• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    What is provided is a method for starting a gas turbine and a system for controlling the startup process of a gas turbine. The method includes the steps of: defining a target ramp-up time to achieve an operating speed for the gas turbine (310); Determining a remaining time to reach the target startup time (320); Monitoring at least one parameter associated with the boot-up process (330); Determining a first operating point for the parameter (340); Adjusting the first operating point for the parameter based at least in part on the startup time to a second operating point (350); Setting an effective parameter based on the second operating point for the parameter (360).
    公开号:CH702608B1
    申请号:CH00123/11
    申请日:2011-01-25
    公开日:2016-08-15
    发明作者:August Snider David；Scott Rosson Randy
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Field of the invention
    The present invention relates generally to gas turbines, and more specifically to a method for starting and a system for controlling the start-up of gas turbines.
    Background to the invention
    Existing systems and methods for controlling the startup process of a gas turbine are based on defined schedules that relate to different start-up parameters, such as minimum / maximum fuel flow, acceleration rate, starting torque, and other suitable parameters. The predefined schedules define start-up characteristics for the gas turbine. Startup parameters are set to follow nominal paths set forth in the flowcharts. However, in practice, due to changes in, for example, the ambient temperature or performance of a component, the gas turbine startup process may differ from the nominal paths set forth in the flowcharts. These deviations can not be corrected during startup and can lead to significant deviations of the startup time for the gas turbine. This in turn can degrade component life, blade tip tolerances, and gas turbine performance.
    [0003] One approach to dealing with driveline deviations is based on allowing large tolerances during the startup time. However, such an approach may not always be desirable because of problems of predictability and efficiency. In addition, commercially increasingly guaranteed startup times for gas turbines are required.
    Another approach that can be used in a gas turbine ramp-up process to handle deviations is the use of a target chase plan. In this approach, the gas turbine speed or other suitable start-up parameter is monitored against the time axis. The control routine determines whether erroneous variations in gas turbine speed or other suitable parameters occur, and sets various action parameters, e.g. the fuel flow and the starting torque to correct any error.
    After the gas turbine speed naturally has a sluggish response characteristic, the scheme, after an error has occurred, in the attempt to correct the error, however, quickly override at predetermined limits. It is usually undesirable to maintain operation at control limits, for example at a maximum ignition or exhaust gas temperature. In addition, if the error is close to zero, the lack of sensitivity may cause control loops to rapidly ramp from one boundary to another, causing wear and other hardware problems.
    Thus, there is a need in the art for an improved method of starting a gas turbine and a system for controlling a gas turbine start-up to allow guaranteed start-up times with reduced tolerances and to overcome the above-mentioned disadvantages.
    Brief description of the invention
    Aspects and advantages of the invention will be discussed in part in the following description, or may be obvious from the description, or may be learned by practice of the invention.
    The invention relates to a method according to claim 1 for starting a gas turbine and a system according to claim 10 for controlling a startup process of a gas turbine. An embodiment of the present invention relates to a method for starting a gas turbine. The method includes the steps of: defining a target ramp-up time to achieve an operating speed for the gas turbine; and determining a remaining time to reach the target startup time. The method includes the steps of: monitoring at least one parameter associated with the boot-up process. The method determines a first operating point for the parameter and adjusts the first operating point for the parameter to a second operating point based, at least in part, on the remaining time remaining for the startup process. Based on the second operating point for the parameter, the method sets an action parameter.
    Another embodiment of the present invention relates to a system for controlling the start-up of a gas turbine. The system includes a monitoring system configured to monitor a parameter for the gas turbine ramp-up process and to provide a feedback signal indicative of the parameter. The system further includes a control system configured to determine a remaining time for the start-up operation of the gas turbine to achieve a target start-up time. The control system is configured to determine a first operating point for the parameter, and to adjust the first operating point for the parameter based on the time remaining for the startup operation to a second operating point. The control system is configured to generate an error signal based at least in part on the feedback signal and the second operating point for the parameter, and is configured to control an action parameter based on the error signal.
    Changes and modifications may be made to the embodiments of the present invention.
    These and other features, aspects and advantages of the present invention will become more apparent from the description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.
    Brief description of the drawings
    A complete and practicable description of the present invention, which includes the best mode of the invention, directed to the person skilled in the art, is made in the description which refers to the attached figures:<Tb> FIG. 1 <SEP> graphically illustrates exemplary acceleration curves that may be utilized in accordance with embodiments of the present invention;<Tb> FIG. FIG. 2 <SEP> graphically illustrates exemplary acceleration curves, as a function of residual time, that serve to achieve a predefined operating speed according to embodiments of the present invention; FIG.<Tb> FIG. 3 <SEP> graphically illustrates an exemplary start-up procedure for a gas turbine according to an embodiment of the present invention;<Tb> FIG. FIG. 4 shows an exemplary control topology for a control system according to an embodiment of the present invention; FIG.<Tb> FIG. FIG. 5 shows an exemplary control topology for a control system according to an embodiment of the present invention; FIG.<Tb> FIG. 6 <SEP> illustrates an exemplary curve fitting plan according to an embodiment of the present invention; and<Tb> FIG. 7 shows a flowchart of a method according to an exemplary embodiment of the present invention.
    Detailed description of the invention
    [0013] Reference will now be made in detail to embodiments of the invention, some examples of which are illustrated in the drawings. All examples serve to illustrate the invention and are not intended to limit this. It will be readily apparent to those skilled in the art that various modifications and changes may be made to the present invention without departing from the spirit or scope of the invention. For example, features that are illustrated or described as part of one embodiment may be used in conjunction with another embodiment to yield yet a further embodiment. The present invention is therefore intended to cover such modifications and variations as fall within the scope of the appended claims and their equivalents.
    [0014] The present description relates generally to a method for starting a gas turbine and a system for improved startup control. While the present description is made with respect to gas turbine engines, it should be understood by those skilled in the art from the disclosures set forth herein that the present invention is not limited to the control of gas turbine start-up operations but is equally applicable to other technologies. Embodiments of the present invention use curve planning to significantly reduce driveline time deviations without causing regulatory response and stability issues. Parameters associated with startup control are used in conjunction with the current state of the startup data to perform real time adjustments to control plans to achieve a predefined setpoint startup time.
    Adjustments to the control plans can be made by means of interpolation tables or other functions that do not require the use of additional control loops. Embodiments of the present invention may be practiced with relatively minor enhancements to an existing design for controlling start-up operations of a gas turbine or other equipment. Since the adjustments to start-up parameters are performed taking into account the cumulative effect occurring at the end of a startup process, readjustments are reduced.
    The inventive methods and systems of the Ablaufkurvensteuerung perform on the basis of a residual time adjustments to control plans to achieve a target startup time. The target ramp-up time is a timing target set for the gas turbine or other device to achieve a predefined operating speed for a gas turbine, e.g. a speed of 100% or a full speed. The target startup time may be predefined in accordance with customer-specific quality requirements or other requirements. The remaining time remaining to reach the desired startup time can be determined or calculated by detecting the elapsed startup time.
    [0017] In embodiments of the present invention, multiple boot-up operations with deviations in the schedules are mimicked to develop a family of startup characteristics. These characteristics may be plotted against the time remaining to define a plurality of curves available to complete the start-up operation from each point during the start-up operation at the target start-up time (i.e., reach a predefined operating speed). Based on the current speed and remaining time to complete the startup process, appropriate adjustments to existing schedules may be made to produce the required turns.
    For example, FIG. 1 illustrates a plurality of acceleration curves 10, 12 and 14 for a gas turbine startup process plotted as a function of the rotational speed over time. The nominal acceleration curve 10 represents a nominal acceleration map, while the acceleration curves 12 and 14 each represent deviations of + 10% from the nominal acceleration map. While only three curves are illustrated in FIG. 1, it should be understood by those skilled in the art from the disclosures set forth herein that any number of acceleration curves can be provided without departing from the scope of the present invention. The plurality of acceleration curves 10, 12, and 14 shown in FIG. 1 are used to determine adjustments to existing schedules based on the remaining time to achieve a predefined operating speed at the target startup time.
    Fig. 2 carries the acceleration curves 10, 12, 14 of Fig. 1 as curves derived from a predefined operating speed, e.g. 100% speed, graphically as a function of the remaining time. The dashed line 15 in FIGS. 2 and 3 illustrates an exemplary boot-up operation. Before the point «A», the acceleration of the gas turbine follows the nominal acceleration plan. This can be attributed, for example, to a slow initialization of the starting torque and / or to a gradual acceleration of the gas turbine with reduced fuel.
    At the point "A" remaining to achieve the target startup time remaining time and the current gas turbine speed are determined. Based on the remaining time and the current speed, adjustments to the acceleration schedule are provided so that the gas turbine achieves a predefined operating speed as the desired startup time expires. For example, as shown in FIGS. 2 and 3, the appropriate curve to achieve the predefined operating speed of about 100% speed at the target startup time is based on the + 10% acceleration curve 12. The control system and method controls different action parameters based on the adjusted acceleration schedule, e.g. the fuel flow, the turbine ignition and / or an applied to the gas turbine starting torque, so that the gas turbine can reach the predefined operating speed at the target startup time.
    Adjustments to the schedules may be made continuously, and multiple schedules may be adjusted simultaneously. For example, the starting torque and the fuel flow may be adjusted to optimally control gas turbine acceleration without stability problems. Since adjustments are determined by means of interpolation tables or as functions of the remaining time, no additional control loops are required.
    Referring now to Figure 4, an exemplary control system 100 according to one embodiment of the present invention will now be discussed in detail. The control system 100 monitors a variety of parameters associated with a start-up operation of a gas turbine. As illustrated, for example, a gas turbine speed N is monitored by a monitoring system, and a speed signal 102 is provided to the control system 100 as an input. In addition, a gas turbine acceleration Ndot is monitored, and an acceleration input signal 104 is also provided to the control system 100 as an input signal. Although the control system 100 monitors the speed N and the acceleration Ndot as operating parameters associated with the gas turbine startup process, it should be apparent to those skilled in the art from the description herein that the present invention is equally applicable to other startup parameters, e.g. Fuel flow, exhaust gas temperature, turbine ignition and other suitable operating parameters.
    The speed signal 102 and the acceleration input signal 104 are used by the control system 100 to determine control output signals that serve to control a variety of action parameters. For example, the control system 100 provides a fuel dispensing control signal 182 to control the fuel flow supplied to the gas turbine during startup. Further, the control system 100 generates a torque output control signal 176 to control the magnitude of a starting torque provided to the gas turbine. Although the control system 100 is discussed with reference to control of effective parameters pertaining to fuel flow and starting torque, it should be understood by those skilled in the art from the descriptions herein that the present invention is equally applicable to other suitable performance parameters to accommodate turbocharging characteristics of gas turbines.
    The speed signal 102 is provided to a plurality of schedules, including an acceleration schedule 130, a minimum fuel plan 150, and a startup torque schedule 170. The acceleration schedule 130, the minimum fuel plan 150 and the starting torque map 170 are utilized by the control system 100 to determine a first operating point for a start-up parameter. For example, the acceleration map 130 is used to determine a first operating point for the gas turbine acceleration based on the current speed N of the gas turbine. The control system 100 generates a first acceleration control signal 132 based on the operating point set forth in the acceleration schedule 130.
    Similarly, the minimum fuel plan 150 is used to determine an operating point for a minimum fuel flow to the gas turbine based on the current speed N of the gas turbine. The control system 100 generates a minimum fuel signal 152 based on the operating point set forth in the minimum fuel plan 150. The starting torque map 170 is used to determine a first operating point for the starting torque based on the current speed of the gas turbine. The control system 100 generates a first starting torque signal 172 based on the operating point set forth in the starting torque plan 170.
    The acceleration schedule 130, the minimum fuel plan 150, and the launch torque plan 170 are based on nominal paths for a gas turbine start-up operation. The gas turbine start-up operation may vary from the nominal paths set forth in the acceleration schedule 130, the minimum fuel plan 150, and the startup torque schedule 170 due to a variety of operating conditions. According to embodiments of the present invention, the control system 100 is adapted to make adjustments to the operating points included in the schedules, e.g. in the acceleration map 130 and in the startup torque map 170 are set to handle deviations of the gas turbine startup process so that the gas turbine can achieve a predefined operating speed at a predefined target startup time.
    The control system 100 makes adjustments to the operating points provided by the acceleration schedule 130 and the starting torque map 170 by first determining a remaining time left to the gas turbine to achieve a target startup time. The target start-up time is predefined by a user or by another user of the control system to meet customer-specific quality requirements or other appropriate requirements. The desired startup time is provided to the control system 100 as a T_soll signal 106.
    Specifically, the T_Soll signal 106 indicative of the target startup time is output to the controller 110. The controller 110 also receives a time signal 105 indicative of the elapsed time. The controller 110 is configured to provide a remainder time signal 112 indicative of a remaining time based on the T_soll signal 106 and the time signal 105. The controller 110 may be a summer or other controller configured to generate the remaining time signal 112 based on the T_soll signal 106 and the time signal 105.
    The control system 100 is adapted to set the operating points included in the schedules, e.g. in the acceleration schedule 130 and the starting torque map 170, are adapted based on the remaining time signal 112. The operating points set out in the timetables shall be adjusted on the basis of graphs. As discussed above, the curve maps are developed by modeling multiple ramp-up operations with deviations in the schedules to develop a family of start-up characteristics. The development of the flowcharts may involve a change of a ranking or predetermined limits. For example, to provide increased stability at low speeds, the cam diagrams may prefer to change the starting torque over changes in other start-up parameters, e.g. acceleration, fuel flow, turbine ignition, exhaust gas temperature or other suitable start-up parameters. These characteristics may be provided as a function of the remaining time to define a plurality of curves that are available to complete the startup operation from each point during the startup operation at the target startup time.
    In one embodiment, the curve map may include an interpolation table that provides fitting values to set the operating points set forth in the ramp-up schedules based on the remaining time and at the current turbine speed. In further embodiments, the adjustment values may be determined as a function of the remaining time and the current turbine speed. The adjustment values are defined based on the number of curves to achieve a predefined operating speed at the target startup time. Since the adjustments can be determined using interpolation tables or as functions of the remaining time, no additional control loops are required.
    Referring to FIG. 4, the remaining time signal 112 and the speed signal 102 are output to the acceleration cam 120. Based on the residual time signal 112 and the speed signal 102, an acceleration adjustment signal 122 is determined based on the acceleration curve map 120. The acceleration adjustment signal 122 is output to the control device 140.
    The controller 140 receives a first error signal 136 from a controller 135. The controller 135 is configured to determine the first error signal 136 based on the acceleration control signal 132 and on the acceleration input signal 104. The controller 135 may be a summer or other suitable device that serves to determine an erroneous deviation between the acceleration control signal 132 and the acceleration input signal 104.
    The controller 140 sums the acceleration adjustment signal 122 with the first error signal 136 to generate an acceleration control signal 142 indicative of a second operating point for accelerating the gas turbine. In this way, the control system * 100 adjusts the first operating point set forth in the acceleration schedule 130 to a second operating point based on the remaining time to achieve a predefined operating speed at the target startup time. As shown in FIG. 4, the adaptation to the acceleration operating point set forth in the acceleration curve plan 120 can be realized by means of a relatively small extension of the typical construction of a start-up control of a gas turbine.
    The control system 100 is adapted to provide an action parameter, e.g. to control the fuel flow or starting torque based on the second operating point for the startup parameter. For example, the acceleration control signal 142 is output to the controller 145, which generates a fuel inflow control signal 146 based on the acceleration control signal 142. The controller 145 may be a proportional controller, proportional-integral controller, proportional-derivative controller, proportional-integral-derivative controller, or any other suitable controller.
    The fuel inflow control signal 146 is compared to a minimum fuel inflow signal 152 at a controller 180. The controller 180 determines which of the signals fuel inflow control signal 146 and minimum fuel inflow signal 152 is greater. The controller 180 outputs the larger of the fuel injection control signal 146 and the minimum fuel injection signal 152 as the fuel output control signal 182. In this way, the control system 100 controls / controls an action parameter, i. the fuel flow based on the second operating point for the acceleration.
    Similarly, the remaining time signal 112 and the speed signal 102 are provided to the starting torque cam 160. A starting torque adjustment signal 162 is determined from the starting torque curve 160 based on the remaining time signal 112 and the speed signal 102. The starting torque adjusting signal 162 is output to a controller 175. The controller 175 adds the value of the starting torque adjusting signal 162 to the first starting torque control signal 172 and generates a starting torque output control signal 176. The control system 100, based on the starting torque output control signal 176, influences the starting torque applied to the gas turbine. In this way, the control system 100 controls an action parameter, i. the starting torque, based on the second operating point for the starting torque.
    Referring now to Fig. 5, another embodiment of the present invention will be discussed in detail. Fig. 5 illustrates a control system 200 which receives a speed signal 202 and an acceleration signal 204 as inputs. The control system 200 is configured to generate a fuel inflow dispensing control signal 246 to provide an impact parameter, i. to control the fuel flow, so that at a target start-up time, a predefined operating speed for the gas turbine is achieved.
    The control system 200 receives a T_soll signal 206 indicative of the predefined target startup time for the gas turbine and a time signal 205 indicative of the elapsed time for the startup operation. The T_soll signal 206 and the time signal 205 are output to a controller 210 which determines a remaining time signal 212 based on the T_soll signal 206 and the time signal 205. The controller 210 may be a summer or other suitable device that serves to determine the remaining time signal 212 based on the T_soll signal 206 and the time signal 205.
    Both the remaining time signal 212 and the speed signal 202 are both output to an acceleration curve map 220. In the following, the control logic for the acceleration curve map 220 will now be discussed in detail. The speed input signal 202 is output to a coasting time schedule 222, which removes a target time remaining relative to the speed for the gas turbine based on a target curve for the gas turbine acceleration. A desired remaining time signal 224 is determined based on the startup timeout schedule 222. The target remaining time signal 224 and the remaining time signal 212 are output to a control device 225. The controller 225 divides the remaining time signal 212 by the target remaining time signal 224 to generate a remaining ratio signal 226.
    The remaining time ratio signal 226 is output to a curve fitting plan 228. An exemplary curve fitting plan 228 is illustrated in FIG. The curve fit plan 228 represents acceleration adjustment values ΔNdot as a function of the speed. The appropriate acceleration adjustment value may be determined by following the run curve associated with the appropriate residual time ratio signal 226 output to the curve fitting plan 228.
    For example, an exemplary curve fitting plan 228 of FIG. 6 includes three run curves 20, 22, and 24. The run curve 20 may be associated with a remaining time ratio of about one. The flow curve 22 may be associated with a residual time ratio of about zero. The flow curve 24 may be associated with a remaining time ratio of about 2. Adjustment values ΔNdot assigned to residual time ratios which are not exactly equal to 0, 1 or 2 can be determined by interpolation or by other suitable methods.
    Based on the curve 20, if the remaining time ratio is about 1 (that is, if the remaining time signal and the target remaining time signal substantially coincide), no adjustments are required, resulting in an acceleration adjustment value ΔNdot of about zero. Based on the curve 22, if the remaining time ratio is about 0 or between 0 and 1 (ie, if the remainder of the time signal lags the desired remainder time signal), a suitable fitting value ΔNdot determined from the curve 22 is generated to suitably adjust the acceleration to effect the gas turbine. As shown in FIG. 6, the magnitude of the adjustment value ΔNdot depends on the actual speed of the gas turbine. Similarly, if the remaining time ratio is about 2 or between 1 and 2 (ie, if the remaining time signal is ahead of the target remaining time signal), based on the curve 24, a suitable adjustment value ΔNdot determined from the curve 24 is generated to effect appropriate adaptation of the acceleration of the gas turbine. The magnitude of the adjustment value ΔNdot depends on the current speed of the gas turbine.
    With continued reference to FIG. 5, the fitting value signal 250, which identifies the appropriate fitting value determined from the curve fitting schedule 228, is output to a controller 235. The control system * 200 uses the trim value signal 250 to make adjustments to operating points set forth in a ramp-up acceleration plan 230. Specifically, the speed input signal 202 is output to the acceleration acceleration map 230. A first operating point is determined from the startup acceleration schedule 230 and is provided as a first acceleration control signal 232. The first acceleration control signal 232 is output to the controller 235, which sums the adjustment value signal 250 with the first acceleration control signal 232 to generate a second acceleration control signal 236. The control device 235 may be a summer or another suitable control device which serves to generate the second acceleration control signal 236 on the basis of the first acceleration control signal 232 and the adaptation value signal 250.
    The control system 200 is configured to control an action parameter based on the second acceleration control signal 236, e.g. the fuel flow or the starting torque. For example, the second acceleration control signal 236 is output to a controller 240 along with the acceleration input signal 204. The controller 240 determines an error signal 242 based on the second acceleration control signal 236 and the acceleration input signal 204. The controller 240 may be a summer or other suitable device that serves to determine an erroneous deviation between the second acceleration control signal 236 and the acceleration input signal 204. The error signal 242 is output to a controller 245 that generates a fuel inflow output control signal 246 based on the error signal 242. The controller 245 may be a proportional controller, a proportional-integral controller, a proportional-derivative controller, a proportional-integral-derivative controller, or any other suitable controller. The fuel inflow output control signal 246 is used to control the fuel flow so that at a target ramp-up time, a predefined operating speed for the gas turbine is achieved.
    Referring now to Figure 7, a flowchart for a method 300 according to an embodiment of the present invention will now be discussed in detail. In step 310, the method defines a target ramp-up time. The target startup time is the desired time in which the gas turbine is to reach the predefined operating speed. The target ramp-up time may be defined based on customer-specific quality requirements or other requirements.
    In step 320, the method 300 determines a remaining time to reach the target startup time. The remaining time is used by the method 300 to make adjustments to work points for a variety of start-up parameters. The remaining time can be determined by monitoring the elapsed time and startup time of start-up. For example, the remaining time may be calculated by subtracting the elapsed time from the target startup time.
    In step 330, the method 300 monitors a parameter associated with the boot-up process. For example, the method may monitor gas turbine speed, acceleration, starting torque, fuel flow, exhaust gas temperature, turbine ignition, or other suitable parameters associated with the startup operation. In step 340, the method 300 determines a first operating point for the parameter. The first operating point can be determined by means of predefined startup schedules based on a nominal path for the startup parameter.
    At step 350, the method 300 adjusts the first operating point for the parameter to a second operating point based, at least in part, on the startup time remaining time. For example, the method 300 may provide the first operating point for the parameter with a trim value to match the first operating point to the second operating point. In step 360, based on the second operating point, the method controls an action parameter, e.g. the fuel flow, the starting torque, the turbine ignition or any other suitable action parameter. Thus, the method 300 uses a current state of the boot process data to perform real-time adjustments to control plans so that a predefined target start time is achieved.
    The present description uses examples to describe the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, for example, make and use any devices and systems, and to carry out any associated methods ,
    LIST OF REFERENCE NUMBERS
    [0050]<Tb> 10 <September> acceleration curve<Tb> 12 <September> acceleration curve<Tb> 14 <September> acceleration curve<tb> 15 <SEP> Typical startup process<Tb> 20 <September> expiration curve<Tb> 22 <September> expiration curve<Tb> 24 <September> expiration curve<Tb> 100 <September> Control System<Tb> 102 <September> speed signal<Tb> 104 <September> acceleration input signal<Tb> 105 <September> Time Signal<Tb> 106 <September> temperature T_setpoint signal input<Tb> 108 <September> T_Start signal<Tb> 110 <September> controller<Tb> 112 <September> Time Signal<Tb> 120 <September> acceleration curve plan<Tb> 122 <September> acceleration adjustment signal<Tb> 130 <September> acceleration plan<tb> 132 <SEP> First acceleration control signal<Tb> 135 <September> controller<tb> 136 <SEP> First error signal<Tb> 140 <September> controller<Tb> 142 <September> acceleration control signal<Tb> 145 <September> Controller<Tb> 146 <September> fuel flow control signal<Tb> 150 <September> minimum fuel plan<Tb> 152 <September> minimum fuel flow signal<Tb> 160 <September> Anfahrdrehmomentkurvenplan<Tb> 162 <September> Anfahrdrehmomentanpassungssignal<Tb> 170 <September> Anfahrdrehmomentplan<tb> 172 <SEP> First starting torque control signal<Tb> 175 <September> controller<Tb> 176 <September> Anfahrdrehmomentausgabesteuersignal<Tb> 180 <September> controller<Tb> 182 <September> fuel output control signal<Tb> 200 <September> control system *<Tb> 202 <September> speed input signal<Tb> 204 <September> acceleration input signal<Tb> 205 <September> Time Signal<Tb> 206 <September> temperature T_setpoint signal<Tb> 210 <September> controller<Tb> 212 <September> Time Signal<Tb> 214 <September> T_Rest- (min.) - Signal<Tb> 215 <September> controller<Tb> 216 <September> time output signal<Tb> 220 <September> acceleration curve plan<Tb> 222 <September> startup rest schedule<Tb> 224 <September> target residual time signal<Tb> 225 <September> controller<Tb> 226 <September> Time ratio signal<Tb> 228 <September> curve adjustment plan<Tb> 230 <September> boot acceleration plan<tb> 232 <SEP> First acceleration control signal<Tb> 235 <September> controller<tb> 236 <SEP> Second acceleration control signal<Tb> 240 <September> controller<Tb> 242 <September> error signal<Tb> 245 <September> Controller<Tb> 246 <September> fuel flow output control signal<Tb> 250 <September> Anpasswertplan<Tb> 255 <September> controller<Tb> 260 <September> controller<Tb> 300 <September> Process<Tb> 310 <September> step<Tb> 320 <September> step<Tb> 330 <September> step<Tb> 340 <September> step<Tb> 350 <September> step<Tb> 360 <September> step<Tb> N <September> Gas turbine speed<Tb> NDOT <September> gas turbine acceleration
    权利要求:
    Claims (10)
    [1]
    A method of starting a gas turbine, comprising:Selecting a nominal acceleration curve from a ramp-up acceleration map that defines the nominal acceleration curve and a plurality of acceleration curves that deviate from the nominal acceleration curve to achieve a desired operating turbine speed at a predefined setpoint ramp-up time, the acceleration curves being from the ramp-up acceleration curve map of FIG zero to a target speed range;Exerting a starting torque on the gas turbine;Determining a current speed of the gas turbine, wherein the current speed is determined at a time before the target start-up time,Determining the remaining time remaining to reach the target startup time based on the time at which the current speed was determined;Comparing the current speed and remaining time with the nominal acceleration curve; andwherein the method, if the current speed and remaining time differ from the nominal acceleration curve, comprises adjusting at least one gas turbine effective parameter such that the gas turbine follows one of the acceleration curves that deviate from the nominal acceleration curve by the predefined setpoint acceleration time to achieve the desired operating speed.
    [2]
    2. The method of claim 1, further comprising continuously determining the current speed of the gas turbine and remaining time to reach the desired startup time, and comparing the current speed and remaining time with the nominal acceleration curve and the plurality of acceleration curves from the nominal one Deviation curve deviate.
    [3]
    3. The method of claim 2, wherein if the current speed and the remaining time differ from a currently selected acceleration curve, the method further comprises adjusting at least one effective parameter of the gas turbine such that the gas turbine follows another acceleration curve to arrive at the predefined setpoint -To reach the desired operating speed.
    [4]
    4. The method of claim 1, wherein the action parameter is a fuel flow and / or a starting torque.
    [5]
    5. The method of claim 1, further comprising monitoring at least one parameter associated with the start-up operation and determining a first operating point for the parameter, wherein the parameter is a fuel flow, an exhaust gas temperature or a turbine ignition.
    [6]
    6. The method of claim 5, wherein the first operating point for the parameter is determined in part based on a nominal acceleration curve defined in the acceleration acceleration graph.
    [7]
    7. The method of claim 5, further comprising adjusting the first operating point for the parameter to a second operating point based at least in part on the remaining time remaining.
    [8]
    8. The method of claim 7, wherein adjusting the first operating point for the parameter to the second operating point is based, at least in part, on a fitting value, the fitting value being determined at least in part from a parameter curve plan provided by an interpolation table.
    [9]
    9. The method of claim 7, wherein the action parameter is adjusted based on the second operating point for the parameter.
    [10]
    10. A system for controlling a start-up of a gas turbine, starting from applying a starting torque to the gas turbine to full speed, the system comprising:a monitoring system configured to monitor gas turbine speed and acceleration and to generate gas turbine speed and acceleration feedback signals indicative of gas turbine speed and acceleration; anda control system configured to receive the gas turbine speed and acceleration feedback signals and, based thereon, provide a current speed at a discrete time, the control system further configured to maintain a remaining time remaining for the gas turbine to reach the full speed based on the current one Determine the speed and a target start-up time;wherein the control system is configured to use a ramp-up acceleration map to reach full speed, wherein the ramp-up acceleration map defines a nominal acceleration curve and a plurality of other acceleration curves that deviate from the nominal acceleration curve to full speed from zero at the predefined one To reach set-up time;wherein the control system is configured to compare the current speed and remaining time with the nominal acceleration curve and, if the current speed and the remaining time deviate from the nominal speed curve, generate a signal to adjust at least one gas turbine operating parameter; such that the gas turbine follows one of the acceleration curves that deviate from the nominal acceleration curve to reach full speed at the predefined setpoint ramp-up time.
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    同族专利:
    公开号 | 公开日
    CH702608A2|2011-07-29|
    DE102011000148A1|2011-07-28|
    CN102135037A|2011-07-27|
    US20110179802A1|2011-07-28|
    JP5860594B2|2016-02-16|
    US8833085B2|2014-09-16|
    CN102135037B|2014-10-29|
    JP2011153621A|2011-08-11|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-08-31| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/694,334|US8833085B2|2010-01-27|2010-01-27|System and method for gas turbine startup control|
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