System, program product and method for detecting thermal stability in a gas turbine system - Patents.com

Abstract

To provide a system, a program product and a method for detecting thermal stability within a gas turbine system.SOLUTION: A system may include a computing device 100 in communication with a plurality of sensors 106 positioned within a gas turbine system 11 or adjacent to the gas turbine system. The sensors may measure operational characteristics of the gas turbine system. The computing device may be configured to detect thermal stability within the gas turbine system by performing processes including calculating a lag output for each of the plurality of measured operational characteristics. The calculated lag output may be based on a difference between a calculated lag for the measured operational characteristics and the measured operational characteristic itself. The calculated lag output may be also based on a time constant for the measured operational characteristics. The computing device may also determine when each of the calculated lag outputs is below a predetermined threshold.SELECTED DRAWING: Figure 1

Description

[Technical field]

[0001] The present disclosure relates generally to gas turbine systems, and more particularly to a system, program product, and method for detecting thermal stability within a gas turbine system. and It concerns the method. [Background technology]

[0002] In conventional power systems, the system and / or To ensure it is operating at its highest efficiency, the operating parameters of Continuous monitoring vinegar For example, various operating parameters in a gas turbine system of measurement and / or Monitoring death Whether the gas turbine system is operating at the desired performance Whether or not / or Is it producing the desired / required amount of power output? No or no Such operating parameters include the temperature of the fluids in the various stages of the gas turbine system. and / or Conventional systems use pressure to determine the operating condition of a gas turbine system. or To estimate the operating parameters of Observation over time death For example, these operating parameters can be observed over time, which allows an operator of a gas turbine system to assume that the system is thermally stable if the operating parameters remain constant. Thermal stability of a gas turbine system can be important in operating the gas turbine system at a desired efficiency, particularly if, for example, the system relies on the operating parameters of a thermally stable system in a steady-state operating model. and / or These operating models can be important in determining power output, operating efficiency, and emissions. and / or Increases other similar properties and / orThe operating parameters are used to tune the gas turbine system for improvement.

[0003] However, in conventional systems, an operator may make inappropriate assumptions about the operating state of a gas turbine system based solely on the operating parameter data. For example, an operator may assume that there is no change in the operating parameter data detected by additional sensors. Or change Based on the fact that parts Heat saw is not fully / completely Q and / or This may lead the gas turbine operator to erroneously conclude that the system has been heated to operating temperature, i.e. that the gas turbine system is thermally stable and therefore does not require any further "start-up" operations. or It may be improperly determined that the system is not operating during the "ramp-up" phase and should be operating at "steady state". As a result of this determination, the flow rates, combustion temperatures, etc., are adjusted to ensure the system is producing the desired power output. and / or Increased operating parameters such as fuel supply death However, the gas turbine system is not thermally stable. and / or System parts Premature transition to "steady state" operation, where the load is not fully heat soaked, can actually reduce the operating efficiency of the system. It is possible / or System parts subject to undesirable operating parameters (e.g., fluid temperature) It is possible Exposure to undesirable operating parameters can lead to, for example, parts There may be an increased risk of damage (e.g. creep) to the Summary of the Invention

[0004] A first aspect of the present disclosure is a gas turbine system. and Multiple Sensors The present invention provides a system comprising at least one computing device in communication with: At least one of the multiple sensors teeth Gas Turbine Systems Within orA gas turbine system having a plurality of sensors disposed adjacent to the gas turbine system. Each Sensors teeth Measuring one of several operating characteristics of a gas turbine system death, At least one computing device teeth , of multiple measured operating characteristics For each lag Calculate the output Steps And the calculated lag The output is a measured operating characteristic of the gas turbine system. About Calculated lag and the difference between the measured operating characteristic, and Multiple measured operating characteristics Regarding each Based on the time constant, Steps And, it was calculated lag Output each Determine when is lower than a given threshold Steps wherein the predetermined threshold is a function of a plurality of measured operating characteristics of the gas turbine system. and Build parameters each Based on Steps and detecting thermal stability in the gas turbine system by performing a process including: R .

[0005] A second aspect of the disclosure, when executed by at least one computing device, comprises: or A plurality of measured operating characteristics of the gas turbine system measured by a plurality of sensors disposed at least one adjacent to the gas turbine system. For each lag Calculate the output Steps And the calculated lag The output is a measured operating characteristic of the gas turbine system. About Calculated lag and the difference between the measured operating characteristic, and Multiple measured operating characteristics Regarding each Based on the time constant, Steps And, it was calculated lag Output each Determine when is lower than a given threshold Stepsthe predetermined threshold is a function of a plurality of measured operating characteristics and build parameters of the gas turbine system; each Based on Steps and detecting thermal stability in a gas turbine system by executing a process that includes:

[0006] A third aspect of the present disclosure is a method for detecting thermal stability in a gas turbine system, the method comprising: or A plurality of measured operating characteristics of the gas turbine system measured by a plurality of sensors disposed at least one adjacent to the gas turbine system. For each lag Calculate the output Steps And the calculated lag The output is a measured operating characteristic of the gas turbine system. About Calculated lag and the difference between the measured operating characteristic, and Multiple measured operating characteristics Regarding each Based on the time constant, Steps And, it was calculated lag Output each Determine when is lower than a given threshold Steps the predetermined threshold is a function of a plurality of measured operating characteristics and build parameters of the gas turbine system; each Based on Steps The present invention provides a method comprising:

[0007] Exemplary aspects of the present disclosure address the problems and / or concerns described herein. or It is designed to solve other problems that have not been considered.

[0008] These and other features of the present disclosure will be more readily understood from the following detailed description of the various aspects of the disclosure, taken in conjunction with the accompanying drawings which illustrate various embodiments of the present disclosure. [Brief description of the drawings]

[0009] [Figure 1] FIG. 1 is a schematic diagram of a gas turbine system including a control system according to various embodiments of the present disclosure. [Diagram 2] 1 is a stability activation function graph of a lag output of an operating characteristic of a gas turbine system according to an embodiment of the present disclosure. [Diagram 3] FIG. 2 illustrates an example process for detecting thermal stability of the gas turbine system of FIG. 1 in accordance with an embodiment of the present disclosure. [Figure 4] FIG. 2 illustrates an environment including a control system for thermal stability of the gas turbine system of FIG. 1 in accordance with an embodiment of the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0010] It should be noted that the drawings of the present disclosure are not drawn to scale. The drawings are intended to illustrate only typical aspects of the present disclosure and therefore should not be considered as limiting the scope of the present disclosure. In the drawings, like numbers represent like elements between the drawings.

[0011] As a first issue, in order to clearly explain this disclosure, the relevant machines in a combined cycle power plant parts When describing the present invention with reference to the above, it becomes necessary to select specific terminology. In doing so, whenever possible, common industry terminology will be used and utilized in the same manner as its accepted meaning. Unless otherwise indicated, such terminology should be given the broadest interpretation consistent with the context of this application and the scope of the appended claims. Those skilled in the art will often recognize that a particular component may be divided into several different or It will be understood that overlapping terms may be used to refer to the same parts. death What may be obtained may include and be referred to in other contexts as being made up of multiple components. or , as described herein as including multiple components death The obtainable result may be referenced elsewhere as a single part.

[0012] Also, certain descriptive terms may be used repeatedly herein and it should be useful to define these terms at the beginning of this section. These terms and their definitions, unless otherwise stated, are as follows: As used herein, "downstream" and "upstream" refer to the flow of a working fluid through a turbine engine or, for example, the flow of air through a combustor or the flow of a turbine. parts A term indicating a direction relative to the flow of a fluid, such as a coolant, through one of the systems. The term "downstream" corresponds to the direction of the fluid flow, and the term "upstream" refers to the opposite direction of the flow. The terms "forward" and "aft" refer to directions, unless otherwise specified, with "forward" referring to the forward or compressor end of the engine and "aft" referring to the aft or turbine end of the engine. It is often required to describe components at different radial positions relative to a central axis. The term "radial" refers to movement or position perpendicular to the axis. In such cases, if a first component is located closer to the axis than a second component, the first component is said herein to be "radially inward" or "inward" of the second component. On the other hand, if a first component is located farther from the axis than the second component, the first component may be said herein to be "radially outward" or "outward" of the second component. The term "axial" refers to movement or position parallel to the axis. Finally, the term "circumferential" refers to movement or position around the axis. It will be appreciated that such terminology may be applied in relation to the centerline axis of the turbine.

[0013] The above Thus, the present disclosure relates generally to gas turbine systems, and more particularly to a system, program product, and method for detecting thermal stability within a gas turbine system. and It concerns the method.

[0014] These and other embodiments are described below with reference to Figures 1-4. However, those skilled in the art will readily appreciate that the detailed description given herein with respect to these figures is for illustrative purposes only and should not be construed as limiting.

[0015] FIG. 1 illustrates a schematic diagram of a system 10 including a gas turbine system 11 according to various embodiments of the present disclosure. The gas turbine system 11 of the system 10 includes a compressor 12 and a compressor coupled or disposed to the compressor 12. and and / or variable or adjustable inlet guide vanes (IGVs) 18 disposed upstream of an inlet of the compressor 12. The compressor 12 compresses an incoming flow of fluid 20 (e.g., air) that may enter the compressor 12 through the IGVs 18. As described herein, the IGVs 18 may regulate the mass flow rate or flow rate of the fluid 20 as it flows through the IGVs 18 to the compressor 12. The compressor 12 delivers a flow of compressed fluid 22 (e.g., compressed air) to a combustor 24. The combustor 24 mixes the flow of compressed fluid 22 with a pressurized flow of fuel 26 provided by a fuel supply 28 and ignites the mixture to generate a flow of combustion gases 30.

[0016] The flow of combustion gases 30 is then forced through a turbine which typically includes a number of turbine blades (not shown). parts The flow of combustion gas 30 is supplied to a turbine parts 32 to generate mechanical work. Turbine parts The mechanical work produced at 32 drives the compressor 12 via a shaft 34, which can be used to drive a generator 36 (e.g., an external component) configured to generate electrical power and / or generate a load. parts The combustion gases 30 flow through and drive the turbine blades at 32 and exit the turbine through an exhaust housing or exhaust pipe 38. parts 32 and released into the atmosphere, or (Re)used by another system (e.g. steam turbine system) death obtain.

[0017] Although gas turbine system 11 is shown in FIG. 1 as having a single shaft configuration, it should be understood that in other non-limiting examples, gas turbine system 11 may have a dual shaft or rotor configuration.

[0018] As shown in FIG. 1, the system 10 is also operably coupled to a gas turbine system 11. and and / or to detect thermal stability within the gas turbine system 11. and and / or may comprise at least one computing device 100 configured to adjust operating parameters of the gas turbine system 11 based on the detected thermal stability. 1 or more Computing Device vinegar 100 is any suitable electronic communication parts or technology Through this, the gas turbine system 11 and various parts (e.g. Compressor 12, IGV 18 and Turbine parts 32, etc.) and / or Wireless connection and / or This specification As stated in , 1 or more Computing Device vinegar 100 is for detecting when the gas turbine system 11 is thermally stabilized. and / or the operating mechanism of the gas turbine system 11 or parts To determine when the various components of the gas turbine system 11 have been heated to operating temperature (e.g., have been sufficiently heat soaked), parts (not shown for clarity). 1 or more Computing Device vinegar The gas turbine system 100 includes a thermal stability system 102, a control system 104, and a control unit 106, as described herein, for obtaining or measuring operating characteristics of the gas turbine system 11. and A plurality of sensors 106 may be provided. As stated in The thermal stability system 102 is used to detect thermal stability within the gas turbine system 11. deathMeanwhile, the control system 104 controls the gas turbine system 11 and its various power supplies based on the detected thermal stability. parts The operating parameters of the device may be controlled / adjusted.

[0019] System 10 1 or more Computing Device vinegar 100 may include multiple sensors 106 and and / or a plurality of sensors 106. As shown in the non-limiting example of FIG. 1 or more Computing Device vinegar of 100 and / or 1 or more Computing Device vinegar At least one or more sensors 106 (shown in phantom) coupled to 100 measure and sense operating characteristics of the gas turbine system 11 during operation. and / or to obtain a gas turbine system 11 Within or Located in various locations adjacent to the gas turbine system 11 death For this reason, the gas turbine system 11 1 or more Sen sa Location and / or 1 or more Sen sa The type / configuration of 106 may determine the operating characteristic that is measured or detected. For example, one of the sensors 106 may be directly adjacent to the compressor 12. and and / or upstream of the compressor 12, more specifically at the inlet of the compressor 12 with the IGV 18. death In this non-limiting example, the sensor 106 measures and detects the inlet temperature of the fluid 20 flowing to the compressor 12, commonly referred to as the compressor inlet temperature. also may be constructed and / or formed from any suitable sensor. death Additionally or alternatively, in the inlet of the compressor 12 including the IGV 18 and and / or a separate one located directly within the compressor 12 (and downstream of the IGV 18). 1 or more Sen sa 106 is also placed death Obtain, configure death obtain, andand / or any suitable sensor capable of measuring, detecting, or obtaining the compressor inlet temperature based on the fluid 20. death obtain.

[0020] In the non-limiting example shown in FIG. 1 , the computing device 100 may include additional 1 or more Sen sa 106. For example, a plurality of separate 1 or more Sen sa 106 of , Turbine parts 32, generator 36, exhaust pipe 38, compressor 12 / turbine parts 32 and the combustor 24 , and within a supply line (not shown) and shaft 34 (not shown), etc. death These 1 or more Sen sa of 106 each is arranged and / or configured to identify, detect and / or measure additional or distinct operating characteristics of the gas turbine system 11. death The distinct operating characteristics may be different from the compressor inlet temperature based on the fluid 20. In addition, as also described herein, As stated in , the distinct operating characteristics are explicitly used to detect the thermal stability of the gas turbine system 11. death obtain, and / or various gas turbine systems 11 parts Used to determine when a device has been heated and / or maintained at operating temperature (e.g., heat soaked) death The operating characteristics may include, but are not limited to, a discharge temperature of the compressed fluid 22 flowing from the compressor 12, an exhaust temperature of the combustion gases 30 flowing through the exhaust 38, a power output of the gas turbine system 11, for example based on operation of the generator 36, a position (e.g., angle or degree of opening) of the IGV 18, a field stroke reference or fuel flow rate of the gas turbine fuel supplied by the fuel supply 28, and a fuel flow rate of the gas turbine system 11 supplied by the fuel supply 28.

[0021] Although seven sensors 106 are shown, in other non-limiting examples, the system 10 may include: 1 or more Computing Device vinegar 100, and in particular to a thermal stability system 102 and a control system 104, configured to provide information or data related to the operating characteristics of the gas turbine system 11 during operation. death It should be understood that more or fewer sensors 106 may be provided.

[0022] In a non-limiting example, 1 or more Sen sa 106 is a diagram of a gas turbine system 11 in operation 1 or more Operational characteristics sex may be intermittently sensed, detected, and / or acquired data relating to. 1 or more Sen sa The intermittent intervals or periods at which the gas turbine system 11 acquires data may depend, for example, on the operating time of the gas turbine system 11, the operating life of the gas turbine system 11, the operating conditions (e.g., start-up, steady state), and 1 or more Sen sa Determined by the type of data acquired by 106, etc. death In another non-limiting example, 1 or more Sen sa 106 is a diagram of a gas turbine system 11 in operation 1 or more Operational characteristics sex The gas turbine system 11 may continuously sense, detect, and / or obtain data relating to the temperature, humidity, and / or temperature of the gas turbine system 11. Additionally, it should be understood that the sensors 106 shown in the gas turbine system 11 may already be present and included within the gas turbine system 11. As such, it may be possible to determine when the gas turbine system 11 is thermally stable, as described herein. 1 or more Computing Device vinegar It may not be necessary to add new sensors to the gas turbine system 11 for 100 to detect.

[0023] This specification As stated inIn particular, the computing device 100, and more particularly the thermal stability system 102 of the computing device 100, may detect when the gas turbine system 11 is thermally stable. The thermal stability system 102 may be configured to detect when the gas turbine system 11 is thermally stable and / or to monitor the operating mechanics or parts The temperature of the gas turbine system 11 as measured by the sensor 106 of the computing device 100 is determined to be at an operating temperature (e.g., is sufficiently heat soaked). 1 or more Operational characteristics sex To detect thermal stability within the gas turbine system 11, the thermal stability system 102 may utilize the measured operating characteristics in a series of calculations. In one non-limiting example, the thermal stability system 102 may utilize the measured operating characteristics in a series of calculations as described herein. As stated in , a single measured operating characteristic associated with and / or corresponding to a single lag In response to the power output being below a predetermined threshold value of the measured operating characteristic, the gas turbine system 11 may be detected and / or determined to be thermally stable. As stated in The thermal stability system 102 may then determine each and / or all of the thermal stability parameters associated with and / or corresponding to each measured operating characteristic. lag In response to the power output being less than a predetermined threshold value of the measured operating characteristics, the gas turbine system 11 may be detected and / or determined to be thermally stable. That is, the thermal stability of the gas turbine system 11 may be determined in response to the power output being less than a predetermined threshold value of the measured operating characteristics. each All the calculated lag Only when the output falls below a predetermined threshold is it detected by the thermal stability system 102. death obtain.

[0024] In a non-limiting example, when the sensor 106 detects, determines, acquires, and / or measures an operating characteristic of the gas turbine system 11, the thermal stability system 102 may use the measured operating characteristic to For each lag or lag The function can be calculated (hereinafter, lag" or "Calculated lag "). Calculated lag is a measurement of a number of measured operating characteristics and build parameters of the gas turbine system 11 (e.g., compressor / combustor / turbine parts (type / size / model, etc.) each For example, the temperature may be based on a plurality of measured operating characteristics of the gas turbine system 11. Each lag teeth,

number

[0025] Measured operating characteristics Each lag (For example, O.C. lag Once the thermal stability (t) has been calculated, the thermal stability system 102 then calculates the thermal stability (t) of the measured operating characteristics of the gas turbine system 11. Each Calculated lag More specifically, the thermal stability system 102 may determine a difference between the measured operating characteristic and the measured operating characteristic. each and the measured operating characteristics Each Calculated lag In a non-limiting example, the absolute difference between lag The difference is, ΔOC lag =OC measured -OC lag Based on the well, ΔO lag is the absolute difference, and OC measured is the data of the operating characteristic measured by the sensor 106, and OC lag is the measured operating characteristic About Calculated lag It could be.

[0026] Absolute difference (e.g., ΔOC lag ) is calculated, and then the performance of multiple measured characteristics is calculated. Each Final lag output of judgement death More specifically, the thermostability system 102 includes: 1 or more Computing Device vinegar Measured by 100 sensors 106 death Each of the plurality of operating characteristics obtained About lag The output can be determined or calculated. Each Calculated lag The output is the measured operating characteristic. Each Calculated lag and the measured operating characteristics Regarding each The calculated / determined absolute difference between the time constants (e.g., ΔOC lag ), i.e. lag The output is a function of the operating characteristic measured by the sensor 106. each and (e.g., O.C. measured ), the measured operating characteristics Each Calculated lag (For example, O.C. lag ) and Multiple measured operating characteristics Regarding each Time constant (e.g., τ OC ) based on death To this end, a plurality of measured operating characteristics of the gas turbine system (11) are obtained. The lag for each The output is,

number

[0027] By obtaining the calculated output, the thermal stability system 102 is able to detect when the gas turbine system 11 is thermally stable. More specifically, the calculated lag Output (e.g., OC lag ) to 1 or more Computing Device vinegar The thermal stability system 102 of the gas turbine system 100 may determine, detect, and / or identify when the gas turbine system 11 is thermally stable. and / or various gas turbine systems 11 parts The thermal stability system 102 may determine when the thermal stability is at or above the operating temperature. lag Output (e.g., OC lag Thermal stability within the gas turbine system 11 may be determined or detected by comparing the measured operating characteristics measured by the sensors 106 and the build parameters of the gas turbine system 11 (e.g., compressor / combustor / turbine, etc.) to a predetermined threshold. The predetermined threshold may be determined or detected by comparing the measured operating characteristics measured by the sensors 106 and the build parameters of the gas turbine system 11 (e.g., compressor / combustor / turbine, etc.) to a predetermined threshold. parts (type / size / model, etc.) each For example, the predetermined threshold may be based on a number of measured behavior characteristics. each and determining a number of measured operating characteristics based on an operating model of the gas turbine system. each Determine, define and / or calculate death The operating model of the gas turbine system 11 may be the same model as the gas turbine system 11 (e.g., same build parameters, same compressor / combustor / turbine). parts The operational model may be based, at least in part, on an ideal, optimized, unconstrained, and / or “fresh clean system” performance or operation of the gas turbine system 11 (e.g., type). That is, the operational model includes build parameters identical to the build parameters of the gas turbine system 11 for modeling an ideal scenario of operation of the gas turbine system 11. As such, the operational model of the gas turbine system 11 may be used to calculate and / or generate the predetermined thresholds for each of the operating characteristics measured by the sensors 106. death The predetermined thresholds for each of the operating characteristics calculated by the operating model of the gas turbine system 11 are set forth in the specification. As stated in , may provide values ​​of operating characteristics that indicate that the gas turbine system 11 is thermally stable.

[0028] Using predetermined thresholds calculated by the thermal stability system 102 based on an operational model of the gas turbine system 11, the thermal stability system 102 can detect when the gas turbine system 11 is thermally stable. For example, the thermal stability system 102 can detect when the gas turbine system 11 is thermally stable by using a plurality of measured operating characteristics. About Calculated lag Output (e.g., OC lag )of each is lower than a corresponding predetermined threshold; verification (verified) and / or confirmed death All calculated lag Output (e.g., OC lag ) is below a predetermined threshold. That is, the thermal stability system 102 determines that the gas turbine system 11 is thermally stable. lag Output each is lower than a corresponding predetermined threshold, the gas turbine system 11 is thermally stable and / or all of the parts has been heated (e.g., heat soaked) to operating temperature. verification It can be used to verify and / or confirm.

[0029] determining that the gas turbine system 11 is thermally stable; verification Upon verifying and / or confirming, additional processes may be performed on the gas turbine system 11. For example, lag Output each is below a corresponding predetermined threshold and ultimately the gas turbine system 11 is determined to be thermally stable, the operating conditions and / or parameters of the gas turbine system 11 are adjusted. death Specifically, 1 or more Computing Device vinegarThe control system 104 of 100 may adjust operating conditions and / or parameters of the gas turbine system 11 to, for example, increase the power output of the gas turbine system 11. In a non-limiting example, the control system 104 may assist in increasing the power output of the gas turbine system 11 by adjusting the operating speed of the shaft 34 and / or adjusting the position (e.g., operating conditions) of the IGVs 18 to change the amount of fluid 20 introduced and / or compressed by the compressor 12 of the gas turbine system 11. In another ... parts Once it is determined that the gas turbine system 11 has been heated (e.g., heat soaked) to an operating temperature, the computing device 100 may perform additional diagnostic and / or operational monitoring processes on the gas turbine system 11. That is, once it is determined that the gas turbine system 11 is thermally stable, additional measurements and / or calculations of the operational characteristics of the gas turbine system 11 may be performed to determine when the gas turbine system 11 is thermally unstable. death It should be understood that the measurements / calculations may be more accurate and / or precise than those obtained by an operator of the gas turbine system 11. As stated in Based on the detected thermal stability of the system, the operation of the gas turbine system 11 can be more accurately monitored.

[0030] Referring to Figure 2, with continued reference to Figure 1, 1 or more Computing Device vinegar 1 shows a non-limiting example of a stability activation function graph 108 (hereinafter "graph 108") used by the thermal stability system 102 (see FIG. 1) of 100. In the non-limiting example, the graph 108 illustrates how the thermal stability system 102 is able to measure a number of measured operating characteristics. About Calculated lag Output (e.g., OC lag ) was calculated lagThis may represent a non-limiting example of determining when the power output is below a predetermined threshold, which in turn may be converted to an absolute value (e.g., (0,1)) for detecting when the gas turbine system 11 (see FIG. 1 ) is thermally stable. In a non-limiting example, the predetermined threshold 110 may represent a non-limiting example of determining when the power output is below a predetermined threshold, which in turn may be converted to an absolute value (e.g., (0,1)) for detecting when the gas turbine system 11 (see FIG. 1 ) is thermally stable. As stated in , may represent values ​​of operating characteristics that indicate that the gas turbine system 11 is thermally stable. As stated in , Measured Operating Characteristics About Calculated lag Output (e.g., OC lag ) is below a predetermined threshold 110, the thermal stability system 102 may indicate or detect that the gas turbine system 11 is thermally stable.

[0031] 2 , the thermal stability system 102 may also identify a range 112 defined by reference lines 118, 120 of the graph 108. The range 112 may represent measured operating characteristics that may be below a predetermined threshold 110, but may not necessarily ensure and / or guarantee thermal stability within the gas turbine system 11. About Calculated lag Output (e.g., OC lag That is, the range 112 may define a portion of a measured operating characteristic that may be below the predetermined threshold 110 but may not necessarily ensure that the gas turbine system 11 is thermally stable. About Calculated lag Output (e.g., OC lag ) The size and / or value of the range 112 may depend at least in part on information related to the measured operating characteristic and / or the sensor 106 used to measure the operating characteristic. For example, the range 112 may depend at least in part on a predetermined or known uncertainty of the sensor 106. In particular, the sensor 106 may include a predetermined uncertainty, sensitivity, and / or data detection deviation based on operational and / or manufacturing variables. As such, the gas turbine system 11 and 1 or more Computing Device vinegarAn operator or user of 100 may understand that data values ​​associated with the measured operating characteristics may be distorted based on the known uncertainties of the sensors. To ensure that the gas turbine system 11 is thermally stable, the thermal stability system 102 may establish ranges 112 using the predetermined uncertainties of the sensors 106. In a non-limiting example, the measured operating characteristics About Calculated lag Output (e.g., OC lag ) is below a predetermined threshold 110 and outside a range 112, the thermal stability system 102 determines that the gas turbine system 11 is thermally stable and / or that the gas turbine system 11 is in a stable state. parts It may be possible to detect when the sensor has been heated (eg, heat soaked) to an operating temperature.

[0032] 3 shows a flow chart illustrating non-limiting exemplary processes for detecting when the gas turbine system 11 is thermally stable. These processes may be performed, for example, by at least one computing device 100 (see FIG. 1 ) that includes a thermal stability system 102 and a control system 104, as described herein. death In other cases, these processes may be performed according to a computer-implemented method for detecting thermal stability within a gas turbine system 11. death In yet other embodiments, these processes include: 1 or more Computing Device vinegar 100, executes computer program code, 1 or more Computing Device vinegar 100, and in particular by having a thermal stability system 102 and a control system 104 detect when the gas turbine system 11 is thermally stable. death obtain.

[0033] In process P1, 1 or more Operational characteristics sex Calculated by measurement deathMore specifically, a number of operating characteristics of the gas turbine system are measured using a number of sensors disposed adjacent to and / or within the gas turbine system. death The measured operating characteristics include a compressor inlet temperature of a fluid flowing to a compressor of the gas turbine system, a discharge temperature of a compressed fluid flowing from the compressor, an exhaust temperature of a combustion gas flowing through an exhaust pipe of the gas turbine system, e.g. 1 or more Power Generation machine These may include, but are not limited to, the power output of the gas turbine system based on the operation of the IGV, the position (e.g., angle or degree of opening) of the IGV, the field stroke reference of the fuel of the gas turbine supplied by the fuel supply source, and the fuel flow rate of the gas turbine system supplied by the fuel supply source.

[0034] In process P2, for each of the plurality of measured operating characteristics lag That is, for each of the multiple operating characteristics measured in the process P1, lag or lag The function is calculated. lag is a measurement of multiple measured operating characteristics and build parameters of a gas turbine system (e.g., compressor / combustor / turbine parts In addition, the calculated lag is each of a plurality of measured operating characteristics About In a non-limiting example, the time constant of each measured operating characteristic may be based on lag The calculation to determine may be based at least in part on a first-order non-steady-state heat transfer condition used to determine or solve for the temperature in the thermally conductive material. The time constant may be specific to the measured operating characteristic. That is, the time constant for each of the plurality of measured operating characteristics may be specific to the first-order non-steady-state heat transfer condition used to determine or solve for the temperature in the thermally conductive material. lag is calculated using time constants specific and / or corresponding to each measured operating characteristic. death Additionally, the time constant may be specific to the build parameters of the gas turbine system, i.e., the operating characteristics (e.g., compressor inlet temperature) AboutThe time constant may vary from system to system and / or may depend on the build parameters (eg, type, size, model, etc.) from the compressor of the gas turbine system.

[0035] In process P3, lag The difference is determined death More specifically, each of a plurality of measured operating characteristics of the gas turbine system is obtained. lag The difference is determined, calculated and / or identified death obtain. lag The difference is a calculated difference between each of the measured operating characteristics of the gas turbine system. lag (e.g., process P2) and the corresponding measured operating characteristic (e.g., process P1). lag The difference is the difference between each of the measured operating characteristics and the calculated lag It can be the absolute difference between

[0036] In process P4, lag The output is calculated death That is, each of a plurality of measured operating characteristics About lag Output is calculated or judged death The calculated values ​​of each of the measured operating characteristics are obtained. lag The output is a calculated function of each of the measured operating characteristics. lag (e.g., process P3) and each of the measured operating characteristics About It may be based on a calculated / determined (absolute) difference between the time constants, i.e. lag The output is a function of each of the operating characteristics measured by the sensor and a calculated function of each of the measured operating characteristics. lag The difference between and Each of the multiple operating characteristics About Calculated based on time constant death Obtained. lag The difference is, lag To calculate the output, the corresponding operating characteristics About Divide by the time constant Calculation In a non-limiting example, the calculated lagThe output may be the first derivative of each of the inputs of the measured operating characteristic (eg, process P2).

[0037] In process P5, the calculated lag Determine whether the output (e.g., process P4) is lower than a predetermined threshold death Specifically, each calculated lag The calculated output of each of the plurality of measured operating characteristics is compared to a predetermined threshold. lag It is determined whether the output is lower than a corresponding predetermined threshold. death The predetermined threshold is determined based on a plurality of measured operating characteristics measured by sensors in process P1 and build parameters of the gas turbine system (e.g., compressor / combustor / turbine). parts For example, the predetermined threshold may be specific to each of the plurality of measured operating characteristics and may be determined, defined, and / or calculated for each of the plurality of measured operating characteristics based on an operational model of the gas turbine system. death The operational model includes build parameters identical to the build parameters of the gas turbine system for modeling an ideal scenario of operation of the gas turbine system, and thus the operational model of the gas turbine system may be used to calculate and / or generate the predetermined thresholds for each of the measured operating characteristics. death The predetermined thresholds for each of the operating characteristics are as set forth herein. As stated in , may provide values ​​of operating characteristics that indicate that the gas turbine system is thermally stable.

[0038] Each of the plurality of measured operating characteristics and / or a calculated lag In response to determining that the threshold value is not lower than the corresponding predetermined threshold value (e.g., "No" in P5), the processes P1 to P5 are repeated. death That is, each of the measured operating characteristics and / or a calculated lag is not lower than the corresponding predetermined threshold (e.g., “No” in P5), the gas turbine system is deemed thermally stable. verification (e.g., Process P6) and the gas turbine system is thermally stable. verification Processes P1 to P5 are repeated until death obtain.

[0039] However, the calculated values ​​of each of the multiple measured operating characteristics lag is lower than a corresponding predetermined threshold (e.g., “yes” in P5), process P6 determines that the gas turbine system is thermally stable. Verify That is, in process P6, the calculated lag determining that the gas turbine system is thermally stable in response to each of the outputs being lower than a corresponding predetermined threshold; verification It can be verified or confirmed that the gas turbine system is thermally stable. verification This also means that all the components of the gas turbine system parts has been heated (e.g., heat soaked) to an operating temperature.

[0040] In process P6, the gas turbine system is thermally stable. verification After the calculation, additional processes can be performed on the thermally stable gas turbine system. For example, lag Each of the outputs is determined to be lower than a corresponding predetermined threshold, and finally, the gas turbine system is determined to be thermally stable. verification In response to the above, the operating conditions and / or parameters of the gas turbine system are adjusted in process P7. death In particular, the operating conditions and / or parameters of the gas turbine system may be adjusted, for example, to increase the power output of the gas turbine system. deathIn a non-limiting example, the power output of the gas turbine system 11 may be increased by adjusting the operating speed of the shaft 34 and / or adjusting the position of the IGVs (e.g., operating conditions) in the gas turbine system to change the amount of fluid introduced and / or compressed by the compressor of the system.

[0041] In another non-limiting example, a gas turbine system may be thermally stable and / or may include parts is heated to operating temperature (e.g., heat soaked) verification Once the diagnostic and / or operational monitoring processes have been performed (e.g., process P6), additional diagnostic and / or operational monitoring processes may be performed on the gas turbine system. death In other words, the gas turbine system is thermally stable. verification Once this is done, additional measurements and / or calculations of the operating characteristics of the gas turbine system may be performed to determine when the gas turbine system is thermally unstable (e.g., during start-up). death It should be appreciated that the thermal stability may be more accurate and / or precise than measurements / calculations obtained from the gas turbine system, and thus an operator of the gas turbine system may perform additional diagnostic and / or operational monitoring processes on the gas turbine system to more accurately monitor the operation of the system based on the detected thermal stability.

[0042] In addition, as shown in FIG. 3, processes P1 to P6 may be performed continuously and / or in a predetermined cycle. death It should be understood that the processes P1 to P6 can be used to constantly or intermittently grasp the thermal stability of the gas turbine system during operation. death Continuously and / or in predetermined cycles to obtain death Therefore, the calculated lag It is determined that the output is lower than a predetermined threshold (e.g., “Yes” in process P5), and the gas turbine system is thermally stable. verification Even if a thermally stable gas turbine system is replaced (e.g., process P6), processes P1 to P6 ensure that the gas turbine system is still thermally stable and / or remains thermally stable. verificationTo continue, the program must then be executed again, either immediately or after a predefined period of time. death obtain.

[0043] It will be understood that other processes or operations not shown in the flowcharts shown and described herein may be performed. The order of the processes may also be rearranged according to various embodiments. For example, although shown as being performed sequentially, processes P6 and P7 may be performed simultaneously. Further, As stated in Processes P1-P7 may be sequentially performed in order to improve operation of the gas turbine system and / or to assist in detecting or determining thermal stability within the gas turbine system. death and / or process P1 may be executed continuously or intermittently, independently of the execution of other processes. death The process flows shown and described herein should not be considered as limitations to the various embodiments.

[0044] 4 illustrates an exemplary environment in which the various process steps described herein may be performed to detect thermal stability within a gas turbine system 11. 1 or more Computing Device vinegar In particular, 1 or more Computing Device vinegar 100 is shown to include a thermal stability system 102 and a control system 104 that enable computing device 100 to detect thermal stability within gas turbine system 11 and control operation and / or adjust operating conditions of gas turbine system 11 by performing one or more of the process steps of the present disclosure.

[0045] Storage parts 146, Processing parts 148, Input / Output (I / O) parts 150 and bus 152 1 or more Computing Device vinegar 100 is shown. Furthermore, 1 or more Computing Device vinegar 100 is shown in communication with the gas turbine system 11 and / or sensors 106. As is known in the art, generally, parts 148 is storage parts 146 or external storage parts The thermal stability system 102 and the control system 104 execute computer program code stored in a processor (not shown). parts 148 stores data for the thermal stability system 102 and the control system 104 while executing the computer program code. parts 146 and / or I / O parts 150. Bus 152 can read from and / or write to 1 or more Computing Device vinegar of 100 parts Provides a communication link between each of the I / O parts 150 is 1 or more You The 153 1 or more Computing Device vinegar Any device that allows interaction with 100, or 1 or more Computing Device vinegar Any device that enables 100 to communicate with one or more other computing devices may be included. Input / output devices (including but not limited to keyboards, displays, pointing devices, etc.) may be coupled to the system either directly or through intervening I / O controllers.

[0046] Either way, 1 or more Computing Device vinegar 100 may include any general-purpose computing product (e.g., a personal computer, a server, a handheld device, etc.) capable of executing computer program code installed by a user 153. However, 1 or more Computing Device vinegarIt will be understood that 100 and thermal stability system 102 / control system 104 are merely representative of various possible equivalent computing devices capable of performing the various process steps of the present disclosure. 1 or more Computing Device vinegar 100 may comprise any special purpose computing product including hardware and / or computer program code for performing particular functions, any computing product including a combination of special purpose and general purpose hardware / software, etc. In either case, the program code and hardware, respectively, may be created using standard programming and engineering techniques.

[0047] Similarly, 1 or more Computing Device vinegar 100 is merely illustrative of various types of computer infrastructure for implementing the present disclosure. For example, in one embodiment: 1 or more Computing Device vinegar 100 comprises two or more computing devices (e.g., a server cluster) communicating via any type of wired and / or wireless communication link, such as a network, shared memory, etc., to perform various process steps of the present disclosure. When the communication link comprises a network, the network can include any combination of one or more types of networks (e.g., the Internet, a wide area network, a local area network, a virtual private network, etc.). Network adapters can also be coupled to the system such that the data processing system can be coupled to other data processing systems or remote printers or storage devices via intervening private or public networks. Modems, cable modems, and Ethernet cards are just a few of the currently available types of network adapters. Regardless, communication between the computing devices can utilize any combination of various types of transmission technologies.

[0048] As previously described and discussed herein, the thermal stability system 102 determines when the gas turbine system 11 is thermally stable. 1 or more Computing Device vinegar While enabling 100 to detect, the control system 104 1 or more Computing Device vinegar 100 enables the gas turbine system 11 to control operation and / or adjust operating conditions. To this end, the thermal stability system 102 and the control system 104 each receive measured operating characteristic data 154, predetermined threshold data 156, lag , lag difference, and lag Includes calculations related to outputs lag Calculation data 158, operating condition data 160, and 4. The operation of each of these data is described further herein. However, some of the various data shown in FIG. 4 may be implemented independently, combined and / or 1 or more Computing Device vinegar 100. Stored in memory for one or more separate computing devices. death It is understood that some of the data and / or functions may not be implemented. or Additional data and / or features 1 or more Computing Device vinegar It should be understood that this may be included as a fraction of 100.

[0049] The flowcharts and block diagrams in the Figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present disclosure. In this regard, each block in the flowcharts or block diagrams may represent a module, segment, or portion of code, which may include: A given 1 or more Logic Machine NohIt should also be noted that in some alternative implementations, the functions described in the blocks may occur out of the order described in the figures. For example, two blocks shown in succession may in fact be executed substantially simultaneously or may sometimes be executed in the reverse order, depending on the functionality involved in the blocks. Each block in the block diagrams and / or flowchart diagrams, and The combination of blocks in the block diagram and / or flow chart is Prescribed It should also be noted that the functions or operations may be implemented by dedicated hardware-based systems, or a combination of dedicated hardware and computer instructions.

[0050] This specification As stated in ,Various systems and components "acquire" data (e.g., 1 or more Operational characteristics sex It is understood that the corresponding data can be obtained using any solution. For example, a corresponding system / parts The system generates data and / or is used to generate data, retrieve data from one or more data stores (e.g., databases), and / or transmit data to another system / parts It is possible to receive data from a specific system / parts When no data is generated by the illustrated system / parts In addition, data is generated and parts and / or systems / parts another system / parts It will be appreciated that the following may be implemented:

[0051] As will be appreciated by those skilled in the art, the present disclosure may be embodied as a system, method, or computer program product. Accordingly, the present disclosure may take the form of an entirely hardware embodiment, an entirely software embodiment (including firmware, resident software, microcode, etc.), or an embodiment combining software and hardware aspects, which may all be generally referred to herein as "circuits," "modules," and / or "systems." Furthermore, the present disclosure may take the form of a computer program product embodied in any tangible medium of expression having computer usable program code embodied in the medium.

[0052] Any combination of one or more computer usable or computer readable media may be utilized. The computer usable or computer readable medium may be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, device, or propagation medium. More specific examples (non-exhaustive list) of computer readable media include an electrical connection having one or more wires, a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a transmission medium such as a medium supporting the Internet or an intranet, or the like, or a magnetic storage device. It is noted that the computer usable or computer readable medium may be paper or another suitable medium on which the program is printed, and the program may be captured electronically, for example, via optical scanning of the paper or other medium, and then compiled, interpreted, or processed in an appropriate manner, as required, and then stored in a computer memory. In the context of this specification, a computer usable medium or computer readable medium may be any medium that can contain, store, communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. The computer usable medium may include a propagated data signal with the computer usable program code embodied in baseband or as part of a carrier wave. The computer usable program code may be transmitted using any suitable medium, including but not limited to wireless, wired, fiber optic cable, RF, etc.

[0053] Computer program code for carrying out the operations of the present disclosure may be written in any combination of one or more programming languages, including object-oriented programming languages ​​such as Java, Smalltalk, C++, and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The program code may run entirely on the user's computer, partially on the user's computer, as a separate software package, partially on the user's computer, partially on a remote computer, or entirely on a remote computer or server. In the latter scenario, the remote computer may be connected to the user's computer via any type of network, including a Local Area Network (LAN) or a Wide Area Network (WAN), or , may be connected to an external computer (eg, via the Internet using an Internet Service Provider).

[0054] The present disclosure is described herein with reference to flowchart and / or block diagrams of methods, apparatus (systems) and computer program products according to embodiments of the present disclosure. and It will be understood that combinations of blocks in the flowcharts and / or block diagrams can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general purpose computer, special purpose computer, or other programmable data processing apparatus to produce a machine, such that the instructions, executed by the processor of the computer or other programmable data processing apparatus, represent a block or blocks of the flowcharts and / or block diagrams. Prescribed Provides a means for performing a function / operation.

[0055] These computer program instructions may also be stored on a computer-readable medium that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored on the computer-readable medium produce an article of manufacture that includes instruction means that implement the function / act specified in the block or blocks of the flowcharts and / or block diagrams.

[0056] The computer program instructions may also be loaded into a computer or other programmable data processing apparatus to cause the computer or other programmable apparatus to perform a series of operational steps to generate a computer-implemented process, whereby the instructions executed on the computer or other programmable apparatus provide a process for implementing the function / operation specified in the block or blocks of the flowcharts and / or block diagrams.

[0057] The technical effect is to provide a system, program product, and method for detecting when a gas turbine system is thermally stable. In particular, the system may use measured operating characteristics of the gas turbine system to detect thermal stability of the gas turbine system. and / or various gas turbine systems parts Used to determine when a device has been heated and / or maintained at operating temperature (e.g., heat soaked) death Being able to determine when the gas turbine system is thermally stable allows an operator to obtain accurate performance information for the gas turbine system and / or adjust operating characteristics or parameters to improve the efficiency of the gas turbine system (e.g., increase power output).

[0058] The terminology used herein is merely for the purpose of describing particular embodiments and is not intended to limit the disclosure. As used herein, the singular forms "a", "an" and "the" are intended to include the plural unless otherwise indicated. It will be further understood that the terms "comprise" and / or "comprising" as used herein specify the presence of stated features, integers, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or sets thereof. "Optional" or "optionally" means that the subsequently described event or circumstance may or may not occur, and the description includes instances in which the event occurs and instances in which it does not occur.

[0059] As used herein throughout the specification and claims, approximation language can be applied to modify any quantitative expression that can reasonably be varied without resulting in a change in the basic function to which it pertains. Thus, values ​​modified by terms such as "approximately," "about," and "substantially" are not limited to the exact value stated. In at least some instances, approximation language can correspond to the precision of an instrument for measuring the value. Here, and Throughout this specification and claims, range limitations are combinable and / or interchangeable, and such ranges are specified and include all subranges subsumed therein, unless the context and language dictate otherwise. "About" as applied to a particular value in a range applies to both values ​​and can indicate + / - 10% of the stated value, unless specifically relied upon the precision of the instrument measuring the value.

[0060] The corresponding structures, materials, acts, and equivalents of all means-plus-function or step-plus-function elements in the appended claims are intended to encompass any structures, materials, or acts to perform that function in combination with other specifically claimed claim elements. The description of the present disclosure has been presented for purposes of illustration and description, and is not intended to be exhaustive or to limit the disclosure to the disclosed form. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the disclosure. The present embodiment has been chosen and described in order to best explain the principles and practical application of the disclosure, and to enable others skilled in the art to understand the disclosure in its various embodiments with various modifications as appropriate for the particular use envisaged. [Explanation of symbols]

[0061] 10. System 11 Gas Turbine Systems 12 Compressor 18 Inlet guide vane (IGV) 20 fluid 22 Compressed Fluids 24 Combustor 26 Fuel 28 Fuel supply source 30 Combustion Gas 32 Turbine parts 34 Shaft 36 Generator 38 Exhaust pipe 100 computing devices 102 Thermostable Systems 104 Control System 106 Sensors 108 Graphs 110 Predetermined Threshold 112 Range 118, 120 Reference line 146 Storage parts 148 Processing parts 150 Input / Output (I / O) parts 152 Bus 153 users 154 Operating characteristic data 156 Predetermined Threshold Data 158 lag Calculated Data 160 Operating Condition Data 162 Diagnostic Data

Claims

1. A system (10) comprising at least one computing device (100) in communication with a gas turbine system (11) and a plurality of sensors (106), comprising: the gas turbine system (11) includes a compressor (12), a combustor (24) and a turbine component (32); at least one of the plurality of sensors (106) is disposed within or adjacent to the gas turbine system (11), and each sensor (106) of the plurality of sensors (106) measures one of a plurality of operating characteristics of the gas turbine system (11); The at least one computing device (100): calculating a lag output for each of the plurality of measured behavior characteristics, the calculated lag output comprising: a difference between the calculated lag for the measured operating characteristic of the gas turbine system (11) and the measured operating characteristic; and a time constant for each of said plurality of measured operating characteristics; and determining when each of the calculated lag outputs is below a predetermined threshold (110), the predetermined threshold (110) being based on each of the plurality of measured operating characteristics and build parameters of the gas turbine system (11); and wherein the build parameters are configured to detect thermal stability within the gas turbine system by executing a process comprising: a) at least one of the type, size, and model of the compressor (12); b) at least one of the type, size, and model of the combustor (24); c) at least one of the type, size, and model of said turbine component (32). Contains The lag for each of the plurality of measured operating characteristics of the gas turbine system (11) is [0010] It is calculated based on t is a first time period; t-1 is a second time that occurs before the first time t; OC lag (t) is the calculated lag for the operating characteristic measured at time t; OC lag (t−1) is the calculated lag for the operating characteristic measured at time t−1; OC measured (t-1) is the operating characteristic measured at time t-1; Δt is the difference between the first time and the second time, τ OC is the time constant for the measured operating characteristic; System (10).

2. The process executed by the at least one computing device (100) for detecting thermal stability within the gas turbine system (11) comprises: and verifying that the gas turbine system (11) is thermally stable in response to each of the calculated lag powers for each of the plurality of measured operating characteristics being less than the corresponding predetermined threshold (110). The system (10) of claim 1 further comprising:

3. The plurality of measured operating characteristics comprises: Compressor (12) inlet temperature, Compressor (12) discharge temperature; the exhaust temperature of the gas turbine system (11); a power output of the gas turbine system (11); Inlet guide vane position, A field stroke criterion for the fuel (26) of the gas turbine system (11); and Fuel (26) flow rate of the gas turbine system (11) The system (10) of claim 1, wherein the system (10) is selected from the group consisting of:

4. The lag output for each of the plurality of measured operating characteristics of the gas turbine system (11) is [0025] It is calculated based on O.C. ｌａｇ is the calculated lag output, ΔOC ｌａｇ is the determined lag difference, τ ＯＣ The system of claim 1 , wherein: x is the time constant of the measured operating characteristic.

5. The process executed by the at least one computing device (100) for detecting thermal stability within the gas turbine system (11) comprises: adjusting operating conditions of the gas turbine system (11) to increase a power output of the gas turbine system (11) in response to determining that each of the calculated lag outputs is lower than a corresponding predetermined threshold (110). The system (10) of claim 1 further comprising:

6. The process executed by the at least one computing device (100) for detecting thermal stability within the gas turbine system (11) comprises: calculating the predetermined thresholds (110) for each of the plurality of measured operating characteristics based on an operating model of the gas turbine system (11); 2. The system (10) of claim 1, further comprising: wherein the operational model of the gas turbine system (11) includes build parameters identical to the build parameters of the gas turbine system (11).

7. The system (10) of claim 1, wherein the time constant is specific to each of the plurality of measured operating characteristics and the build parameters of the gas turbine system (11).

8. A method for detecting thermal stability in a gas turbine system (11) including a compressor (12), a combustor (24), and a turbine component (32), the method comprising: calculating a lag output for each of a plurality of measured operating characteristics of the gas turbine system (11) measured by a plurality of sensors (106) located at least one of within or adjacent to the gas turbine system (11), the calculated lag outputs comprising: a difference between the calculated lag for the measured operating characteristic of the gas turbine system (11) and the measured operating characteristic; and a time constant for each of said plurality of measured operating characteristics; and determining when each of the calculated lag outputs is below a predetermined threshold (110), the predetermined threshold (110) being based on each of the plurality of measured operating characteristics and build parameters of the gas turbine system (11); and the build parameters include a) at least one of the type, size, and model of the compressor (12); b) at least one of the type, size, and model of the combustor (24); c) at least one of the type, size, and model of said turbine component (32). Contains The lag for each of the plurality of measured operating characteristics of the gas turbine system (11) is [0030] It is calculated based on t is a first time period; t-1 is a second time that occurs before the first time t; OC lag (t) is the calculated lag for the operating characteristic measured at time t; OC lag (t−1) is the calculated lag for the operating characteristic measured at time t−1; OC measured (t-1) is the operating characteristic measured at time t-1; Δt is the difference between the first time and the second time, τ OC is the time constant for the measured operating characteristic; method.

9. and verifying that the gas turbine system (11) is thermally stable in response to each of the calculated lag powers for each of the plurality of measured operating characteristics being less than the corresponding predetermined threshold (110). The method of claim 8 further comprising:

10. adjusting operating conditions of the gas turbine system (11) to increase a power output of the gas turbine system (11) in response to determining that each of the calculated lag outputs is lower than a corresponding predetermined threshold (110). The method of claim 8 further comprising:

11. calculating the predetermined thresholds (110) for each of the plurality of measured operating characteristics based on an operating model of the gas turbine system (11); and wherein the operational model of the gas turbine system (11) includes build parameters identical to the build parameters of the gas turbine system (11).

12. The method of claim 11 , wherein the time constant is specific to each of the plurality of measured operating characteristics and the build parameters of the gas turbine system (11 ).

13. The lag output of each of the plurality of measured operating characteristics of the gas turbine system (11) is [0045] It is calculated based on O.C. ｌａｇ is the calculated lag output, ΔOC ｌａｇ is the determined lag difference, τ ＯＣ The method of claim 8 , wherein: is the time constant of the measured operating characteristic.

Images