is performed,
The set time is determined on the basis of the arrival time of the fuel of the unit calorie amount until the fuel reaches the combustor after receiving the unit calorie from the outside
A method of operating a gas turbine. 17. The method of claim 16,
In the timing control step, the flow rate of the fuel is received from the outside, and the arrival time is determined using the flow rate
A method of operating a gas turbine. 17. The method of claim 16,
The set time is the same as the arrival time
A method of operating a gas turbine. 17. The method of claim 16,
Wherein the set time is shorter than the arrival time when the amount of the unit heat received from the outside is larger and is shorter than the arrival time when the amount of the unit heat received from the outside is smaller
A method of operating a gas turbine.
KR1020167002453A 2013-09-06 2014-08-19 Gas turbine plant, control device thereof, and gas turbine operation method KR101752110B1 (en)

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