JP5452420B2 - Multi-shaft gas turbine engine controller - Google Patents

Description

  The present invention relates to a control device for a multi-shaft gas turbine engine having inlet guide vanes.

  A multi-shaft gas turbine engine composed of a gas generator and a power turbine is widely used for power generation, aircraft, marine use, machine drive and the like because the operation load can be made variable.

  By the way, since the multi-shaft gas turbine engine has a multi-shaft structure in which the rotating shafts of the gas generator and the power turbine are not connected, it is required to perform a load operation at a constant rotational speed of each shaft.

  In order to stabilize the rotational speed of each shaft, it is effective to adjust the intake air of the gas generator and the inlet gas flow rate of the power turbine. In addition, variable guide vanes (hereinafter referred to as “internal variable guide vanes”) are provided in the inlet of an air compressor that is a part of the gas generator and in the internal flow path between the gas generator and the power turbine, Cited Documents 1 and 2 disclose examples of load control methods for adjusting the flow rate and performing stable operation.

  However, the gas downstream of the gas generator is at a high temperature due to the combustion reaction inside the combustor. For this reason, installing the internal variable guide vanes in the downstream of the gas generator improves the operability of the gas turbine engine, but leads to an increase in manufacturing cost due to heat-resistant design and an increase in man-hours in terms of maintenance. In particular, in recent years, the combustion temperature in the combustor has been increased in order to improve thermal efficiency, and it has become difficult to install the internal variable guide vanes on the material.

  In Patent Document 3, a blade opening signal based on an atmospheric temperature change is generated on a variable guide blade at the inlet of an air compressor, and an exhaust gas temperature converted value of a turbine is generated based on compressed air from the air compressor. A blade opening correction circuit that calculates by adding the actual exhaust gas temperature of the turbine to the exhaust gas temperature conversion value, and selects either the high value signal from this calculation signal or the blade opening signal and gives a blade opening correction signal. It is described that it is provided.

JP 63-212725 A Japanese Patent Laid-Open No. 2-9919 JP-A-8-82228

  In Patent Documents 1 and 2, the amount of gas flowing into the power turbine is adjusted by controlling the internal variable guide vanes installed between the gas generator and the power turbine, and the shaft rotational speed during load operation is stabilized. Therefore, this method is effective only for the configuration having the internal variable guide vanes in the downstream of the gas generator. Therefore, when the internal variable guide vanes cannot be installed, the flow rate of the gas flowing into the power turbine cannot be adjusted. Therefore, it is difficult to perform the load operation while stabilizing the rotational speed of each shaft.

  The variable guide vanes installed at the air compressor inlet of Patent Document 3 are controlled for the purpose of avoiding surging of the air compressor, and the air flow rate is calculated from the rotational speed of the shaft having the air compressor. Therefore, it is used to calculate the target opening of the inlet guide vane. For this reason, in the multi-shaft gas turbine engine having the internal variable guide vanes only at the power turbine inlet, it is difficult to control the shaft rotational speed of the gas generator.

  An object of the present invention is to stabilize the rotational speeds of both shafts of a gas generator and a power turbine during a load operation of a multi-shaft gas turbine engine having no internal variable guide vanes.

  In order to solve the above problem, an air compressor having an inlet guide vane for adjusting a suction air flow rate, a combustor that combusts compressed air and fuel compressed by the air compressor, and the combustor generated by the combustor. In the control apparatus for a multi-shaft gas turbine engine configured by a gas generator configured by a high-pressure turbine driven by combustion gas and a power turbine driven by combustion gas discharged from the gas generator, the inlet A plurality of opening control modes for calculating a target opening of the guide blade, and a mode selection function for selecting one of the plurality of opening control modes, and at least one of the plurality of opening control modes. One has an inlet guide vane opening degree control function for controlling the opening degree of the inlet guide vanes so that the shaft revolution number of the gas generator is maintained at an arbitrary target revolution number. Characterized in that it.

  ADVANTAGE OF THE INVENTION According to this invention, the rotation speed of both shafts of a gas generator and a power turbine can be stabilized at the time of load driving | running of the multi-shaft gas turbine engine of a structure which does not have an internal variable guide blade.

1 is a schematic view of a two-shaft gas turbine engine of the present embodiment. It is a block schematic diagram of an inlet guide blade control device of the present embodiment. It is a fuel control valve control device block schematic diagram of the present embodiment. It is a fuel control valve control device block schematic diagram of the present embodiment. It is a shaft rotation speed hysteresis structure schematic of a present Example. It is a control characteristic figure of the gas turbine engine in a present Example.

  Hereinafter, modes for carrying out the present invention will be described.

  FIG. 1 is a schematic view of a two-shaft gas turbine engine which is a kind of multi-shaft gas turbine engine. The two-shaft gas turbine engine includes an air compressor 103 having an inlet guide vane 102 connected to an inlet guide vane drive device 101, compressed air compressed by the air compressor 103, and fuel whose flow rate is adjusted by a fuel adjustment valve 104. A gas generator 107 composed of a combustor 105 for mixing and combustion, a high-pressure turbine 106 driven by the combustion gas generated by the combustor 105, and a power turbine driven by the gas discharged from the gas generator 107 108. The power turbine 108 is connected to a load to supply output, and the gas from the gas generator 107 is exhausted after working in the power turbine 108. In the case of a power generation gas turbine engine, the load corresponds to the generator 109.

  In the load operation for supplying output from the power turbine 108 to the load, the operation at the rated load is defined as the rated load operation. Further, a gas generator rated rotational speed is a rotational speed having a sufficient margin from the natural frequency of the gas generator 107 during the rated load operation (hereinafter referred to as a resonance region) and the maximum rotational speed of the shaft permitted in strength. Partial load operation is below the rated load.

  When the output is increased or decreased in the partial load operation, the flow rate of fuel input to the combustor 105 is adjusted by the fuel adjustment valve 104, and the energy of the gas flowing from the gas generator 107 to the power turbine 108 is increased or decreased.

  Due to the change in the fuel flow rate, the shaft rotational speed of the gas generator 107 changes, the intake air flow rate of the air compressor 103 increases or decreases, and the power of the air compressor 103 and the output of the high-pressure turbine 106 are balanced.

  When the load applied to the power turbine 108 increases, the fuel flow rate input to the combustor 105 is increased by the control function for adjusting the fuel flow rate, the output of the high-pressure turbine 106 increases, and the shaft rotational speed of the gas generator 107 increases. The air flow rate sucked by the air compressor 103 increases. Thereby, the power of the air compressor 103 is also increased, and the torque acting on the shaft of the gas generator 107 is balanced. On the contrary, when the load applied to the power turbine 108 is reduced, the flow rate of fuel input to the combustor 105 is reduced, and the shaft rotational speed of the gas generator 107 is lowered. As a result, the torque acting on the shaft of the gas generator 107 is balanced.

  If the shaft rotational speed of the gas generator 107 is significantly increased, there is a possibility that a margin for the maximum rotational speed allowed for strength (hereinafter referred to as the gas generator maximum rotational speed) is reduced and exceeds the maximum gas generator rotational speed. In this case, the stable operation of the air compressor 103 or the high-pressure turbine 106 may be difficult due to the elongation of the constituent members due to the centrifugal force.

  In addition, the shaft rotation speed of the gas generator 107 may approach the above-described resonance range due to the fluctuation of the load applied to the generator 109. When the shaft rotation speed of the gas generator 107 approaches the resonance range, stable operation of the air compressor 103 and the high-pressure turbine 106 may be difficult due to shaft vibration.

  Therefore, as a transition control from the partial load operation to the rated load operation of the two-shaft gas turbine engine, the fuel flow rate supplied to the combustor 105 can be adjusted by the fuel adjustment valve 104 and the gas generator rated rotation speed can be maintained. When the load becomes a large load, the opening degree of the inlet guide vane 102 is controlled so that the shaft speed of the gas generator is settled at or near the gas generator rated speed. In other operation states, the opening degree of the inlet guide vane 102 is controlled with respect to other operation constraints.

  Although the air flow rate sucked by the air compressor 103 is increased or decreased by increasing or decreasing the shaft rotation speed of the gas generator 107 and the opening degree of the inlet guide vane 102, the function of adjusting the intake air flow rate is unified to the inlet guide vane 102. The shaft rotation speed of the gas generator 107 is stabilized.

  The present invention realizes the object of stabilizing the rotational speeds of both the shafts of the gas generator and the power turbine by the control device during the load operation of the multi-shaft gas turbine engine. Hereinafter, the present invention will be described using examples.

  An embodiment in which the present invention is applied to a power generating two-shaft gas turbine engine will be described with reference to FIG. The gas turbine control device 110 includes an inlet guide blade control device 111 and a fuel adjustment valve control device 112, and the present invention is applied to the inlet guide blade control device 111.

  In addition, the twin-shaft gas turbine engine for power generation according to this embodiment includes a temperature attached to the inlet of the air compressor 103, an inlet air measuring device 113 for measuring pressure, and a temperature attached to the outlet of the air compressor 103. An outlet air measuring device 114 for measuring pressure, a gas generator rotational speed measuring device 115, an exhaust temperature measuring device 116 for the power turbine 108, and a power turbine rotational speed measuring device 117 are provided.

  Further, an output measuring device 118 of the generator 109 and a combustion temperature measuring device 119 for directly or indirectly measuring the combustion temperature inside the combustor 105 having the highest temperature in the system constituting the gas turbine engine are provided. You may prepare.

  The inlet guide blade control device 111 calculates an inlet guide blade opening command value that becomes a control target opening of the inlet guide blade 102 based on the measurement signal obtained from each measurement device, and transmits the command value to the inlet guide blade drive device 101. To do. Similarly, the fuel adjustment valve control device 112 calculates a fuel adjustment valve opening command value that becomes the target opening of the fuel adjustment valve 104 based on the measurement signal, and transmits it to the fuel adjustment valve 104. Thereby, the opening degree of the inlet guide vane 102 and the fuel adjustment valve 104 is adjusted, and the load operation of the gas turbine engine is performed.

  FIG. 2 shows a configuration example of the inlet guide blade control device 111. The inlet guide blade control device 111 calculates inlet guide blade target opening candidates in a plurality of control modes, respectively, and selects an inlet guide blade target opening candidate suitable for the operating state of the gas turbine engine from among them by the mode selector 207. Then, it is transmitted to the inlet guide blade driving device 101 as the inlet guide blade opening command value.

  FIG. 2 shows an example in which the inlet guide vane control device 111 is configured to have a rotation speed control mode, a surge avoidance control mode, and other control modes.

  The inlet guide blade target opening candidate in the rotational speed control mode is calculated by the following procedure.

  The target revolution number of the shaft of the gas generator 107 is output from the gas generator revolution number setting unit 201. The gas generator rotational speed setter 201 is configured to output a value smaller than the gas generator rated rotational speed in advance. However, the amount to be reduced is about several percent with the gas generator rated speed being 100%.

  The output value of the gas generator rotation speed setting unit 201 is input to the temperature compensator 202, and is corrected and changed using the intake air temperature (hereinafter, measured inlet temperature) of the air compressor 103 measured by the inlet air measuring device 113 as an argument.

  Next, in the subtractor 203, the deviation between the corrected rotational speed output from the temperature compensator 202 and the shaft rotational speed of the gas generator 107 measured by the gas generator rotational speed measuring instrument 115 (hereinafter referred to as gas generator measured rotational speed). Calculate

  The deviation is input to the PI controller 205 via the dead zone setter 204, and by performing PI control with a small deviation suppressed, the opening degree of the inlet guide vane 102 is calculated, and the inlet guide vane target opening by the rotational speed control mode is calculated. The candidate is output.

  Here, in the figure, the dead zone setting unit 204 is represented by a broken line type dead zone, but the important point is that if the deviation output from the subtracter 203 is small, the return value for the opening command value of the inlet guide vane 102 The function of the dead zone setting unit 204 is not limited.

  In this embodiment, the inlet guide blade target opening candidate in the rotational speed control mode is calculated by the PI control, but the calculation method is not limited, and the target shaft rotational speed of the gas generator 107, the gas generator measured rotational speed, The inlet guide blade target opening candidate may be calculated so as to reduce the deviation.

  The inlet guide blade target opening candidate in the rotational speed control mode determined as described above is input to the mode selector 208.

  In the present embodiment, as another example of the control mode, the inlet guide blade target opening candidate in the surge avoidance control mode is calculated by the following procedure. The surge avoidance control mode is set for the purpose of avoiding surging of the air compressor 103 when the gas turbine engine has a low load and the shaft speed of the gas generator 107 is low.

  The modified rotational speed calculator 206 is a commonly used modified rotational speed calculation formula using the gas generator measured rotational speed measured by the gas generator rotational speed measuring instrument 115 and the measured inlet temperature measured by the inlet air measuring instrument 113 as arguments. Calculate the corrected rotation speed with.

  The function generator 207 includes a function having the corrected rotational speed calculated by the corrected rotational speed calculator 206 as an argument, calculates the opening degree of the inlet guide blade 102 according to the corrected rotational speed, and enters the inlet guide blade target opening degree. Output as a candidate. The output of the function generator 207 is input to the mode selector 208 as an inlet guide blade target opening candidate in the surge avoidance control mode.

  Although the surge avoidance control mode has been described as an example, the control mode combined with the rotation speed control mode is not limited to this. As other control modes, as shown in the function generators 209 and 210, the number and forms of control modes to be combined other than the rotational speed control mode are not limited to those listed here.

  The mode selector 208 has a function of selecting a signal suitable for stable operation from among a plurality of inlet guide blade opening candidates. The mode selector 208 also monitors the output signal of the operating state measuring device 211 whose output value changes according to the operating state of the gas turbine engine, and depending on the operating state, the inlet guide blade target opening forcibly selected is monitored. It is also possible to change the candidate. Thereby, the inlet guide blade control apparatus 111 of a present Example can switch a rotation speed control mode and another control mode as needed.

  FIG. 3 shows a configuration example of the fuel adjustment valve control device 112. The fuel adjustment valve control device 112 includes a load control device 301, an exhaust temperature control device 309, a gas generator rotation speed control device 312, a minimum value selector 316, and a fuel distribution calculator 317.

  In the load control device 301, the output command value given by the output command generator 302 is converted into the target rotational speed of the power turbine 108 by the rotational speed converter 303. The subtractor 304 calculates a deviation between the target rotational speed of the power turbine 108 and the shaft rotational speed measured by the power turbine rotational speed measuring instrument 117 (hereinafter, power turbine measured rotational speed).

  The deviation calculated by the subtractor 304 is multiplied by the load control gain 306 while the dead zone setter 305 suppresses correction due to minute fluctuations in the shaft rotational speed of the power turbine 108. After the gain multiplication, an adder 307 adds a value corresponding to the fuel flow rate command value in the no-load operation output from the bias signal generator 308, and the fuel flow rate command value (hereinafter referred to as the load flow rate command value) of the load control device 301. Value).

  In the exhaust gas temperature control device 309, the exhaust gas temperature measured by the exhaust gas temperature measuring instrument 116 (hereinafter, measured exhaust gas temperature) is input to the fuel flow rate command function unit 311. The divider 310 receives the air compressor inlet pressure (hereinafter, measured inlet pressure) measured by the inlet air measuring instrument 113 and the air compressor outlet air pressure (hereinafter, measured outlet pressure) measured by the outlet air measuring instrument 114. Then, the pressure ratio of the air compressor 103 is calculated. The pressure ratio is input to the fuel flow rate command function unit 311 as a correction signal, and a fuel flow rate command value (hereinafter referred to as an exhaust gas temperature flow rate command value) for suppressing an excessive temperature rise in the high temperature portion of the gas turbine engine is calculated.

  In the gas generator rotational speed control device 312, the subtractor 314 calculates a deviation between the gas generator rated rotational speed preset in the gas generator rated rotational speed setter 313 and the gas generator measured rotational speed. The deviation is input to the PI controller 315 and output as a gas generator rotation speed control fuel flow rate command value (hereinafter referred to as a rotation rate flow rate command value).

  The aforementioned load flow rate command value, exhaust temperature flow rate command value, and rotation speed flow rate command value are selected by the minimum value selector 316, and the fuel distribution calculator 317 adjusts the fuel with respect to the input fuel flow rate command value. An opening command value of the valve 104 is calculated. Here, a plurality of fuel adjustment valves 104 may be provided. In addition, as shown in the figure, other fuel flow command values are transmitted to the minimum value selector 316, the number and form of the control devices for calculating the fuel control command values are limited to those listed here. It is not a thing.

  Other examples of the configuration of the fuel adjustment valve control device 112 include the following.

  As shown in FIG. 4A, the deviation between the output command value and the generator output measured by the output measuring device 118 may be directly calculated by the subtractor 304.

  As shown in FIG. 4B, in the case of the gas turbine engine having the combustion temperature measuring device 119, the exhaust temperature control device 309 uses the combustion temperature measured by the firing temperature measuring device 310 as an argument of the fuel flow rate command function unit 311a. It is also possible to calculate the exhaust temperature flow rate command value with the function function.

  As described above, the opening command value of the fuel adjustment valve 104 is calculated by the fuel distribution calculator 317 and is transmitted to the fuel adjustment valve 104 to adjust the fuel flow rate and perform the load operation of the gas turbine engine. In load operation, the load flow rate command value is normally the minimum value of the fuel flow rate command value, and the shaft rotational speed of the power turbine 108 and the output of the generator 109 are adjusted. The exhaust temperature flow rate command value and the rotational speed flow rate command value suppress the increase in combustion gas temperature, the shaft rotational speed of the gas generator 107, and the load.

  As described above, in this embodiment, the target shaft rotation speed value of the gas generator rotation speed setting device 201 shown in FIG. 2 is set to a value that is smaller by several percent than the gas generator rated rotation speed of the gas generator rated rotation speed setting device 313. Set.

  In some cases, the setting value of the gas generator rated speed setting device 313 is set to a value larger than the original gas generator rated speed. The amount to be increased is about several percent with the gas generator rated speed being 100%.

  That is, the target rotation speed of the shaft of the gas generator set in the rotation speed control mode of the inlet guide vane control device 111 and the rated rotation speed of the gas generator used for calculating the rotation speed flow rate command value of the fuel regulating valve control device 112. Thus, the hysteresis width can be given to each other by setting the target gas generator rotation speeds to different numerical values in the opening control of the inlet guide vane 102 and the opening control of the fuel adjustment valve 104. .

  Here, the setting of the hysteresis width will be described.

  FIG. 5A shows the shaft rotational speed N of the gas generator 107 during partial load operation, the target rotational speed (i) of the shaft of the gas generator set in the rotational speed control mode of the inlet guide vane control device 111, and the fuel adjustment valve. The relationship of the gas generator rated rotation speed (ii) utilized in order to calculate the rotation speed flow rate command value of the control apparatus 112 is shown.

  During the load operation, the shaft rotational speed N varies in the vicinity of the target rotational speed (i) depending on the rotational speed control mode of the inlet guide blade control device 111. In the gas generator rotational speed control device 312 of the fuel regulating valve control device 112, the subtractor 314 calculates the deviation of the shaft rotational speed, but the relationship between the gas generator rated rotational speed (ii) and the target rotational speed (i) is maintained. It becomes a positive value with a larger hysteresis width.

  By feeding back the positive deviation, the rotational speed flow command value calculated by the gas generator rotational speed control device 312 becomes a large value to increase the shaft rotational speed N. Since the minimum value selector 316 selects the minimum value of the fuel flow rate command value, the load flow rate command value of the load control device 301 is selected instead of the rotational speed flow rate command value.

  FIG. 5B shows the relationship between the shaft rotational speed N of the gas generator 107, the target rotational speed (i), and the gas generator rated rotational speed (ii) when the rated load operation is reached.

  After the inlet guide vane 102 reaches the maximum opening in the operation plan, the intake air flow rate of the gas generator 107 increases due to the increase in the rotational speed of the shaft rotational speed N. The shaft rotational speed N increases to the gas generator rated rotational speed (ii).

  In the gas generator rotation speed control device 312 of the fuel regulating valve control device 112, the deviation of the shaft rotation speed is calculated by the subtractor 314. However, since the correction corresponding to the hysteresis width is not added, the minimum value selector 316 does not rotate the gas generator. The rotational speed flow rate command value calculated by the numerical control device 312 is selected, and the shaft rotational speed N is maintained at the gas generator rated rotational speed (ii) by the opening of the fuel adjustment valve 104 based on this.

  According to the above embodiment, the rotational speeds of both the shafts of the gas generator 107 and the power turbine 108 can be stabilized during the load operation of the two-shaft gas turbine engine, and at the same time, the inlet guide vanes 102 in the rotational speed control mode can be stabilized. By having an opening degree control function, even in a two-shaft gas turbine engine that does not have an internal variable guide vane, it is possible to perform a load operation in which the shaft speed of the gas generator 107 is over-rotated and maintained at a sufficient speed from the resonance range. effective.

  By operating the load with the shaft speed of the gas generator 107 kept constant in the speed control mode, the intake air flow rate of the gas generator 107 can be controlled only by adjusting the opening of the inlet guide vane 102, and the gas turbine against the load fluctuation There is an effect that the state convergence of the engine is accelerated and load followability is improved.

  In addition to the above, the following items can be cited as effects of the control device obtained in the present embodiment.

  By having a function of setting a dead zone to the deviation of the shaft rotational speed of the gas generator 107 that feeds back to the opening degree of the inlet guide blade 102 in the rotational speed control mode, when operating at a constant load, Slight fluctuation in opening is suppressed. Thereby, it is possible to suppress the fluctuation of the operation state of the gas generator 107 and to obtain the effect of improving the operation stability.

  Further, the function of setting the hysteresis width to the target gas generator rotational speed by the opening degree control of the inlet guide vane 102 and the opening degree control of the fuel adjustment valve 104 allows the fluctuation of the shaft rotational speed of the gas generator 107 to occur. Even if it occurs, the opening degree control function of the inlet guide vanes 102 acts preferentially, and the opening degree control of the fuel adjustment valve 104 can continue the control for the purpose of load following, and the effect that the load following ability is improved can be obtained. .

  Further, by having a function of correcting the gas generator target rotational speed set by the opening degree control of the inlet guide vane 102 with the air temperature sucked by the air compressor 103, it is possible to widen a margin for surging during high load operation. .

  In addition, even if the rated load of the gas turbine engine changes due to the air temperature sucked in by the air compressor 103, there is also an effect that the control set value can be changed so that the hysteresis width is effective.

  Hereinafter, control characteristics in the gas turbine engine to which the present invention is applied will be described.

  In FIG. 6, the solid line represents the control characteristics when the control device according to the present embodiment is applied, and the broken line represents the control characteristics when the control device according to the present embodiment is not applied (hereinafter, comparative example). The horizontal axis represents time, and the vertical axis represents the shaft rotation speed of the gas generator 107 in FIG. 6A, the opening degree of the inlet guide vane 102 in FIG. 6B, and the shaft rotation of the power turbine 108 in FIG. The number and the load by the generator 109 are shown.

  As shown in FIG. 6A, the shaft rotational speed of the gas generator 107 reaches the target rotational speed B so as to widen the resonance area indicated by the hatched portion due to the effect of the rotational speed control mode from A in the figure. To rise. The shaft rotational speed of the comparative example continues to increase at a constant rate, and the effect of immediately moving the shaft rotational speed away from the resonance region cannot be obtained.

  After the shaft rotational speed of the gas generator 107 reaches the target rotational speed B, the opening degree of the inlet guide vane 102 is controlled by the rotational speed control mode so that the rotational speed becomes constant from C in FIG. Therefore, it is possible to perform load operation at a shaft speed with a margin for the over-rotation range. The opening degree of the inlet guide vanes 102 is the maximum opening degree at D in the figure. When the maximum opening is reached, the intake air flow rate of the gas generator 107 increases as the shaft speed of the gas generator 107 increases, as indicated by E in FIG. In the comparative example, since the intake air flow rate of the gas generator 107 is adjusted by both the opening degree of the inlet guide vane 102 and the shaft rotation speed of the gas generator 107, the shaft rotation speed of the gas generator 107 increases as the load increases. It becomes the rotation range.

  Further, in this embodiment, as shown in FIG. 6C, the shaft rotational speed of the power turbine 108 is controlled to be constant by following the load by controlling the opening of the fuel adjustment valve 104. The adjustment of the shaft rotational speed and output of the power turbine 108 is performed by opening control of the fuel adjustment valve 104, so that the load changes in the same manner as the opening of the fuel valve opening 104.

  Further, according to the present embodiment, since the shaft rotation speed of the gas generator 107 is kept constant and the load fluctuation is followed, the shaft rotation speed of the gas generator 107 and the air flow rate are balanced, and the operation state is settled. The required response time is shortened, and the effect of improving load followability is obtained.

101 Inlet guide vane drive device 102 Inlet guide vane 103 Air compressor 104 Fuel adjustment valve 105 Combustor 106 High-pressure turbine 107 Gas generator 108 Power turbine 109 Generator 110, 111 Inlet guide vane control device 112 Fuel adjustment valve control device 113 Inlet air Measuring instrument 114 Outlet air measuring instrument 115 Gas generator rotational speed measuring instrument 116 Exhaust temperature measuring instrument 117 Power turbine rotational speed measuring instrument 118 Output measuring instrument 119 Combustion temperature measuring instrument 201 Gas generator rotational speed setting instrument 202 Temperature compensator 203, 304, 314 Subtractor 204, 305 Dead band setter 205, 315 PI controller 206 Modified rotation speed calculator 207, 209, 210 Function generator 208 Mode selector 211 Operation state measuring instrument 301 Load controller 302 Output command generator 303 Rotation speed Change 306 Load control gain 307 Adder 308 Bias signal generator 309 Exhaust temperature control device 310 Divider 311 Fuel flow rate command function unit 311a Fuel flow rate command function unit 312 Gas generator rotation speed control device 313 Gas generator rated rotation speed setting device 316 Minimum Value selector 317 Fuel distribution calculator

Claims (2)

An air compressor having inlet guide vanes for adjusting the intake air flow rate, a combustor that combusts compressed air and fuel compressed by the air compressor, and a high pressure driven by combustion gas generated by the combustor A gas generator constituted by a turbine;
A power turbine driven by combustion gas emitted from the gas generator;
In a control device for a multi-shaft gas turbine engine constituted by:
A plurality of opening control modes for calculating a target opening of the inlet guide vane;
A mode selection function for selecting one of the plurality of opening control modes;
At least one of the plurality of opening control modes has an inlet guide blade opening control function for controlling the opening of the inlet guide blade so as to maintain the shaft rotation speed of the gas generator at an arbitrary target rotation speed. The inlet guide vane opening degree control function includes a dead zone setting device for setting a dead zone to the deviation between the measured shaft rotational speed of the gas generator and the arbitrary target rotational speed,
A fuel flow rate command value calculation function for calculating a flow rate command value of fuel to be supplied to the combustor based on a measured value of the shaft rotation rate of the gas generator and an arbitrary target rotation rate of the gas generator set in advance; ,
And a function of setting a hysteresis width between a target rotational speed of the gas generator set in the opening degree control mode and a target rotational speed set by the fuel flow rate command value calculation function. A control device for a shaft type gas turbine engine. In claim 1,
A control apparatus for a multi-shaft gas turbine engine, having a function of correcting the arbitrary target rotational speed based on a measured value of an inlet temperature of the air compressor.

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