Method and system for a burn fashion transition in a gas turbine.

[0001] description concerns the control of a gas turbine and is concerned more precisely Method The present said and systems for controlling a transition between burn modes , while a gas turbine is under direct price increase of edge of burn.

[0002] In at least some known a kind is the control gas turbine systems is used as a direct price increase of edge of burn denotes the, , to provide for fuel and air streams to the various nozzles of the one or more combustion chambers within a gas turbine. For the purposes of the present text "direct price increase of edge of burn " the regulation of the combustion within a gas turbine means, for example by way of controlling the air and/or flows of fuel to nozzles in such combustion chambers within the gas turbine that one or more predetermined combustion parameter, including, for example, temperatures, pressures, and/or concentrations of by-products of the combustion dynamics, or limit values are maintained within predetermined limits. In gas turbine systems the gas turbine comprises a plurality of combustion chambers at least some known, and each combustion chamber comprises a plurality of nozzles. In at least some of these can be controlled the fuel and air streams are about individual gas turbine systemsair feed circles fuel and, independently, to the individual nozzles passed. One way, as the amounts of air and/or fuel, are fed to the a single nozzle can be defined within a combustion chamber, is that the total amount of air and/or fuel, which is to be fed to the gas turbine or combustion chamber, the amounts of fuel and/or air and then determined defined, the individual nozzles (sometimes referred to as "Split") are supplied. The "Split" for a particular nozzle the proportion of the total required fuel flow to the gas turbine or combustion chamber defined, over the respective nozzle must be supplied. Therefore, during a direct price increase of edge of burn a Split, the channeled to a single nozzle is, be different from a split, to any other nozzle is channeled within the same combustion chamber.

[0003] a control system for a gas turbine system used during the direct price increase of edge of burnautomatic control loop loops Split supplied to the nozzles for adjusting the one or more. Each edge parameter can be defined by a circuit. gas turbine emissionsedge parameter are, for example, predetermined numerical values or areas for such as NOx, CO, etc., and/or burn system dynamics[...] - [...] -characteristics, including parameters, the lean Show go out. [...][...] is a function of a defined for each feedback loop of the nominal value for the commanded edge parameter , said feedback to edge parameter and of the actual-Split actual value of the. The feedback to a direct measurement of the actual edge parameteredge parameter via can, or a combination of both a modeled estimate of the obtained edge parameter be. Another a further containment of a plurality of rear [...] -priority logic unit can carry out solvents-Split, so as to define the final commanded Split for the relevant nozzle.

[0004] at least some known burn modesgas turbine systems the gas turbine may be split into a number of different For be operated. The various burn modes , the numbers for the purposes of this disclosure (1.2, 3, etc.) and/or letters with (A, B, carbon, X, Y, Z, etc.) can be described, are different from one another with respect to the amounts of fuel and/or air, are supplied to the each nozzle within a combustion chamber, and/or with respect to the amounts of fuel and/or air, are supplied to the respective combustion chambers within the gas turbine. Specifically, burn modes determine the various, which nozzles are activated (i.e. get an amount of fuel and/or air supplied) and which nozzles are deactivated (i.e. no fuel and/or air supplied to get).

[0005] In at least some known burn modesgas turbine systems the various needed can, over a range of operating conditions for the gas turbine to operate optimally time. This range of operating conditions comprises different load conditions, the act on the gas turbine. Therefore, a combustion mode can correspond to a low load mode , a further combustion mode can correspond to an average load mode , and another combustion mode can correspond to a high load mode. These are only examples, and wherein at least some known burn modesgas turbine systems other criteria of interest can be linked with other. Furthermore, secondary factors may exist, which can influence the selection of the combustion mode for a particular gas turbine operating condition , such as ambient conditions, gas turbine conditions , and so on.

[0006] Such gas turbine systems , can work in several burn modes , it can be desirable, from a combustion mode transition to another, while the gas turbine is continuously operated further. However, it is not possible in such known gas turbine systems , burn modes to move between, while the turbine operates even under the conditions of a direct price increase of edge of burn. This is because that some of the edge measurements , directly for controlling and/or as an input in the models for edge parameter[...] , are used to control, are being used, of the instantaneous combustion mode are dependent on. Therefore these measurements may not be used, the passive Split predict precise. Therefore it is needed that the control system and the direct leaves price increase of edge of burn[...] without direct feedback loops would have resorted to a Of- [...] -. Open-Split burn reference parameter disposed on the basis of a measured or can be modeled, a, not by the combustion mode is dependent on the correspond to, and are usually stored in the memory within the control system, comprises the Split, under different operating conditions the various burn modes , for a change between burn modes to implement. After original or "landing points"-have been retrieved from a split-Plan Split completely reflect the operation of the gas turbine and the associated measurements in the new combustion mode, the direct price increase enterprise of edge of burn the gas turbine can be resumed. This method has several disadvantages, however. The first is the lack of reliability in operation and the additional risk of a possible exceeding of a edge borderopen circle plans according, when the direct Margin control is disabled. Secondly, determining and maintaining many different conditions for different [...]burn modes and can (, for example, different load transfer paths or discharge opening temperatures) for each mode and be expensive labour-intensive, since the drafting and maintenance of predetermined for repeated periodic [...] for a gas turbine the use of the maintenance operator includes pre-place-vote of the gas turbine.

[0007] a method is provided for use in the transition between an aspect In burn modes in a gas turbine. The procedure shall be implemented using a computing device, the comprises a processor is coupled with a storage device. The method comprises generating, with the computing device, data, the accounts for an original set of Split, so as to conduct fuel and/or air to at least a combustion chamber in the gas turbine. The method also comprises generating, with the computing device, a model of the gas turbine, wherein the data generated as an output gas turbine model , the account for at least an operating condition within the gas turbine. The method also comprises generating, with a first [...] within the computing device, data, the stand for at least one set of active [...] , for use in controlling the gas turbine in a first combustion mode, wherein the original [...] be used as an input. The method also comprises generating, with at least one second [...] within the computing device, data, the account for at least a set of passive [...] , for use in controlling the gas turbine in at least a second combustion mode, wherein a is used as an input [...] -created set.

[0008] The method can comprise that the generating a data signal, this is for at least one set of active [...] , comprises, with the first to generate data [...] , the represent several sets active [...] , the correspond to more combustion parameter- boundary values.

[0009] Each described above method can comprise, select data to the computing device, the stand for a set of active [...] , the correspond to at least one of the combustion parameter-extremes.

[0010] Each described above method can comprise that generating, with a first [...] within the computing device, data, the stand for at least one set of active [...] , comprising: receiving and selectively retransmitting, with a first logic knot , the original [...] ; generating, with a transfer function computation knot , which selectively logic knot is coupled with the first and is coupled with the gas turbine model module , data, the stand for a set operating parameters [...] , for use in calculating one or more on the basis of at least one predetermined combustion parameter-margin Split; generating, with a processing node, which selectively logic knottransfer function computation knot is coupled with the first and is coupled with the, data, the represent several sets active [...] , on the basis of the at least one first predetermined combustion parameter-margin; selecting, with a priority selection node is coupled to the processing nodes, a set of active [...][...] from the plurality of sets of active, the corresponding to a selected at least one combustion parameter-margin value; and sending, with the priority selection node , the selected active logic knot[...] to the gas turbine and the first.

[0011] Each described above method can comprise that the method comprises, between transition burn modes , determined after the computing device that a threshold a monitored operating condition exceeds a predetermined threshold value.

[0012] Each described above method can comprise that the transitioning between burn modes comprises, active [...] , the burn fashion transition be detected at the beginning of a, and passive [...] , the approach to use burn fashion transition Calculating continuously during the, , wherein the active [...]increment-hurry so be adjusted at the beginning of the transition, to move the passive [...].

[0013] Each described above method can comprise that generating, with a second [...] within the computing device, data, the generating account for at least a set of passive [...] , comprising :, with a transfer function computation knot , which selectively logic knot is coupled with a first and with the gas turbine model module is coupled, of data, the stand for a set operating parameters [...] , for use in calculating at Split on the basis of at least one predetermined combustion parameter-margin; generating, with a processing node, which selectively logic knottransfer function - computation knot is coupled with the first and is coupled with the, data, the represent several sets of passive [...] , on the basis of the at least one predetermined combustion parameter-margin; selections, with a priority selection node is coupled to the processing nodes, a set of passive [...][...] from the plurality of sets of active, the corresponding to a selected at least one combustion parameter-margin value; sending, with the priority selection node , the selected passive logic knot[...] with the first; and receiving and selectively retransmitting, with the first logic knot , the selected passive [...]transfer function computation knot and the processing nodes with the.

[0014] Each described above method can comprise that the method comprising: receiving, with a second logic knot , the active and the passive [...][...] ; and controlling the gas turbine using the active [...].

[0015] Each described above method can comprise that the method comprising: monitoring, with the computing device, at least one operating condition within the gas turbine; and passing, with the computing device, the control of the gas turbine from the first combustion mode to the second combustion mode, when the monitored operating condition exceeds a predetermined threshold value.

[0016] Each described above method can comprise that the transitioning, with the computing device, the control of the gas turbine from the first combustion mode to the second combustion mode comprises: selectively controlling the gas turbine using the passive [...] ; [...] from an active to a passive control regimecontrol regime converting the first; and converting from a passive to an active control regimecontrol regime[...] of the second.

[0017] According to a further aspect is provided a system for the transition between burn modes in a gas turbine. The system contains a computing device, the comprises a processor, and a computer readable storage device, the computer readable instructions are encoded on, by the processor. The-readable instructions cause the processor, to generate data, the accounts for an original set of Split, so as to conduct fuel and/or air to at least a combustion chamber in the gas turbine. The computer readable instructions further cause the processor, to generate a model of the gas turbine, wherein the data generated as an output gas turbine model , the account for at least an operating condition within the gas turbine. The computer readable instructions further cause the processor, to generate data [...] within the computing device with a first, the stand for at least one set of active [...] , to use it to be used in controlling the gas turbine in a first combustion mode, wherein the original [...] as an input. The-readable instructions cause the processor further, [...] within the computing device to generate data with at least one second, the account for at least a set of passive [...] , it is used in controlling the gas turbine in order to use at least a second combustion mode, wherein as an input a [...] -created set. The-readable instructions cause the processor further, between transition burn modes , by active [...] , the burn fashion transition be detected at the beginning of a, and passive [...] , the approach burn fashion transition Calculating continuously during the, be used, wherein the active [...]increment-hurry so be adjusted at the beginning of the transition, to move the passive [...].

[0018] The computer executable instructions of the system can cause the processor, with the first to generate data [...] , the represent several sets active [...] , the correspond to more combustion parameter- boundary values.

[0019] The computer executable instructions cause the processor system, can each above discussed, a set of active [...][...] select from the plurality of sets of active, the corresponding to a selected at least one combustion parameter-margin value.

[0020] The computer executable instructions can cause the processor to each above discussed system: receiving, with a second logic knot , the active and the passive [...][...] ;

and controlling the operation of the gas turbine using the active [...].

[0021] The computer executable instructions can cause the processor to each above discussed system: monitoring at least one operating condition within the gas turbine; and transitioning from the first combustion mode to the second combustion mode the control of the gas turbine, when the monitored operating condition exceeds a predetermined threshold value.

[0022] computer executable instructions discussed above may cause the processor to each system The the following: selectively controlling the gas turbine using the passive [...] ; [...] from an active to a passive control regimecontrol regime converting the first; and converting from a passive to an active control regimecontrol regime[...] of the second.

[0023] The computer executable instructions cause the processor system, can each above discussed, the first so to reconfigure [...] , [...] used as an input a self-created set that it.

[0024] The computer executable instructions cause the processor system, can each above discussed, the second to reconfigure [...] so that it the original [...] used as an input.

[0025] a gas turbine system is provided further According to one aspect. The gas turbine system comprises a compressor section, a combustion chamber assembly is coupled to the compressor section, a turbine section is coupled to the compressor section, and a system. The system comprises a processor and a computer readable storage device, the computer readable instructions are encoded on, by the processor. The-readable instructions cause the processor to generate data, the accounts for an original set of Split, so as to conduct fuel and/or air to at least a combustion chamber in the gas turbine. The computer readable instructions further cause the processor, to generate a model of the gas turbine, wherein the data generated as an output gas turbine model , the account for at least an operating condition within the gas turbine. The computer readable instructions further cause the processor, to generate data [...] within the computing device with a first, the stand for at least one set of active [...] , to use it to be used in controlling the gas turbine in a first combustion mode, wherein the original [...] as an input. The-readable instructions cause the processor further, [...] within the computing device to generate data with at least one second, the account for at least a set of passive [...] , it is used in controlling the gas turbine in order to use at least a second combustion mode, wherein as an input a [...] -created set. The-readable instructions cause the processor further, between transition burn modes , determined after the computing device that a threshold a monitored operating condition exceeds a predetermined threshold value.

[0026] The computer executable instructions can cause the processor, a rate limited change between the active and the passive [...] to implement [...] , wherein the active [...]increment-hurry be adjusted so that they are the passive approach [...].

[0027]

Fig. 1 is a graph of an exemplary gas turbine system.

2 is a schematic sectional view of an exemplary combustion chamber Fig. for use in the gas turbine system 1 shown in Fig..

Fig. [...]load path 3 is shown a gas turbine system 1 of an exemplary for the in Fig..

4 is a block diagram of the gas turbine system 1 shown in Fig. Fig., the an exemplary control system illustrated.

Fig. 5 is a graph of exemplary components, which are contained in the control system 4 shown in Fig..

Fig. 6 is a topological Chart of an exemplary procedure for the transition between burn modes.

[0028] It is possible that certain features of various embodiments of the disclosure are shown in some drawings, not in others. These but serves alone of simpler representation. According to the principles of the disclosure can each feature a drawing and/or in combination with each feature a different Drawing claimed be mentioned.

[0029] For the purposes of the present text "operating conditions" means one or more numerical values for physical parameters, the act during operation of a gas turbine, such as temperature and pressure of the exhaust manifold, compressor printing , compressor temperature , turbine power output, fuel flow and inlet air temperature. Some operating conditions, such as temperature and pressure of the exhaust manifold, can be measured directly, for example, by means of suitably placed sensors, are coupled with an appropriate programmed computing device. Other operating conditions, such as combustion pressure and temperature is difficult for them to be reliably measured by direct measurement, but by means of calculations can, be carried out by the computing device, on the basis of mathematical models are estimated, the work with other, measurable parameters.

[0030] The present disclosure concerns the control of a gas turbine, in particular using techniques of direct price increase of edge of burn. Techniques of direct price increase of edge of burnactive circle -Feedback method for controlling a gas turbine engine include the use of a using one or more sensors for feedback and the use of one or more actuators for controlling the gas turbine enterprise. At least some known gas turbines are, however, in a position, to work in several burn modes , correspond to the various combinations of fuel and/or air, are supplied to the individual nozzles within the combustion chambers, and/or the various combinations of fuel and/or air are in accordance with, the various combustion chambers within the gas turbine are supplied. Each combustion mode can not only include the supply of fuel and air in different quantities to each combustion chamber within a gas turbine, but also in different quantities, including no fuel and/or no air, to each nozzle within each combustion chamber.

[0031] As described above, the amount of fuel and/or air is, the denotes a nozzle is supplied, as a "split". Therefore, wherein at least some known gas turbine systems Split is the combination of, (for example, "X" mode) in a combustion mode are used, other than the combination of Split, in another combustion mode (for example, "Y" mode) are used. It should be noted that the determining of Split edge price increase logicburn operating mode and by the both by the direct, the combustion mode is used depends for the respective,.

[0032] In gas turbine systems it is not possible at least some of the region's popular, the gas turbine to operate over a substantially continuous direct price increase of edge of burn , while from a combustion mode is switched to another. Instead of whose a control system of a gas turbine system are correlated are fed to a set of plans managed provide fuel/air-Split, with burn reference parameters , "desired"-Split to original, said nozzles in each combustion mode at the beginning of the operation a gas turbine, prior to the implementation or resumption of direct price increase of edge of burn. The present disclosure provides for such a transition between burn modes in a gas turbine system before, while the gas turbine is located under a substantially continuous direct price increase of edge of burn.

[0033] algorithms for determining Split, the measured or estimated to be used within a gas turbine system under operating conditions, are well known. (Sometimes referred to as "transfer functions") comprise algorithms Such functions, the for predicting of parameters are used, are used during the control of gas turbine operations , the cannot be so simply by direct measure method. The present disclosure describes a method for the transition between burn modesprocessing regime[...] simultaneously in two separate in a gas turbine system with the aid of:a) an active control regime ; and b) a passive control regime. processing regimecontrol regime is defined as a An active, in which the system determined, are what the instantaneous Split, and this instantaneous Split used, so as to generate a gas turbine in a particular combustion mode for a realtime control [...] idealized, for example, mode X,. Or other words: the active processing regimecontrol regime is the is used to control the therefor, at that time the gas turbine. A processing regimecontrol regime is defined as a passive, in which so would be operated Split Calculating, as if the gas turbine system in another combustion mode, for example, mode Y, , but the mode Y-Split be determined under the assumption that the gas turbine operates under the same operating conditions, under which the active Calculating control regime -Split. When [...]control regime the transfer functions as a feedback input the passive use, would be operated under the passive regime would have been calculated are used, the for controlling the gas turbine, if the gas turbine under combustion mode Y. Or other words: control regime used during the control system the active, the splits are used to provide are used would calculated, the for the freewheeling turbine operation in a combustion mode, the control system simultaneously the splits, as a combustion mode for operating the gas turbine system in another stable condition solution.

[0034] In a gas turbine system, in which for example only two burn modes , X and Y, are available is used at any given time (for example, mode X) in active control regime a single combustion mode, while the other combustion mode is used in the passive control regime (mode Y). If, for example, during the operation of the gas turbine system in the determined mode X the control system is displayed that a change for combustion mode Y, so the control system can directly implement Split, stable condition enterprise in mode Y correspond to the one. As a result of the transition between control regimeburn modes combustion mode is for passive X, and Y is for actively control regime combustion mode.

[0035] More specifically, and as described above, a finite amount of time is-because a transition between burn modes requires-a mechanism for carrying out to transition from a pre-transition-Split to a After-transition-Split provided. Without such a mechanism there is a risk of an interruption of the smooth operation of the gas turbine, which can lead to undesirable effects, such as the interruption of electricity produced by the gas turbine or even a shutdown of the gas turbine. In the exemplary embodiment the gas turbine using the pre-transition-Split can burn fashion transition be operated up to the initiation of the. In the exemplary embodiment the advancing and statically [...]burn fashion transition could be detected upon initiation of the after-the move-. Having burn fashion transition is initiated the, a statically detected more guess-limited change can be implemented between advancing and After-transition-Split. Whereas guess-limited change could based on at least one of between the advancing and After-transition-Split original numerical value-difference are determined. The difference between the numerical values of the advancing and Split burn fashion transition are detected upon initiation of the can after-the move-. This numerical difference at a predetermined rate or over a certain finite time could then moves to zero (for example increment-hurry amended) and to the after the transition are added Split calculated. During the burn fashion transition can be calculated continuously in the passive mode the after the transition calculated Split, since it is not necessary that the gas turbine operates in the combustion mode for this second [...]. Once has been moved completely to zero and the associated measurements reflect the difference that the gas turbine operates in the new combustion mode, the direct [...]price increase enterprise of edge of burn can of the gas turbine using the second, the operates in the active mode, again will received.

[0036] In the described embodiments described in the present text are two burn modes. The control system can be configured in an alternative embodiment, , the gas turbine system to operate in an arbitrary number of burn modes. In such a system is the combustion mode is used to determine of Split, the actually the combustion chambers are fed in the gas turbine, the active control regime , during all below the passive control regime Calculating burn modes Split for the other.

[0037] 1 is a schematic illustration of an exemplary gas turbine system 101 Fig., 100 and a control system 120 comprises the a gas turbine. The 102 104 100 comprises a gas turbine and a combustion chamber assembly 100 comprises compressor building group. The gas turbine 108 and a common compressor/turbine rotor 110 further comprises a turbine section.

[0038] 102 103 flows compressor building group During the operation by the air, so that compressed air is fed to 104 of the combustion chamber assembly. Fuel (not shown) is channeled to a 105 burn region and/or zone, 104 defined within the combustion chamber assembly, wherein the fuel is ignited and mixed with the air. Generated combustion gases are channeled to the turbine section 108, wherein heat energy is converted into mechanical rotational energy from the gas stream. The turbine section 108 is coupled to the rotor 110, to rotate about an axis 106. In the exemplary embodiment the system comprises a load 101 112, 110 is coupled to the rotor. The 112 can be any device or system load, the 100 receives a rotational driving force from the gas turbine 110 over the rotor or the, order to function. 112 can be an electric generator, for example, the load. In the exemplary embodiment the gas turbine system comprises a control system 101 120, as is described further below in more detail.

[0039] 200 2 is a schematic cut end view of a combustion chamber Fig., 104 of the gas turbine 100 can be used in the combustion chamber assembly, the is shown in 1 Fig.. In the exemplary embodiment comprises five nozzles 202-210 200 the combustion chamber, around a peripheral edge 214 of the combustion chamber are arranged around 200. The nozzles 202-210 212. In an alternative embodiment, the combustion chamber a central nozzle surrounded 200 can any number, arrangement and/or configuration of nozzles comprise, the it allows the gas turbine 100, in the manner described in this text, to function. Some or all of the nozzles 202-212 can be adapted, for example, to supply a single component, including, for example, fuel and air. Alternatively, some or all of the nozzles can be arranged 202-212, any combination of these and/or other components to supply. Furthermore, 200 100 can comprise any number of combustion chambers the gas turbine, the allow the gas turbine 100, in the manner described in this text, to function.

[0040] In the exemplary embodiment can 103 105 and/or air fuel independently to each of the nozzles 202-212 (1 shown in Fig.) are channelled, so that the relative amounts (or the "split") of fuel and/or air, are channeled to the nozzle 202, other than the Split of fuel and/or air may be, the 204 is channeled to the nozzle, and the split of fuel and/or air, the channeled 206 to the nozzle is, as one of the other can be a Split, the to the nozzles 204 202 or channeled, and so on. 208 and 206 during a combustion mode include, for example, the nozzles need to receive only combustion air, while the remaining nozzles 202, 204, 210 and 212 only fuel or a combination of fuel and air received. In another combustion mode all nozzles 202-212 a combination of fuel and air received can. These are only examples, and the disclosure is not limited to this.

[0041] In the exemplary embodiment the gas turbine can by the control system 100 (shown in Fig. 1) 120 are controlled (1 shown in Fig.), so as to pass through a sequence of operating conditions is referred to, as a "load circuit". Fig. [...] 3 is a 300, 301 of the gas turbine 100 shows an exemplary generalized the load circuit (1 shown in Fig.). The load circuit 3 is a diagram 301 100 304 of the gas turbine as a parameter in Fig. as a function of a load acting on the gas turbine 302 shown 100. In the exemplary embodiment of the parameter 304 can be the exhaust gas temperature, the exhaust manifold (not shown) is sensed in a 100 of the gas turbine. Therefore, the parameter 304 can have a positive value as a function of the used units of measure non-zero, even if the gas turbine is under the load 100 302, the is a zero load. In an alternative embodiment, the parameter 304 can be any other characteristic of the gas turbine 100, the allows, as described in this text, to control the gas turbine 100.

[0042] in the exemplary embodiment of the parameter 304 (exit temperature is rising) in the mass, as the load on the gas turbine rises 100 302, 306 is as indicated by the ascending line. 100 (1 shown in Fig.) a reaches the gas turbine Ultimately, state, where the parameter 304 has a constant value. Falls the parameter 304 is the exit temperature, so the condition is an isothermal state, as indicated by a horizontal line 308. Throughout the rest of the operation of the gas turbine 100 can decrease the value of the parameter 304, as indicated by the descending line 310, 312 is achieved until a basis load. The basis loadstable condition the operation of the gas turbine 100 312 may represent a desired. 312 can represent basis load For example, the a state, in which the gas turbine (i.e. a generator) 100 a load 112 rotates with a desired minimum speed (1 shown in Fig.), operates to generate a required minimum amount of current can be fed to, the into a power distribution network, whereas, under a particular combustion mode.

[0043] In at least some known gas turbine systems , for example in turbine systems , are used in heat-stream-combined cycle, the load circuit 301 is fixed. It may, however, be desirable, a gas turbine 100 to allow it, a variable load circuit 301 to follow, for example, in response to a wide variety of variables. Such variables may, for example, variations in the ambient conditions, the gas turbine operating conditions , the external load requirements and/or fuel quality and availability include. This variables will be called simply as an example, and the disclosure is not limited to this. It allows the gas turbine 100 Will, to work by non-fixed load transfer paths, so is the number of enlarged [...] , the 120 must be managed in the memory of a control system may require includes, since every possible load circuit, a different combination of operating conditions (such as exit temperature), what, the various nozzles 104 100 202-212 each combustion chamber assembly within the gas turbine to supply other combinations of fuel/air-Split.

[0044] 4 is a block diagram of the gas turbine system 101 Fig., this shows in particular the control system 120. In the exemplary embodiment the control system comprises a computing device 305 120, 350 is coupled with one or more sensors. The or the sensors 350 are coupled with the gas turbine 100, 112 is coupled to the load. The (not shown) with a plurality of physical control devices 120 is further comprises control system coupled, such as valves or other flow control devices , the sources of fuel and air (not shown) are in flow communication with, the 100 are supplied to the gas turbine. In the exemplary embodiment the method described in the present text are arranged and systems, using existing physical control devices to be implemented, the are present in at least some known gas turbine systems.

[0045] The computing device 305 is programming techniques configured using known, the gas turbine and bring about, 100 to control the transition between burn modes , while the gas turbine 100 with the active price increase of edge of burn is direct. 314 315 305 comprises a memory device and a processor's computing device, are operatively connected with the storage device 314, to execute instructions. The processor 315 can comprise one or more processing units (for example, in a multi-core configuration). In some embodiments be stored in the storage device 314 executable instructions. The computing device 305 can be configured, by programming the processor to perform one or more operational processes described in this text 315. 315 can be programmed, for example, the processor, by an operation as one or more executable instructions coded and the executable instructions are provided in the storage device 314.

[0046] the term "processor" is present text For the purposes of not only limited to those integrated circuits, referred to as a computer which the person skilled in the art, but believes micro CONTROLLER a in the general sense, a microcomputer, a programmable logic controller (PLC), an application specific integrated circuit, and other programmable circuits, and these terms are used in this text, synonymous. In the present text "memory" can, for example, in the described embodiments a computer-readable medium, such as a random access memory (ram), and a computer readable non-volatile medium, such as a flash memory, be. Alternatively, a floppy-disk, a compact disc-read only memory (CD-ROM), a magnetic optical disk (MOD) and/or a digital versatile disk (DVD) are used. Thanks be further input channels in the described embodiments computer peripheral in this text, are connected with a user interface, such as a mouse and a keyboard. Alternatively, other computer peripheral are used, such as a scanner. In the exemplary embodiment can also be, for example, a further output channels user interface monitor.

[0047] The memory device 314 can be adapted, to store operational measurements, such as real time temperature and temperature profile and mass flow values , and/or other other types of data. In some embodiments removed or "rinsed" the processor 314 315 data on the basis of their age from the memory device 315 Overwrite previously recorded and stored can. For example the processor data, the are associated with a later time and/or a later event. Furthermore, or alternatively the processor can remove 315 data, the exceed a predetermined time interval. Furthermore, the memory device 314 comprises, for example, enough data, algorithms and commands, to allow for the execution of one or more shown transfer function computationsburn modes described 100 (in 1 Fig.) the gas turbine, as in this text,.

[0048] the term "real time" thinks of the present text For the purpose of entering the associated events and/or a time to the time of the measurement and detection of pre-established data and/or the time for processing the data and/or the time of a system response to the events and the surrounding area. In this text, these activities can occur in the substantially instantaneously and events described embodiments.

[0049] In some embodiments the computing device 320 a 305 comprises presentation interface , 315 is coupled to the processor. The presentation interface 320 325 presents a user information, such as a user interface and/ora alarm. 320 (not shown) the In one embodiment comprises a display adaptor presentation interface , (not shown) is coupled with a display device, such as a cathode ray tube (CRT), a liquid crystal display (LCD), an organic LED (OLED)-display and/or a "Electronic Ink"-display. In some embodiments the one or more display devices 320 comprises presentation interface.

[0050] In some embodiments the computing device comprises a user input interface 330 305 330. In the exemplary embodiment the user input interface includes 325 315 is coupled to the processor 330 receives inputs from the user and a keyboard, for example, can. The user input interface includes, a pointing device, a mouse, a pin, a touch panel (for example a touch pad or a touch screen) (including, for example, a microphone) comprise audio entrance interface and/or a. A single component, such as a touch screen, can also act as both as a display device as a 330 320 and user input interface includes presentation interface.

[0051] A 315 335 is coupled to the processor and configured communications interface, communicatively to be coupled with one or more other devices, such as a sensor, an actuator or another computing device 305, and input and output operations with respect to such devices to execute. A wireline network adapter 335 can include, for example, the communication interface, a wireless network adapter, a mobile telecommunications adapter , comprise a serial adapter and/or a parallel communication adaptor. Data from one or more remote devices can 335 communication interface The receive and/or transmit data to one or more remote devices. For example a communication interface 305 335 335 can send an alarm to the communication interface a computing device 305 a different computing device.

[0052] The presentation interface 320 335 are both in a position and/or the communication interface, provide information, are suitable for use with the method described in the present text (325 or other devices, for example, to the user). Therefore, 335 320 can be described as the output devices and the communications interface presentation interface. 330 335 able and the communication interface are equally the user input interface includes, receive information, are suitable for use with the method described in this text, and can be described as input devices.

[0053] to perform the functions described in this text, in order, the control system 120 comprises a plurality of functional components or modules within the computing device 305 (4 shown in Fig.). These functional components or modules in the exemplary embodiment have the form of a suitable programming is stored in said memory device and using the computing device 305 Running 314. Fig. 5 is a graph 500 of at least some of the functional components, the control system 120 are contained within the (4 shown in Fig.). In controlling the operation of the gas turbine 502 can a database For example 100 (1 shown in Fig.) are used. In the exemplary embodiment the control system comprises an arbitrary number and type of databases 120 502, the enable the control system 120, in the manner described in this text, to function. The database 502 is coupled with a plurality of separate modules within the computing device 305, the Run certain tasks, as is described further below in more detail. In the exemplary embodiment, the database is divided into multiple sections 502, 504 and 506, for example, including the exemplary embodiment a reference data sectionplanning data section 502 a comprises an arbitrary number. In the database and type of sections, the enable the control system 120, in the manner described in this text, to function. 504 and 506 may bind together sections The, to retrieve information, the operations described below and with the components contexts. 504 can comprise reference numerical valuesreference data section For example, the various, such as Re- [...] - exhaust elbow union discharge opening temperatures , the be used, to determine order is required, when a displacement from one combustion mode to another combustion mode. Plans of fuel/air ratios 506 can planning data section The (also referred to in this text as "Split") comprise, the quantities of fuel and air are used for defining, for example, each of the fuel/air nozzles 202-212 are supplied (2 shown in Fig.).

[0054] 120 can further function components (5 shown in Fig.) control system The comprise, including for example a fuel system model module 508, 510 a gas turbine model module , a first ("mode X"-) [...] 512, 514 and a second ("mode Y"-) 508 516. The fuel system model module[...] Split a general processing module determined original, are 100 104 of the gas turbine to supply the of the combustion chamber assembly, prior to implementing the price increase of edge of burnturbine enterprise from a direct. The module 508 determines the original Split based on one or more actual real-time parameters of the gas turbine 100. In the exemplary embodiment (not shown) shall send one or more sensors, such as difference of pressure signal converter , data to the computing device 305, the stand (not shown) exhaust manifold of the gas turbine for a pressure within a 100. On the basis of the print data 508 engages the module (not shown) back to a split-plan, for example is stored in the storage device 314 (4 shown in Fig.), so as to determine appropriate Split to be fed, the 104 of the combustion chamber assembly. This Split can ultimately affect the command signals, the (not-shown) to different gas turbine actuators Sending, such as command signals to gas price increase valves.

[0055] The gas turbine model module developed and continuously updated 510 turbine enterprise a mathematical model of the gas turbine during the 100. 440 510 receives input signals from various sensors 736 The module, such as the values represent exhaust elbow union temperature , compressor printing , compressor temperature , power output of the load (1 shown in Fig.) 112, such as the generator output, fuel flow and inlet air temperature. The 440 can be the same sensors as the sensors 4 shown in these values generated 350. Using Fig. sensors 510 estimated numerical values for instantaneous operating conditions within the module 100 of the gas turbine, the express otherwise may not are observable, including, for example, estimated emissions, gas turbine dynamics and temperatures and pressures at locations within the gas turbine 100, where no sensors can work reliably and can be placed, such as combustion chamber temperatures and-.

[0056] The [...] 512 presents a number of mathematical processes and calculations, the lead for generating data, the correspond to a set of Split, the corresponds to a first combustion mode. In the exemplary embodiment of the first combustion mode can be an arbitrary desired combustion mode, for example, mode X, can be linked with a set fuel and [...] , the correspond to a first load state. More specifically, the module is 512, as described in this text, practically in the situation, to calculate Split, the correspond to more edges of parameter , are associated with combustion mode X, in which the gas turbine 100 can operate. However, , as is described further below in more detail, only a single set of Split, the correspond to at least one predetermined edge of burn parameter of combustion mode X, than is ultimately output of the module 120 512 selected by the control system. The [...] 514 presents a number of mathematical processes and calculations, the lead for generating a set of Split, the correspond to a second combustion mode, in the exemplary embodiment any other mode than the mode may be, the the control system 120 has selected the output from module 512 may be linked as, for example, mode Y, with a set fuel and [...] , the correspond to a second load state. The module 514 is being equally able, to calculate Split, corresponding to said more edges of parameter , are linked to the combustion mode Y, in which the gas turbine 100 can operate.

[0057] Same as above described in this text, as the case may be is, 512 and 514 which operates in the "active control regime " of the modules and which operates in the "passive control regime ", the output of one of said modules (referred to as " [...] ") 512 a set Split, the practically for controlling the flow of fuel, air, etc. are used within the gas turbine 100, while the output of the other of said modules are used as a feedback (also " [...] ") 514, so that the module, the is located in the passive control regime , continuously generates Split, the for the prevailing operating conditions within the gas turbine are currently or "valide" 100.

[0058] in the exemplary embodiment, the control system 512 and 514 120 comprises two [...]. In an alternative embodiment, the control system 120 can comprise any number of [...] , the enable the gas turbine system 101, to function in the manner described in the present text. Moreover, the control system can comprise an arbitrary number and type of other modules 120, which may be required, the control system 120 to allow for it to function, in the manner described in the present text. Furthermore, each can comprise further functional components in the modules described in this text itself. In the exemplary embodiment each of the modules and comprises For example 512 514 further function components therein, including a first logic knot , a transfer radio - [...] , of a processing node and a priority selection node , as is described further below in more detail.

[0059] Fig. 700 is a topological Figure 6, shows the flow of information between the modules operates the 508, 510, 512, 514 and 516 during a direct price increase of edge of burn of the gas turbine 100 and in particular (1 shown in Fig.) illustrates, as transitions between Enabling burn modes , while the gas turbine 100 from a direct price increase of edge of burn. The control system 120 via the module 508 receives, via one or more sensors 702, such as exhaust elbow union difference of pressure signal converter , signals 704, the (not shown) within a a represent real time printing 100 of the gas turbine exhaust manifold. After the converting the signals to a pressure value (not shown) the control system on the basis of a determined 120 Split-plan, of the in the storage device is stored (3 shown in Fig.) 314, a set of original Split. In the exemplary embodiment, the control system can store in the storage device 120 314 original Split plans, the correspond to each combustion mode, in which the gas turbine 100 can operate. In another alternative the control system can manage a Split-Plan for use 120, which simply correlated with certain pressure values regardless of the combustion mode Split. In a further alternative the control system can use any Split-Plan 120, it can be derived from the original Split 101 enables the gas turbine system and the, in the manner described in this text, to function. The control system 120 transmits a data signal 706, the corresponds to the original Split, 512 and 514 to the modules at the same time 6 shown in the exemplary embodiment is located. In Fig. under mode X-controlling the gas turbine, either as Default (such as during the booting), or by the control system 120 has been selected by mode X previously.

[0060] As previously described, each 512 514 further comprises a first of the modules and logic knot , a transfer function computation knot , a processing node and a priority selection node. To be more specific, the module 710 comprises a 512 logic knot , at least one transfer- function computation knot 714, 716 and 726 priority selection nodeequally comprises at least one processing node 514 a logic knot the module 738. a, 746 transfer function computation knot at least one, at least one processing node 748 756 priority selection node. In the exemplary embodiment the respective node and a lead 512 and 514 similar types of calculations from within the modules, has been described as above. However, the calculations on exported 512 within said module be concentrated within the combustion mode X Split, while the inside of the module within the combustion mode are concentrated on Split 514 executed calculations Y.

[0061] For example, the control system 120 is configured in Fig. 6 that module 514 512 operates in the combustion mode in the active control regimecontrol regime operates in the combustion mode in the passive module X and Y. Therefore, 512 708 mode decision signal configured in the module (516 is implemented, for example, by means of the module the) the node 710 so that the data signal 706, 508 by the module 120 is transmitted by the control system, via said link 712 714 is transmitted as an input to the node. By contrast, , because the module operates in the passive control regime 514, the node 708 738 mode decision signal the configured so that it receives a signal 760, 756 is output of the node that sends a, 742 744 and 746 it as an input to the node via said link.

[0062] node 120 746 714 and constitute put portions of the control system, which is advantageously are programmed, so as to receive as inputs signals correspond to, the splits. 746 714 and 715 or additionally as inputs signals received node The 750, 510 Sending by the module. As previously described, the module 510 510 100 generates a mathematical model of the gas turbine serves as a "mathematical" sensor the module. Therefore, , the data generated, represent the instantaneous real-time operating conditions, which exist within the gas turbine 100. Each the node 714 746 has presented a series of mathematical processes and/or calculations constitute and, the lead for generating data, the operating parameters for the gas turbine 100 [...] correspond to a set, can be used to calculate the corresponding to in turn, Split, the burn modes. These data in output signals are 720, embodies 752, or 714 746 Sending the of nodes. 512 and 514 processed its respective inputs and a plurality of the modules Each produced by Split sets, are embodied as outputs 728 or 760 corresponds to the, wherein each set of Split a potential combustion mode of the gas turbine 100.

[0063] If the module 512 control regime operates in the active, as shown in 6 Fig., so the processing node receives as inputs the original [...] 716 718, 720 one or more signals, by the node 714 Transferring shown, and an equivalent number of reference signals 722, for example, from the memory device 314 (in 2 Fig.) Fetching. The reference signal comprises data 722, the parameters represent target being for different, as the controlling parameters for burn operations have been defined previously. If the module operates in the passive control regime 514, as shown in 6 Fig., so the processing node receives as inputs the 744 748 [...] , one or more signals 752, 746 were transmitted by the node, and an equivalent number of reference signals 754 754. In the exemplary embodiment the reference signal 722 can be identical with the reference signal. The is to say, it goes without saying that "signals" 720, 722, 724, 752, 754 and 758 in one embodiment each represent a group or a set of signals, and not a single signal.

[0064] The node 748 716 and generate, using their respective inputs, as described above, several sets of Split, wherein each set corresponds to a predetermined X or Y edge of burn parameter of the combustion mode, the available are of the gas turbine 100. 716 748 758 724 or generate output signals and the nodes Therefore, , which comprise each data, the corresponding to each of the sets of Split, 716 or have been generated by the node 748. 756 758 724 and 726 and respective signals received and priority selection node The a selection logic to turn, correspond to limit as outputs signals comprise has determined to correspond to, the data, the certain edges of burn parameter for burn modes X and Y, the the control system and the actively and passively control regime 120 for use. If we adopt for example that in the exemplary embodiment, the control system 120 has determined that the gas turbine is to operate in mode X 100 control regime[...] the active, wherein a particular edge of burn parameter A of the controlling parameter is, 724-726 ostracises the signal priority selection node so the data, the mode a and transmits these data correspond to- edge of burn parameter A-Split X as an output 728, the module 516 710 Sending logic knot both for and with respect to the first. Therefore, 120 causes the control system, when the module is located in the passive control regime 514, as determined by the control system 120, the priority selection node 756, 758-data from the signal, the select edge of burn parameter B correspond to-the one combustion mode Y (of optionally the same controlling edge of burn parameter may be is used in the active control) and transmits this data as an output to the module 760 760. The signal 738 logic knot 516 Transferring both and with respect to the first. 512 and 514 continuously a stable condition solution for each module determines a Accordingly Split set, the 760 728 and are embodied in the signals, controls are required to be used is determined to corresponds to is transmitted to forward them to the gas turbine 100 is transmitted via the signal 734, by the module 516, the another combustion mode and/or another controlling edge of burn parameter , wherein the signal 100 728 actively the gas turbine, and the signal 760 passively and available, to the gas turbine 100 and, when the control system 120 that a transition between burn modes. To be more specific, the signal 760 serves as a prediction for the "objective"- [...]stable condition -Split combustion mode, in the is to be moved.

[0065] In the exemplary embodiment, node 748 716 and are illustrated as individual or individual node. 716 (not shown) alternative embodiment, each node in a can, be replaced by a plurality of node 748, whose signals are channelled priority selection node 726 or 756 to, wherein the plurality of nodes represent different controlling edges of burn parameter for an individual common combustion mode.

[0066] As previously described, [...] control, are carried out over the module 512, actively Split pre-Transitional combustion mode, so that the instantaneous measurements, are used for a direct Margin control, are used as inputs to the models or the, order to generate direct edge estimations valide are, before burn fashion transition. As previously described, the control over the module 514 calculated Split not, at least initially, as described in this text, the gas turbine before the mode transition , and thus as an input a self-created set [...] use. [...] , 514 are carried out over the module, the output as an input into one or more transfer functions Split use, which model the necessary [...]. In this configuration the module 514 leads from an iteration, so as to determine an estimate of the desired Split would work, as if the gas turbine 100 in the second combustion mode. The system 120 is configured that converge above-mentioned calculations such a way that it to a final solution before burn fashion transition , so that the on the module can be used to determine [...] 514 executed, the desired final After-transition burn transition just before the initiation of the-Split.

[0067] in the exemplary embodiment the decision signal to the processing module 120 generates and 732 516 can be sent by the system is required by the control system 120 to implement provisions for, when a transition from a combustion mode to another. For example, the control system can monitor 120 mode transition criterion or a given set a predetermined criteria, for example, an operating parameter, such as the exhaust elbow union temperature. If a predetermined threshold of the operating parameter (either upwardly or downwardly) is exceeded, so the control system 120 generates a signal 732, 516 is received by the module, so as to cause to Send shown, as in Fig. 6, a change between 100 728 burn modes by terminating transmission of the signal to the gas turbine, and instead the signal 760 to the gas turbine 100. The 712 742 are so connected and left that the node 728 710 714 receives as input the signal for sending to the node, and the node receives as input the data signal 738 746 706 to send to the node 120 is configured in the exemplary embodiment the control system ., a smooth transition between the active and the previously passive Split 760 728 Split of the signal to cause the signal. The output signal 514 760 of the module, when working in the passive control regime , a set of Split appropriates, the "landing points" than the original Split or serves for the initiation of the active control during a changing over from the (previously actively controlled via the module 512) combustion mode X (previously passively controlled via the module 514) for combustion mode Y.

[0068] Specifically, can, as previously described, without a mechanism for effecting the controlled physical transition between burn modes be affected the operation of the gas turbine 100. In an exemplary embodiment of the operation of the gas turbine 100 can be continued using pre-transition-Split, 512 are generated by the module is initiated until a determined burn fashion transition , for example, from mode to mode Y. After the system 120 X that the conditions are met for a burn fashion transition , the advancing and prior to initiation of the statically burn fashion transition could After- [...] -values are detected. The system 120 initiates burn fashion transition by implementing a rate limited alternation between the static advancing and a recharging transition-Split. The system 120 can be configured in an exemplary embodiment, for example, via the module 516 the rate limited change based on one or more original numerical value differences between one or more corresponding pairs of the advancing and After-transition-Split to calculate. The differences between the numerical values of the corresponding pairs of said advancing and burn fashion transition Split are detected upon initiation of the can after-the move-. This difference in figures (oder-differenzen) over a certain finite time at a predetermined rate or could then moves to zero (for example increment-hurry amended) and to the after the transition are added Split calculated. During the burn fashion transition can be calculated continuously in the passive mode the after the transition calculated Split, since it is not necessary that the gas turbine 100 operates in the combustion mode for the calculation of the Split of the passive regime. After the difference to zero has been moved completely the operation of the gas turbine and the associated measurements reflect 100 in the new combustion mode Y, the direct price increase enterprise of edge of burn can be resumed using Split 100 of the gas turbine, over the module 514 have been calculated, but now in the operation of the active mode. The above-described actions are only as an example, for the transition between burn modes , and can be carried out in other embodiments other actions and calculations, to allow the system to function to it, in the manner described in the present text.

[0069] in the exemplary embodiment, the control system 120 is described as the transitioning between two burn modes , X and Y,. In an alternative embodiment, the control system 120 can be in a position, between each desired number of transition burn modes. In such an embodiment, the control system would comprise 120 so many Accordingly burn transition mode modules , as it gives burn modes , the stand 100 available to the gas turbine. mode selection logic functions 710 738 shown by the processing module 516 and can as a result be carried out. The above-described operations can take place during any phase of the operation of the gas turbine 100, including during start up, the steady-state operative condition and the shutdown of the turbine.

[0070] 512 and 514 at least two modules 120 can by providing the control system continuously determine, which are supposed to be implemented for transitions between at least two burn modes Split efficient, if the control system 120 determined that a change of the combustion mode at any [...]price increase enterprise of edge of burn of the gas turbine requires 100 is a direct. Therefore, the control system must do not achieve substantial [...] Invoke 120, the otherwise developed and 314 are managed in the memory device (4 shown in Fig.) would have. Whereas burn fashion transition allows a direct Margin control in active form during the the use of a more reliable control of Split, so as to prevent the exceeding of edge of burn parameter -limit values.

[0071] The method described in this text, at least some of the disadvantages of known systems and eliminate gas turbine systems. For example, the method described in this text, and systems enable burn modes with reduced the aid of predetermined [...] transitions between. Furthermore, the method described in this text, the operation of gas turbine combustion chambers and systems enable via a further range of operating conditions and load paths , instead of working to be limited to point, along a limited number of fixed predetermined load transfer paths. The method described in this text, further comprising the use of a direct and systems enable price increase of edge of burnprice increase enterprise of edge of burncombustion chamber operatings mode with fewer interruptions in active in more direct. More specifically, the methods and systems described in this text, allow reliable transitions between burn modes , while the gas turbine is located with the active control further. Furthermore, the method described in this text, and systems enable burn modesgas turbine control hardware without additions and/or modifications of existing improved transitions between.

[0072] It is understood that the above-discussed embodiments, are described in more specific detail the were, only exemplary and that there are many other combinations or possible embodiments, additions or alternatives that may be contained.

[0073] Furthermore, the specific nomenclature is of the components, the Capitalization of terms, the attributes, data structures or any other programming or structural aspects neither mandatory still be distinguished, and the mechanisms, which implement the disclosure or their features, may also other names, formats or protocols have. Furthermore it via a combination of hardware and software the system, as described, or completely in hardware elements are implemented. Furthermore, the specific pitch is the functionality between the various system components described in this text, only as an example and not mandatory; functions, are performed by a single system component, may be performed instead by a plurality of components, and functions, are performed by a plurality of components, may be performed instead by a single component. Systems and techniques described here can in digital electronic implementations of Miscellaneous circuits, integrated circuits, specially designed ASICs (application-specific integrated circuits), hardware, firmware, software and/or combinations thereof are realized. These various implementations may include one or more computer programs in an implementation, the system can be designed and/or interpreted in a programmable, including at least one programmable processor, a general purpose processor may be a [...] is coupled the so that he data and instructions from one storage system, at least one input device and at least one output device can send to and abutting received.

[0074] This computer programs (also as programs, software, software applications or code known) can comprise a programmable processor and in a higher machine instructions for procedural and/or object-oriented programming language and/or be implemented in Assembly-/ machine language. For the purposes of the present text the terms "machine readable medium" and "computer-readable medium" my any computer program products, devices and/or equipment (for example, magnetic discs, optical disks, memory, logic devices (PLDS) Programmable), the are used, in order to forward data to a programmable processor machine instructions and/or receives, including a machine-readable medium, the machine-readable signal machine instructions as a. The term "machine readable medium" means any instrument or signal, the is used, and/or data to a programmable processor to forward order machine instructions. "Machine readable medium" and "computer-readable medium" contain the The but no transitory signals.

[0075] Whereas logic rivers not specifically shown in Figures shown require the order or sequential sequence, to achieve desirable results for. Furthermore, further steps can be omitted or added to the described by these rivers, and further components can be added or to the systems described by these omitted. Other embodiments lie within the scope of protection of the following claims also accordingly.

[0076] Some basis of algorithms and symbolic representations portions of the above description of operations on information present characteristics. Algorithmic descriptions and representations can be used by the data processing specialist this, the essence of his work most effectively to convey other experts. Although functionally or logically described are These operations, but it goes without saying that it be implemented by computer programs. Furthermore, it is occasionally considered appropriate has been shown, these arrangements of operations as modules or to give function names to describe them, without that the universality is lost.

[0077] Provided from the above clearly indicates otherwise Meeting, it is understood that throughout the description Meetings, where "processing" or "computer calculation" for example, concepts such as "calculating" or "determining" or ortho-the "displaying" or "providing" or the like are used, on the action and processes of a computer system or similar electronic computing device relate to, and converts the data manages, as physical (electronic) quantities within the the computer system memory or-registers or other such information storage, - [...] - indicators be represented.

[0078] The method described in the present text by a computing device in communication with a storage device and systems may [...] - engineer techniques be implemented using, such as computer software, firmware, hardware or any combination or subset thereof, wherein the technical effects are achieved, at least one of the following actions is performed by:a) generating data, the accounts for an original set of Split, are to be used to conduct fuel and/or air are generated in the gas turbine to at least one combustion chamber; b) creating a model of the gas turbine, wherein the as an output data gas turbine model , the inside of the gas turbine for at least an operating condition; c) generating data, the for at least one set of active [...] , for use in controlling the gas turbine in a first combustion mode, wherein the original Split data as an input;

and d) generating data, for at least one set are passive [...] , for use in controlling the gas turbine in at least a second combustion mode, wherein a is used as an input [...] -created set.

[0079] The technical effects can also be achieved by by performing at least one of the following actions: a) generating data, the represent several sets active [...] , the correspond to more combustion parameter- boundary values ; b) selecting data, the stand for a set of active [...] , the correspond to at least one of the combustion parameter-extremes; c) receiving and selectively retransmitting the original [...] ; d) generating, with a transfer function computation knot , data, the stand for a set operating parameters [...] , for use in calculating one or more on the basis of at least one combustion parameter-margin value Split; e) generating data, the represent several sets active [...] , on the basis of the at least one first combustion parameter-margin; f) selecting a set of active [...][...] from the plurality of sets of active, the corresponding to a selected at least one combustion parameter-margin value; g) sending the selected active logic knot[...] to the gas turbine and the first;

and hr) merge between burn modes , determined after the computing device that a threshold a monitored operating condition exceeds a predetermined threshold value.

[0080] The technical effects can also be achieved by performing at least one of the following actions: a) implementing a rate limited change between static advancing and After-transition-Split; b) calculating the rate limited change on the basis of one or more original numerical value differences between one or more corresponding pairs of the advancing and After-transition-Split; c) detecting the differences between the numerical values of the corresponding pairs of said advancing and After-transition-Split burn fashion transition upon initiation of a; 1) moving the difference to zero (for example changing [...]) or over a certain finite time at a predetermined rate and adding the moving difference to the after the transition calculated Split; d) continuously calculating the recharging Transitional Split in the passive combustion mode; and e) resuming direct price increase enterprise of edge of burn , reflecting the difference to zero after the operation of the gas turbine and the associated measurements has been moved completely in the new combustion mode, the mode is now the active.

[0081] This written description uses examples for Where of the claimed article, including the best mode, and also for the purpose, to allow it to a person skilled in the art, to practice the claimed article, including any devices or systems and the manufacture and use of execution any herein of picked-up method. The patentable scope of protection defined by the claims and is described in this text, the article can comprise also other examples, the incident to the person skilled in the art. Such other examples are intended to fall within the scope of protection of the claims, if they have structural elements, which comprise there are no different from text of the claims, or if they equivalent structural elements, the only insignificantly differ from the text of the claims.

[0082] a method and a system are provided for transitioning between 120 It burn modes in a gas turbine. A processor generates data, the accounts for an original set of Split, so as to conduct fuel and/or air to at least a combustion chamber in the gas turbine. A gas turbine model module 510 generates data, the at least one stand for turbine operating condition. A first [...] 512 generates data, the stand for at least one set of active [...] , for controlling the gas turbine in a first combustion mode, wherein the original [...] be used as an input. A second [...] 514 generates data, the account for at least a set of passive [...] , for controlling the gas turbine in at least a second combustion mode. The transition between burn modes[...] using at least one of the active and the passive [...] can be accomplished.

310 Down inclined line 312 basis load

314 315 processor memory device

320 325 user presentation cutting hurry

330 335 350 sensor communication cutting hurry user input interface includes

440 sensor

500 Chart

502 database

504 506 508 510 reference data sectionplanning data sectiongas turbine model module[...] m m or 512 514 [...] fuel 516 General processing module 700 [...] u I topological Chart 702 sensor

704 signal

706 signal

708 710 logic knotmode selection logic

712 Link

714 715 signal transfer function computation knot

716 718 720 output signal [...] Original processing nodes

722 reference signal

724 output signal

726 728 output signal [...]

732 logic knot

734 signal

736 input signal

738 First logic knot

742 Link

744 [...]

746 transfer function computation knot

748 processing nodes

750 signal

750 output signal

752 output signal

754 reference signal

756 [...]

758 output signal

760 output signal