JP2002147251A - Control device of gas turbine facility - Google Patents

Abstract

PROBLEM TO BE SOLVED: To prevent excessive torque from acting on a device to be driven without structurally changing a gas turbine body and the device to be driven. SOLUTION: A torque limiting circuit 94 limits the output torque of an output turbine 45, and prevents the torque from acting on a water discharge pump 42 and a reduction gear 56. Since the torque limiting circuit 94 limits the output torque of the output turbine 45 based on the number of revolutions N3 of the output turbine 45, the output of the output turbine 45 can be selected without being dependent on a load from the pump 42 and the reduction gear 56. Since axial torque resistance is relieved in designing and manufacturing the pump 42 and the reduction gear 56, an input shaft connected to the output shaft 55 of the output turbine 45 can be designed and manufactured without receiving any structural restriction to allow the maximum torque of the output turbine 45.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine facility directly connected to a driven device such as a drain pump, which can control the output of the gas turbine so that excessive torque does not act on the driven device. Related to a control device.

[0002]

2. Description of the Related Art Conventionally, the control of a gas turbine is usually performed by controlling the number of revolutions, controlling the temperature, or controlling the load. The protective functions include various functions such as acceleration / deceleration limit, maximum load limit and compressor turbine outlet gas temperature limit. Is equipped. Furthermore, in a gas turbine for driving a generator, when an abnormality is detected on the generator side, the breaker is disconnected by the protection function of the generator itself, and the generator and the output turbine are mechanically directly connected. It is possible to disconnect the generator itself from the load and to prevent the drive torque from acting on the generator, thereby preventing damage to the generator and the gas turbine body.
However, in gas turbine equipment that directly drives mechanical equipment such as a drain pump, when the load side suddenly changes and the load torque increases suddenly, the power generated by the gas turbine body connected to the driven device is reduced. There is no means for protecting the driven device and the gas turbine body. In order to cope with such a sudden change in load, in the conventional drain pump, instead of directly driving the drain pump with the output turbine, the generator is driven by the output turbine and the power generated by the generator is used. It has been practiced to install a driven motor and drive the drain pump with the motor, but this has a problem that the equipment cost is excessive.

FIG. 6 is a system diagram showing a schematic configuration of a gas turbine power generation facility 1 having a typical prior art gas turbine control device 25. This prior art is disclosed in Japanese Patent Application Laid-Open No. 2-3088928. Is disclosed. The gas turbine power generation equipment 1 has a compressor 2, a compressor turbine 3 and a combustor 4, and the compressor 2 is coaxially connected to the compressor turbine 3 by a compressor turbine shaft 6 to form a gas generator 5. I do. The air compressed by the compressor 2 is mixed and burned in a combustor 4 with a fuel supplied through a flow control valve 8, and the combustion gas is supplied to the compressor turbine 3. The output of 3 drives the compressor 2.

[0004] The combustion gas from the gas generator 5 is supplied to an output turbine 10 via a variable stationary blade 9. The output turbine 10 has an output shaft 11. After the rotation of the output shaft 11 is reduced by a speed reducer 12, the rotation is input to a generator 13 as a load to drive the generator 13. The variable stator blade 9 is driven by blade driving means 14 to change the blade angle, and the output of the output turbine 10 is controlled. The combustion gas discharged from the output turbine 10 is exchanged with the air supplied from the compressor 2 to the combustor 4 by the heat exchanger 15 to recover heat, and then exhausted.

[0005] Such a gas turbine power generation facility 1 includes:
A load detector 16 for detecting the load on the generator 13; a rotational speed detector 17 for detecting the rotational speed of the compressor turbine shaft 6; a rotational speed detector 18 for detecting the rotational speed of the output shaft 11;
Inlet temperature detector 19 for detecting the inlet temperature of the compressor, and inlet temperature detector 20 for detecting the inlet temperature of the compressor turbine 3
Is provided.

FIG. 7 is a block diagram showing a configuration of a gas turbine control device 25 provided in the gas turbine power generation equipment 1. The gas turbine control device 25 includes a target rotation speed setting unit 26, a fuel flow rate control unit 27, a feedforward amount setting unit 28, a variable stationary blade control unit 29, a load determination unit 30, a rotation speed determination unit 31, and a rotation speed increase. It has a degree limiting means 32.

The target speed setting means 26 includes a load detector 16, an inlet temperature detector 22, and an inlet pressure detector 2.
3 to set and output a target target rotation speed of the compressor turbine shaft based on each of the detected values from (3). The fuel flow rate control means 27 controls the flow rate regulating valve 8 so that the rotation speed detection value of the compressor turbine shaft 6 detected by the rotation speed detector 17 becomes the target rotation speed, and a deviation of each rotation speed. Adjust the fuel flow rate according to. The feedforward amount setting means 28 includes a load detector 16, an inlet temperature detector 2
2. The variable stator vane 9 based on each detection value from the inlet pressure detector 23 and the rotation speed detector 17 of the compressor turbine shaft 6
Set the feedforward amount at the angle of and output. The variable vane control means 29 is configured to determine the rotation speed of the output shaft 11 detected by the rotation speed detector 18 based on the deviation of each rotation speed and the feedforward amount such that the rotation speed detection value becomes a predetermined target rotation speed. The wing driving means 14 is controlled.

Further, the load determining means 30 determines whether or not a load greater than a predetermined value has been applied based on the detected load value of the generator 13 detected by the load detector 16. When the rotation speed determination means 31 determines that the result of the determination by the load determination means 30 is equal to or greater than a predetermined value, a predetermined rotation speed range is determined based on the rotation speed detection value of the rotation speed detector 18 of the output shaft 11. It is determined whether or not it has recovered. The rotational speed increase limiter 32 limits the increase in the rotational speed of the compressor turbine shaft 6 when the rotational speed determiner 31 determines that the rotational speed does not recover within the predetermined range of the rotational speed.

Such a conventional gas turbine power plant 1
With this configuration, the degree of increase in the number of revolutions of the compressor turbine shaft 6 immediately after the load is applied is suppressed to a relatively low level, thereby preventing a rapid increase in the number of revolutions of the output shaft 11 due to feedforward control when the load is applied.

[0010]

In such a conventional technique, the load determining means 30 determines whether or not a load greater than a predetermined value has been applied based on the detected load value of the generator 13 to determine the rotational speed. The means 31 determines whether or not the rotation has recovered to a predetermined rotation speed range based on the rotation speed detection value of the rotation speed detector 18 of the output shaft 11 when the determination result by the load determination means 30 is equal to or more than the predetermined value. The rotation speed increase limiter 32 is further provided with the rotation speed determiner 3.
When it is determined that the engine speed does not recover within the range of the predetermined number of rotations, the degree of increase in the number of rotations of the compressor turbine shaft 6 is limited.

When the driven device is a generator as in the prior art, if an abnormality is detected on the driven device side, it is possible to avoid the abnormal state by opening the circuit breaker of the generator. When a generator is driven by this output turbine, an electric motor for driving a driven device such as a drain pump is separately required, and the overall equipment cost becomes excessive. On the other hand, if the output turbine is directly connected to the driven equipment and the driven equipment is driven directly by the output turbine, the load torque will increase sharply due to a change in the state of the driven device, and if The abnormality cannot be avoided on the device side.

Generally, in the case of a gas turbine body having an output turbine, the power of the output turbine changes substantially according to the fuel flow rate. Therefore, when the rotation speed of the output turbine decreases due to an increase in load torque, the rotation speed of the output turbine decreases. When the output torque increases almost in inverse proportion and the rotation speed of the output turbine is significantly reduced, the output torque is several times as large as the output torque at the rated rotation speed, which is the basis of the design.
Therefore, as the load torque increases, the rotation speed of the output turbine decreases, and as a result, the output torque sharply increases, so that the transmission torque from the output turbine to the driven device increases. The drive shaft connecting the output turbine and the driven device and the driven device may exceed the allowable strength limit.

Therefore, in order to provide a facility that will not be damaged even when the output torque increases due to a decrease in the rotation speed of the output turbine, the output torque must be several times as large as the output torque at the rated rotation speed normally used for the basis of design. A problem arises in that the output turbine, the drive shaft, and the driven device must all have sufficient strength margin to withstand the torque.

Further, according to this conventional technique, the output of the gas turbine cannot be controlled in accordance with the number of revolutions of the output turbine. Therefore, foreign matter or the like is caught in the pump, and the load torque on the output turbine increases sharply. Although the output turbine speed decreases, excessive torque acts on the output turbine, drive shaft and pump, and as a result,
There is a problem that the power turbine, the drive shaft and the pump may be damaged.

An object of the present invention is to provide a gas turbine system capable of preventing an excessive torque from acting on a driven device without structurally changing the gas turbine body and the driven device. It is to provide a control device.

[0016]

According to the present invention, air compressed by a compressor and fuel guided through a fuel flow control valve are supplied to a combustor and burned. A gas generator that supplies combustion gas from a combustor to a compressor turbine coaxially connected to the compressor to drive the compressor, and drives a driven device by energy of gas output from the gas generator. Control of gas turbine equipment comprising a gas turbine body comprising an output turbine, wherein the output turbine adjusts the opening of the fuel flow control valve in accordance with the power for driving the driven device to control the fuel flow supplied to the combustor. A control device for gas turbine equipment, comprising: a torque limiter that limits an output torque of the output turbine based on a rotation speed of the output turbine. That.

According to the present invention, the torque limiting means limits the output torque of the output turbine based on the rotation speed of the output turbine, that is, the rotation speed. The output turbine, the drive shaft, and the driven device can be protected by preventing excessive torque from acting on the turbine, the drive shaft, and the driven device. In addition, the torque limiting means limits the output torque of the output turbine based on the rotation speed of the output turbine, and does not depend on the load torque from the driven device. Therefore, it is not necessary to provide a special load detector. Further, in the design and manufacture of the output turbine, the drive shaft, and the driven device, it is not necessary to consider that an excessive torque exceeding the rating, which is the basis of normal design, acts. In the design and manufacture of the, without being limited as in the prior art,
Productivity is improved.

Thus, it is possible to prevent an excessive torque from acting on the driven device without structurally changing the gas turbine body and the driven device.

According to a second aspect of the present invention, the torque limiting means controls the fuel flow control valve based on a predetermined torque limit value corresponding to the number of revolutions of the output turbine.

According to the present invention, the fuel flow control valve is controlled by the torque limiting means so as not to exceed a predetermined torque limit value corresponding to the number of revolutions of the output turbine. Also, it is possible to secure a required number of revolutions after the load torque returns to a predetermined value without applying excessive torque to the output turbine, the drive shaft and the driven device.

[0021]

FIG. 1 shows a gas turbine facility 4 having a gas turbine control device 40 according to an embodiment of the present invention.
1 is a system diagram illustrating a schematic configuration of FIG. The gas turbine equipment 41 of the present embodiment includes a drain pump 42 as a load,
It comprises the drain pump 42 and the gas turbine body 43 that drives the speed reducer 56. The gas turbine body 43 is
A multi-shaft gas turbine having a gas generator 44 and an output turbine 45, wherein the gas turbine control device 40
Calculates the output torque of the output turbine 45, and when the rotation speed (that is, the rotation speed) of the output turbine 45 decreases, the amount of fuel supplied to the combustor 46 so that the output torque does not exceed the torque limit set value. The configuration is such that the output of the gas generator 44 can be adjusted and the output of the output turbine 45 can be reduced by controlling the fuel flow rate adjusting valve V <b> 1 for adjusting the input amount. The fuel flow control valve V1 is realized by, for example, a throttle valve.

FIG. 2 is a graph showing the relationship between the output turbine speed and the output torque when the output of the output turbine 45 is kept constant. As is clear from the figure, when the torque limit control is not performed, the output torque increases as the rotational speed decreases, as shown by the line L1.

That is, because the output Q of the output turbine is given by using the fuel flow rate F as a parameter due to the characteristics of the gas turbine body, the output torque Tr is the ratio of the output Q to the output turbine speed N3 Tr = K · (Q ( F) / N3) (1) Here, Q (F) is a relational expression given by the characteristics of the gas turbine, and K is a constant for unit conversion. Therefore, the fuel flow rate Fmax at which the output torque Tr becomes the torque limit set value Trmax is a value when Tr = Trmax in the above equation (1). Specifically, by solving Trmax = K · (Q (Fmax) / N3) (2) for an arbitrary output turbine speed N3, the torque limit set value when the output turbine speed is N3 is obtained. The value of the fuel flow rate Fmax according to the considerable output torque can be obtained.

In accordance with the rotational speed of the output turbine, the fuel flow rate corresponding to the torque limit set value is sequentially obtained, and the fuel flow rate supplied to the combustor through the fuel flow rate adjusting valve V1 is changed to the fuel flow rate corresponding to the torque limit set value. By restricting the flow below the flow rate, the output of the power turbine 45 is restricted,
As a result, the torque input to the drain pump 42 can be limited.

In the embodiment of FIG. 1, the gas generator 44 includes a low-pressure compressor 47, a high-pressure compressor 48, a high-pressure turbine 49, a low-pressure turbine 50, the combustor 46, a low-pressure shaft 51, and a high-pressure shaft 52. The low-pressure compressor 47 is coaxially connected to the low-pressure turbine 50 by a low-pressure shaft 51,
The high-pressure compressor 48 is driven by a high-pressure shaft
Is connected coaxially. The low-pressure shaft 51 is coaxially inserted through the high-pressure shaft 52 and can rotate individually with each other. Further, the output turbine 45 has an output shaft 55, which is connected to an input shaft (not shown) of a speed reducer 56,
The output shaft (not shown) of the speed reducer 56 is
The rotation of the output shaft 55 is input to the pump 42 at a reduced speed.

The fuel supplied to the gas turbine main body is guided to the combustor 46 via a fuel flow control valve V1 controlled by the gas turbine controller 40.

The air compressed by the low-pressure compressor 47 is supplied to a high-pressure compressor 48, and after being further compressed, the high-pressure air is supplied to a combustor 46. The fuel whose flow rate has been adjusted through the flow rate adjusting valve V1 is supplied to the combustor 46, the fuel and the high-pressure compressed air are mixed and burned, and the combustion gas is supplied to the high-pressure turbine 49. The high-pressure turbine 49 is driven.

The combustion gas that has driven the high-pressure turbine 49 is guided to the low-pressure turbine 50 to drive the low-pressure turbine 50, and then is supplied to the output turbine 45, where the output turbine 4
5 is driven. After the rotation of the output shaft 55 of the output turbine 45 is reduced by the speed reducer 56, the rotation is input to the drainage pump 42 to drive the drainage pump 42.

FIG. 3 is a block diagram showing a specific configuration of the gas turbine control device 40. The gas turbine control device 40 includes an output turbine speed control circuit 81, an output limit circuit 82, a startup fuel control circuit 83, a low pressure compressor maximum speed limit circuit 86, and a high pressure compressor maximum speed limit circuit 8
7, includes an output turbine inlet gas temperature limiting circuit 88, a torque limiting circuit 94, and a minimum value selecting circuit 96.

The output turbine speed control circuit 81 includes:
An output turbine speed setting value provided from an externally installed speed setting device (not shown) and an output turbine speed signal output from the output turbine speed detecting means 69 are input, and the rotation of the output turbine 45 is performed. A command signal X1 is output to the fuel flow control valve so that the number matches the output turbine speed setting value command. This function is selected in a normal operation state as a basic control group of the fuel control.

The output limiting circuit 82 is provided with a fuel flow control valve V1 for adjusting the fuel flow so that the rotational speed of the low-pressure compressor 47 does not exceed the limit corresponding to the maximum output set value under any conditions. To output a command signal X2. This output limiting function utilizes the fact that the rotation speed of the low-pressure compressor 47 has a fixed relationship with the output of the gas generator 44, and the rotation speed of the low-pressure compressor 47 matches the value corresponding to the output set value. And outputs a command to adjust the fuel flow rate. The output set value increases from idling to the maximum output when the gas turbine is started, and increases the output of the gas generator 44. During this control, the control is switched to the control by the output turbine speed control circuit 81,
In the normal operation state, as a function to perform the maximum limit,
It is on standby, and when the gas turbine is stopped, the set value is reduced from the maximum output to idling.

The start-up fuel control 83 performs control from the start-up of the gas turbine to the arrival of idling, and outputs a command signal X4 to the fuel flow control valve V1. This command signal X4 is a signal for controlling the gas turbine from the start of the gas turbine until the gas turbine reaches idling, and is configured not to be selected after the gas turbine reaches idling.

The low-pressure compressor maximum rotation speed limiting circuit 86
Is controlled so that the rotation speed of the low-pressure compressor 47 does not exceed a predetermined limit value under any conditions.
Adjust the opening of. This restriction is based on a predetermined low-pressure compressor rotation speed limit set value N1max preset in the low-pressure compressor maximum rotation speed limiting circuit 86, and the low-pressure compressor rotation speed detection means 70.
Is compared with the low-pressure compressor speed signal N1 output from the
The low-pressure compressor rotation speed N1 is equal to the low-pressure compressor rotation speed limit set value N.
An opening command X5 of the fuel flow control valve V1 is output so as not to exceed 1max (N1max> N1).

The high-pressure compressor maximum rotation speed limiting circuit 87
The fuel flow control valve V1 is controlled so that the rotational speed of the high-pressure compressor 48 does not exceed a predetermined limit value under any conditions.
Adjust the opening of. This restriction is based on a predetermined high-pressure compressor rotation speed limit set value N2max preset in the high-pressure compressor maximum rotation speed restriction circuit 87 and the high-pressure compressor rotation speed detection means 72.
Is compared with the high-pressure compressor rotation speed detection signal N2 output from the controller, and the opening of the fuel flow control valve V1 such that the high-pressure compressor rotation speed N2 does not exceed the high-pressure compressor rotation speed limit set value N2max (N2max> N2). The degree command X6 is output.

The output turbine inlet gas temperature limiting circuit 8
8 adjusts the opening command of the fuel flow control valve V1 such that the inlet gas temperature of the output turbine 45 does not exceed a predetermined limit value under any conditions. This restriction is based on a predetermined output turbine inlet temperature limit set value Т6max preset in the output turbine inlet gas temperature limiting circuit 88 and the output turbine inlet gas temperature detection signal T6 output from the output gas turbine inlet gas temperature detecting means 73. And outputs an opening command X7 of the fuel flow control valve V1 such that the output turbine inlet gas temperature T6 does not exceed the output turbine inlet gas temperature limit set value T6max (# 6max># 6).

The minimum value selection circuit 96 includes the output limiting circuit 82, the torque limiting circuit 94, the starting fuel control circuit 8,
3. Opening command signals X1, X2, X3 of the fuel flow control valve V1 output from each of the low pressure compressor maximum rotation speed limiting circuit 86, the high pressure compressor maximum rotation speed limiting circuit 87, and the output turbine inlet gas temperature limiting circuit 88. , X4, X5, X6, X
7, the signal corresponding to the smallest valve opening degree, that is, the smallest fuel flow rate is selected and output to the fuel flow rate control valve V1 as the output signal X of the gas turbine control device 40.

The fuel flow control valve V1 receives a valve opening command signal X output from the gas turbine control device 40, and controls the opening of the fuel flow control valve to a value corresponding to the signal, thereby opening the fuel flow control valve. The fuel flow according to the degree is supplied to the combustor 46.

Next, the torque limiting circuit 94 will be described. The output torque of the output turbine can be obtained from the ratio Q / N3 between the output turbine output Q and the output turbine speed N3. Here, the output turbine speed N3 is output from the output turbine speed detecting means 69. Since the output turbine output has a unique relationship with the low-pressure compressor rotation speed N1, it can be determined from the low-pressure compressor rotation speed N1.
Therefore, the output torque of the output turbine can be obtained from the low-pressure compressor rotation speed N1 and the output turbine rotation speed N3. As a result, the relationship between the output turbine speed N3 and the low-pressure compressor speed limit N1L when the output torque of the output turbine reaches a value corresponding to the torque limit set value can be obtained. That is, when the actual low-pressure compressor rotation speed N1 is small by the low-pressure compressor rotation speed limit value N1L corresponding to the output turbine rotation speed determined by this relationship, the output torque of the output turbine is smaller than the torque limit set value. Conversely, the low pressure compressor speed N
When 1 is larger than the low-pressure compressor rotation speed limit value N1L obtained from the output turbine rotation speed N3 at that time, the output torque of the output turbine exceeds the torque limit set value. The relationship between the output turbine rotation speed and the low-pressure compressor rotation speed limit value is, for example, a straight line as shown in FIG. 5 when the output torque of the output turbine is a constant value Trmax.

FIG. 4 shows the structure of the torque limiting circuit 94. The low-pressure compressor calculates the low-pressure compressor speed limit value N1L corresponding to the torque limit set value from the output turbine speed N3 by the above-described method. The control operation is performed by inputting a rotation speed limit value calculation circuit 94a, the low pressure compressor rotation speed limit value N1L output from the low pressure compressor rotation speed limit value calculation circuit, and the actual low pressure compressor rotation speed N1. And a torque control circuit 94b for outputting a command signal X3 to the fuel flow control valve such that the compressor speed N1 does not exceed the low-pressure compressor speed limit value.

According to the present embodiment, the torque limiting circuit 9
4 limits the output torque of the output turbine 45 on the basis of the rotation speed N3 of the output turbine 45, so that the control of the gas turbine body 43 by the gas turbine controller 40 causes the output turbine 45 and the drainage pump which is the driven device. It is possible to prevent excessive torque from acting on the reduction gear 42 and the reduction gear 56, and to protect the output turbine 45, the drain pump 42, and the reduction gear 56. Moreover, the torque limiting circuit 94 limits the output torque of the output turbine 45 based on the rotation speed N3 of the output turbine 45.
No special detector for detecting the load from the drain pump 42 and the reducer 56 is required. Output turbine 4
5. In the design and manufacture of the drainage pump 42 and the speed reducer 56, since the shaft torque resistance is reduced, the design and manufacture of the input shaft connected to the output shaft 55 of the output turbine 45 should be the same as in the above-described prior art. The productivity of the drain pump 42 and the speed reducer 56 can be improved.

As described above, according to the present embodiment, it is possible to prevent an excessive torque from acting on the driven device without structurally changing the gas turbine body and the driven device.

Since the output of a gas turbine is greatly affected by the atmospheric temperature and pressure at which the gas turbine is used, it is common practice to use a corrected value converted to a reference state when calculating its characteristics. It is a target. Therefore, in the gas turbine controller 40 as well, the values related to the state of the gas turbine, such as the number of revolutions and the output, are corrected by the atmospheric temperature and the atmospheric pressure and converted into the reference state. No control device can be realized.

[0043]

According to the first aspect of the present invention, since the torque limiting means limits the output torque of the output turbine based on the rotation speed of the output turbine, the control of the gas turbine body by the gas turbine control device. Accordingly, it is possible to protect the driven device by preventing excessive torque from acting on the driven device without structurally changing the gas turbine body and the driven device. Moreover, the torque limiting means limits the output torque of the output turbine based on the rotation speed of the output turbine, so that a special detector for detecting the load from the driven device is not required. Also, in the design and manufacture of the driven device side, since the shaft torque resistance is reduced, the design and manufacture of the input shaft connected to the output shaft of the output turbine are not restricted as in the above-described conventional technology. Performance can be improved.

According to the present invention, the fuel flow control valve is controlled by the torque limiting means so as not to exceed a predetermined torque limit value corresponding to the number of revolutions of the output turbine. The required number of revolutions and torque can be secured without applying excessive torque to the device.

[Brief description of the drawings]

FIG. 1 is a system diagram illustrating a schematic configuration of a gas turbine facility 41 including a gas turbine control device 40 according to an embodiment of the present invention.

FIG. 2 is a graph showing the relationship between the output turbine speed and its output torque when the output of an output turbine 45 is kept constant.

FIG. 3 is a block diagram showing a specific configuration of the gas turbine control device 40.

FIG. 4 is a block diagram showing a specific configuration of a torque limiting circuit 94.

FIG. 5 is a graph showing a relationship between an output turbine speed and a low-pressure compressor speed limit value.

FIG. 6 shows a typical prior art gas turbine controller 2
FIG. 1 is a system diagram showing a schematic configuration of a gas turbine power generation facility 1 including a fuel cell 5.

FIG. 7 is a block diagram showing a configuration of a gas turbine control device 25 provided in the gas turbine power generation facility 1.

[Explanation of symbols]

 40 Gas Turbine Controller 41 Gas Turbine Equipment 42 Drain Pump 43 Gas Turbine Body 44 Gas Generator 45 Output Turbine 46 Combustor 47 Low Pressure Compressor 48 High Pressure Compressor 49 High Pressure Turbine 50 Low Pressure Turbine 51 Low Pressure Shaft 52 High Pressure Shaft 55 Output Shaft 56 Reduction Device 69 output turbine speed detecting means 70 low pressure compressor speed detecting means 72 high pressure compressor speed detecting means 73 output turbine inlet gas temperature detecting means 81 output turbine speed control circuit 82 output limiting circuit 83 starting fuel control circuit 86 low pressure Maximum compressor speed limit circuit 87 High pressure compressor maximum speed limit circuit 88 Output turbine inlet gas temperature limit circuit 94 Torque limit circuit 96 Minimum value selection circuit

Claims (2)

[Claims] An air compressed by a compressor and a fuel guided through a fuel flow control valve are supplied to a combustor for combustion, and combustion gas from the combustor is coaxially transmitted to the compressor. A gas generator that supplies a compressor turbine connected to the gas turbine to drive the compressor, and an output turbine that drives a driven device by energy of gas output from the gas generator.
A control device for gas turbine equipment for controlling the flow rate of fuel supplied to a combustor by adjusting the opening of the fuel flow control valve in accordance with the motive power of the output turbine driving a driven device, comprising: A control device for gas turbine equipment, comprising torque limiting means for limiting based on the number of revolutions of a turbine. 2. The fuel flow control valve according to claim 1, wherein the torque limiter controls the fuel flow control valve based on a predetermined torque limit value corresponding to a rotation speed of the output turbine.
A control device for a gas turbine facility as described in the above.