Gas turbine mass difference determination system and method

Abstract

A method for determining a mass discrepancy in a hot gas path component of a gas turbine (13) includes monitoring operating conditions of the gas turbine (13), determining whether a wheel space (51) temperature of the gas turbine (13) has changed, determining whether the change in the wheel space (51) temperature is indicative of a change in temperature by comparing the wheel space (51) temperature to at least one of a compressor (11) inlet temperature and a compressor (11) discharge temperature, determining, in response to determining that the wheel space (51) temperature is indicative of a change in temperature has occurred, whether at least one of a gas turbine (13) exhaust temperature is indicative of a simultaneous change in the temperature change as compared to the wheel space (51) temperature and the at least one of the compressor (11) inlet temperature and the compressor (11) discharge temperature, and a gas turbine (13) vibration change. In response to at least one of the simultaneous change and the vibration change being present, a mass deviation in the hot gas path component of the gas turbine (13) is indicated.

Description

Background Technology

[0001] This disclosure generally relates to systems and methods for determining mass changes or differences in a gas turbine. Specifically, this disclosure relates to systems and methods for determining mass changes or differences in hot gas path components of a gas turbine.

[0002] Detecting mass variations in gas turbine components (including, but not limited to, the hot gas path components of a gas turbine) when these variations are minor and alerted is useful for preventing substantial mass changes associated with missile incidents, blade failures and releases, and fatigue. The realization and detection of small mass variations during gas turbine monitoring can alert gas turbine operators to the potential for impending failure. Therefore, monitoring mass variations associated with causes such as corrosion, cracking, spalling, scaling, accumulation of emission particles, and other such causes can reduce further damage to gas turbine components. Summary of the Invention

[0003] A first aspect of this disclosure provides a method for determining mass variations in a hot gas path component of a gas turbine, comprising: monitoring operating conditions of the gas turbine; determining whether a change has occurred in the gas turbine impeller space temperature; indicating a temperature change by comparing the impeller space temperature with at least one of a compressor inlet temperature and a compressor discharge temperature; in response to determining that a temperature change has occurred, indicating that a temperature change has occurred; and determining whether at least one of the following exists: a simultaneous change in the gas turbine discharge temperature indication and a temperature change in the impeller space temperature compared with at least one of the compressor inlet temperature and compressor discharge temperature, and a change in gas turbine vibration. In response to the presence of at least one of the simultaneous change and the vibration change, a mass deviation in the hot gas path component of the gas turbine is indicated.

[0004] A second aspect of this disclosure provides a gas turbine control device for a gas turbine that monitors and determines mass variations in the hot gas path components of the gas turbine. The control device includes at least one sensor for monitoring gas turbine operating conditions, the at least one sensor monitoring one or more of shaft speed, gas turbine load, impeller space temperature, vibration, gas turbine exhaust temperature, compressor inlet temperature, and compressor discharge temperature; and a non-transitory computer-readable medium including computer-executable instructions for operating the gas turbine, the instructions including instructions for performing the following operations: monitoring gas turbine parameters and operating conditions; determining whether the gas turbine impeller space temperature has changed; determining whether the impeller space temperature indicates a temperature change; determining whether the impeller space temperature indicates a temperature change has occurred; and then determining whether at least one of the following exists: the gas turbine exhaust temperature indicates a simultaneous change with a temperature change compared to at least one of the impeller space temperature and the compressor inlet temperature and compressor discharge temperature; and a gas turbine vibration change. In response to the presence of at least one of the simultaneous change and the vibration change, a mass deviation in the hot gas path components of the gas turbine is indicated.

[0005] The exemplary aspects of this disclosure are designed to address the problems described herein and / or other problems not discussed herein. Attached Figure Description

[0006] These and other features of the present disclosure will be more readily understood from the following detailed description of various aspects of the present disclosure in conjunction with the accompanying drawings depicting various embodiments thereof, wherein:

[0007] Figure 1 This is a schematic diagram of an exemplary combustion gas turbine engine, as illustrated in this disclosure, in which embodiments of the present application can be used;

[0008] Figure 2 For as set forth in this disclosure Figure 1 A cross-sectional view of the compressor in a combustion gas turbine engine;

[0009] Figure 3 For as set forth in this disclosure Figure 1 A cross-sectional view of the gas turbine in a combustion gas turbine engine;

[0010] Figure 4 A flowchart illustrating one aspect of the process as embodied in this disclosure is shown; and

[0011] Figure 5 An exemplary control device and associated computer for determining mass differences in the hot gas path components of a gas turbine are shown, including monitoring parameters and operating conditions of the gas turbine.

[0012] It should be noted that the accompanying drawings of this disclosure are not drawn to scale. The drawings are intended to depict only typical aspects of this disclosure and therefore should not be considered as limiting the scope of this disclosure. In the drawings, similar numbers denote similar elements between the figures. Detailed Implementation

[0013] First, in order to clearly describe the present technology, it will be necessary to select certain terms when referring to and describing relevant machine components within, and specifically, the hot gas path portion of, a gas turbine. To the extent possible, common industry terms will be used and adopted in a manner consistent with their accepted meaning. Unless otherwise stated, such terms should be given a broad interpretation consistent with the context of this application and the scope of the appended claims. Those skilled in the art will understand that several different or overlapping terms may generally be used to refer to a particular component. An object that can be described herein as a single part may include multiple components and is referred to in another context as being composed of multiple components. Alternatively, an object that can be described herein as comprising multiple components may elsewhere be referred to as a single part.

[0014] In addition, several descriptive terms may be used periodically throughout this document, and it should prove helpful to define these terms at the beginning of this section. Unless otherwise stated, these terms and their definitions are as follows. As used herein, “downstream” and “upstream” are terms indicating the direction of fluid flow, such as the working fluid of a gas turbine engine, or, for example, the airflow through a combustor or the coolant through one of the component systems of a gas turbine. The term “downstream” corresponds to the direction of fluid flow, and the term “upstream” refers to the direction opposite to the flow. Without any other particularity, the terms “front” and “rear” refer to directions, where “front” refers to the front end of the engine or the compressor end, and “rear” refers to the rear end of the engine or the gas turbine end.

[0015] It is often necessary to describe parts positioned at different radial locations relative to a central axis. The term "radial" refers to movement or position perpendicular to the axis. For example, if a first part is closer to the axis than a second part, this document will describe the first part as "radially inward" or "inner" of the second part. On the other hand, if the first part resides further away from the axis than the second part, this document may describe the first part as "radially outward" or "outer" of the second part. The term "axial" refers to movement or position parallel to the axis. Finally, the term "circumferential" refers to movement or position about the axis. It should be understood that such terms can be applied relative to the central axis of a gas turbine.

[0016] In addition, several descriptive terms may be used regularly in this document, as described below. The terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of a single component.

[0017] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that, when used in the specification, the terms “comprising” and / or “including” specify the presence of the 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 groups thereof. “Optional” or “optionally” means that an event or condition subsequently described may or may not occur, and the description includes instances where the event occurs and instances where the event does not occur.

[0018] When an element or layer is referred to as “on,” “joined to,” “connected to,” or “linked to” another element or layer, it may be directly on, joined to, connected to, or linked to another element or layer, or an intermediary element or layer may be present. In contrast, when an element is referred to as “directly on another element or layer,” “directly joined to another element or layer,” “directly connected to another element or layer,” or “directly linked to another element or layer,” an intermediary element or layer may not be present. Other terms used to describe relationships between elements should be interpreted in a similar manner (e.g., “between” vs. “directly between,” “adjacent” vs. “directly adjacent,” etc.). As used herein, the term “and / or” includes any and all combinations of one or more of the associated listed items.

[0019] For background information, please now refer to the attached diagram. Figures 1 to 3 An exemplary combustion gas turbine engine in which embodiments of this application can be used is shown. Those skilled in the art will understand that this embodiment is not limited to this type of application. As mentioned above, this embodiment can be used in combustion gas turbine engines, such as engines for power generation and aircraft, steam gas turbine engines, and other types of rotary engines.

[0020] Figure 1An exemplary combustion gas turbine engine is shown, in which embodiments of this application can be used. Those skilled in the art will understand that this embodiment is not limited to this type of combustion gas turbine engine. As mentioned above, this embodiment can be used in combustion gas turbine engines, such as, but not limited to, engines for power generation and aircraft, steam gas turbine engines, and other types of rotary engines. Generally speaking, combustion gas turbine engines operate by extracting energy from the pressurized hot gas stream generated by the combustion of fuel in a compressed air stream. Figure 1 As shown, the combustion gas turbine engine system 10 can be configured to have an axial compressor 11 mechanically connected via a common shaft or rotor to a downstream gas turbine section or combustion gas turbine engine 13 (hereinafter “gas turbine”), and a combustor 12 disposed between the compressor 11 and the gas turbine 13.

[0021] Figure 2 It shows that it can be used Figure 1 An illustrative, non-limiting view of a multi-tray axial compressor 11 with a gas turbine 13 is shown. As illustrated, the compressor 11 may include multiple trays. Each tray may include a row of compressor rotor blades 14, followed by a row of compressor stator nozzles 15. Thus, a first tray may include a row of compressor rotor blades 14 that rotates about a central axis, followed by a row of compressor stator nozzles 15 that remain stationary during operation. The compressor stator nozzles 15 are generally circumferentially spaced from each other and stationary about the axis of rotation. The compressor rotor blades 14 are circumferentially spaced and attached to the shaft. As the shaft rotates during operation, the compressor rotor blades 14 rotate with it. The compressor rotor blades 14 are configured such that, when rotated about the shaft, they impart kinetic energy to air or fluid flowing through the compressor 11. The compressor 11 may have a... Figure 2 Other trays besides the tray shown. Additional trays may include a plurality of circumferentially spaced compressor rotor blades 14, followed by a plurality of circumferentially spaced compressor stator nozzles 15.

[0022] Figure 3 It shows what can be used for Figure 1A non-limiting partial view of an exemplary gas turbine section or gas turbine 13 of a combustion gas turbine engine. The gas turbine 13 may also include multiple towers. Three exemplary gas turbine towers are shown, but this is merely illustrative and non-limiting, and is not intended to limit the embodiment in any way. Therefore, more or fewer gas turbine towers may be present in the gas turbine 13. A first gas turbine tower includes a plurality of gas turbine blades or gas turbine rotor blades 16 (hereinafter “blades”) that rotate about a shaft during operation, and a plurality of nozzles or gas turbine stator blades 17 (hereinafter “nozzles”) that remain stationary during operation. The nozzles 17 are generally circumferentially spaced from each other and fixed about the axis of rotation. The gas turbine rotor blades 16 may be mounted on a gas turbine impeller or disk (not shown) to rotate together with the gas turbine shaft 50. A second tower of the gas turbine 13 is also shown. The second gas turbine tower similarly includes a plurality of circumferentially spaced nozzles 17, followed by a plurality of circumferentially spaced gas turbine rotor blades 16, which are also mounted on the gas turbine impeller for rotation. A third gas turbine tray is also shown, and similarly includes multiple nozzles 17 and rotor blades 16. It should be understood that the gas turbine nozzles 17 and rotor blades 16 are located in the hot gas path of the gas turbine 13. The flow direction of the hot gas through the gas turbine hot gas path is indicated by arrows. The gas turbine 13 may have... Figure 3 Other trays besides the tray shown. Each additional gas turbine tray may include a row of gas turbine nozzles 17, followed by a row of gas turbine rotor blades 16.

[0023] In the non-limiting description used, the compressor rotor blades 14 rotate within the axial compressor 11 to compress the airflow. In the burner 12, energy is released when compressed air is mixed with fuel and ignited. The resulting hot gas flow from the burner 12 (which may be referred to as the working fluid) is then directed over the gas turbine rotor blades 16, causing the gas turbine rotor blades 16 and the shaft 50 to rotate. Thus, the energy of the working fluid flow is converted into the mechanical energy of the rotating blades, and the shaft 50 rotates due to the connection between the rotor blades and the shaft. The mechanical energy of the shaft 50 can then be used to drive the rotation of the compressor rotor blades 14, thereby generating the necessary compressed air supply, and also, for example, driving a generator to produce electricity.

[0024] The operation of the gas turbine can be monitored by several sensors 26, which detect various operating conditions of the gas turbine, generator and power plant facilities, including those conditions of the surrounding environment of the gas turbine. Figure 1Various locations where sensor 26 can be positioned to determine various parameters and operating conditions are shown. As embodied in this disclosure, these locations are not intended to limit the implementation in any way, and sensor 26 can be positioned at any location now known or determined below in the gas turbine 13 or gas turbine system that would make it possible to determine parameters and operating conditions.

[0025] As embodied in this disclosure, at least one sensor 26 is positioned on, in, or in communication with the impeller space 51 to determine the impeller space temperature (WS Temp). In one aspect of the embodiment, multiple sensors 26 may be positioned in the same impeller space 51. Multiple sensors 26 positioned in the same impeller space 51 are radially spaced to provide multiple impeller space temperatures (WS Temp).

[0026] In addition, WS Temp will be evaluated to determine any mass variation (increase or decrease) in the hot gas path components. Furthermore, as embodied in this disclosure, other sensors 26 may be provided to determine various parameters and operating conditions of the gas turbine, which may also be evaluated to determine any mass variation (increase or decrease) in the hot gas path components. These conditions include, but are not limited to, shaft speed (TNH), load (DWATT), shaft vibration, gas turbine exhaust temperature (TTXM), bearing vibration, gas turbine total power and efficiency variations, and compressor inlet and exhaust temperatures (CTIM and CTD, respectively), as well as any other gas turbine parameters and operating conditions now known or identified below as necessary for gas turbine operation monitoring.

[0027] As embodied in this disclosure, temperature sensor 26 can monitor the ambient temperature around gas turbine 13, compressor discharge temperature, gas turbine exhaust temperature, and other temperature measurements of the gas flow through gas turbine 13.

[0028] Sensor 26 may also include flow sensors, speed sensors, rotor (or shaft) vibration sensors, flame detector sensors, valve position sensors, guide vane angle sensors, etc., that sense various parameters related to the operation of gas turbine 13. As used herein, operating conditions refer to the items that can be used to define the gas turbine, such as temperature, pressure, and flow rate at a defined location in the gas turbine that can be used to represent a given gas turbine operating condition.

[0029] One aspect of this embodiment includes detecting an increase or decrease in the mass of a gas turbine hot gas path section component. As embodied in this disclosure, detection can be due to a decrease resulting from a release and / or mass loss event (even a minor mass loss event) in the gas turbine hot gas path section. Such minor mass loss events may include material release from gas turbine hot gas path section components, including but not limited to at least one of nozzles and blades.

[0030] Furthermore, as embodied in this disclosure, another aspect includes detecting an increase in the mass of components in the hot gas path section of the gas turbine. According to various aspects of this disclosure, the increase in the mass of components in the hot gas path section of the gas turbine can be caused by deposits on stationary or rotating components within the hot gas path section of the gas turbine, including but not limited to at least one of nozzles and blades.

[0031] As used herein, the term "gas turbine hot gas path section component" includes, but is not limited to, combustion liners, transitions, turbine nozzles and turbine blades, end caps, fuel nozzle assemblies, crossfire tubes, turbine shrouds, and turbine blades (wheel blades) that are typically exposed to hot gases. These gas turbine hot gas path section components may be stationary (such as nozzle assemblies and combustion liners) or rotating (such as blades), and may also be cooled by secondary gas flow in the gas turbine system.

[0032] As illustrated in this disclosure, detecting an increase or decrease in the mass of a gas turbine hot gas path section component includes monitoring changes in turbine operating parameters, such as impeller space temperature, vibration, exhaust temperature, exhaust temperature difference, compressor discharge temperature, and various other operating conditions of the gas turbine. Another aspect of the detection, as illustrated in this disclosure, includes determining various operating conditions in real time using on-site monitoring (OSM) data, and subsequently using these real-time operating conditions to determine an increase or decrease in the mass of the gas turbine hot gas path section component.

[0033] According to certain aspects of the implementation scheme, real-time monitoring of changes and deviations in various parameters and operating conditions using on-site monitoring (OSM) data can indicate an increase (deposit) or decrease (release / mass loss) in at least one of the components in the hot gas path section of a stationary or rotating gas turbine. As embodied in this disclosure, changes in impeller space temperature are at least one primary indicator of an increase or decrease in the mass of at least one of the components in the hot gas path section of a stationary or rotating gas turbine. As described above, at least one sensor 26 is capable of determining the temperature and, accordingly, determining the temperature change in the impeller space.

[0034] Depending on whether an upward or downward trend or behavior is observed, impeller space temperature data can be normalized using turbine inlet temperature. The normalized impeller space temperature can be used in conjunction with variations in rotor vibration (typically used only to identify anomalies in rotating gas turbine hot gas path components) and at least one of the gas turbine exhaust temperature difference to determine the value at which anomalies have occurred in at least one of the stationary or rotating gas turbine hot gas path components. Anomalies in at least one of the stationary or rotating gas turbine hot gas path components can be a decrease or increase in mass.

[0035] As embodied in this disclosure, the process described below utilizes diagnostics of a combination of analytical parameter variations to detect whether any quality deviation is indicated. In some embodiments of this disclosure, the quality deviation may include an increase or decrease in the mass of at least one of the components of a stationary or rotating gas turbine hot gas path section.

[0036] Furthermore, as embodied in this disclosure, the process and diagnostics are effective in determining a minor increase or decrease in the mass of at least one of the components in the hot gas path section of a stationary or rotating gas turbine, wherein the term minor means a mass difference associated with, for example, corrosion, cracking, spalling, scaling, or the accumulation of particulate matter.

[0037] like Figure 4 As shown, a process 100 for using diagnostics to analyze combinations of changing conditions to detect the presence of any mass deviation (such as an increase or decrease in the mass of at least one of the components in the hot gas path section of a fixed or rotating gas turbine) will now be described. At step 110, the combustion gas turbine 10 is equipped with a sensor 26 that transmits real-time gas turbine parameters and operating conditions to a computer device or control unit 200 (hereinafter referred to as "control unit"). As described below, the control unit 200 may include or have a computer device and utilizes diagnostics to analyze combinations of various gas turbine real-time parameters and operating condition changes to detect whether any mass deviation, such as an increase or decrease in the mass of at least one of the components in the hot gas path section of a fixed or rotating gas turbine, is indicated.

[0038] Monitoring in control device 200 is provided in real time and includes calculations and analyses that can be performed in real time, dynamically, and automatically. Therefore, the operator of control device 200 does not need to repeatedly reprogram the algorithm. As used herein, real time refers to a substantially short period of time following a change in the input that affects the result (e.g., numerical calculation). In an exemplary embodiment, calculations are updated periodically in real time, determined by the scan time and clock speed of control device 200.

[0039] Process 100 continues, and control device 200 receives various real-time gas turbine parameters and operating conditions at step 115. These real-time gas turbine parameters and operating conditions include, but are not limited to, impeller space temperature (WS Temp), shaft speed (TNH), load (DWATT), shaft vibration and vibration amplitude, gas turbine exhaust temperature (TTXM), bearing vibration and vibration amplitude, gas turbine total power and efficiency variations, and compressor inlet and outlet temperatures (CTIM and CTD), as well as any other gas turbine parameters and operating conditions now known or identified below as necessary for gas turbine operation monitoring.

[0040] Then, at step 120, the control device 200 determines whether the real-time parameters and operating conditions of the gas turbine are sufficient to detect an increase or decrease in the mass of the gas turbine hot gas path section component. In response to the gas turbine real-time parameters and operating conditions being determined to be insufficient, such as some data being unavailable or more data being required, the control device 200 generates a notification at step 121 to provide additional, supplementary, or suitable real-time parameters and operating conditions for the gas turbine.

[0041] In response to the availability of sufficient real-time gas turbine parameters and operating conditions, process 100 proceeds to step 125, where at least one of the compressor inlet and outlet temperatures (CTIM and CTD) is normalized to the impeller space temperature (WS Temp) and analyzed. These real-time parameters and operating conditions are evaluated to determine if there is an increasing or decreasing trend in WS Temp. If there is no increasing or decreasing trend in WS Temp, monitoring continues at step 126 because there is no indication of release and / or mass loss events in the gas turbine hot gas path section, nor is there any indication of deposits on stationary or rotating gas turbine hot gas path components within the gas turbine hot gas path section.

[0042] Regardless of whether an increasing or decreasing trend in WS Temp is determined at step 125, process 100 continues to analyze at least one of the following: the gas turbine exhaust temperature (TTXM) at step 130 or the TTXM difference between monitored events; and any changes in the vibration amplitude of real-time parameters and operating conditions from the gas turbine 13 at step 135. These two steps, 130 and 135, can be performed in parallel, one at a time (with either step performed first), or in any other manner that provides the control device 200 with indications of changes at steps 130 and 135.

[0043] As embodied in this disclosure, depending on whether, at step 130, the TTXM or the TTXM difference between monitored events exhibits an increasing or decreasing trend in TTXM or TTXM difference, which occurs simultaneously with an increasing or decreasing trend in WS Temp, the control device 200 generates a mass deviation alarm at step 175. The mass deviation alarm at step 175 indicates a mass loss or mass increase in a stationary or rotating gas turbine hot gas path component within the gas turbine hot gas path section.

[0044] Depending on whether there is no increasing or decreasing TTXM or TTXM difference trend simultaneously with the increasing or decreasing WS Temp trend at step 130, the control device 200 causes process 100 to continue monitoring the real-time parameters and operating conditions of the gas turbine at step 140. Monitoring continues because the control device 200 does not have indications for release and / or mass loss events in the gas turbine hot gas path section components, nor for deposits on the gas turbine hot gas path components within the gas turbine hot gas path section.

[0045] Depending on whether an increasing or decreasing trend in WS Temp is determined at step 125, process 100 may continue to step 135. At step 135, control device 200 analyzes the monitored real-time parameters and operating conditions of the gas turbine to determine if there are any changes in gas turbine vibration amplitude occurring simultaneously with the increasing or decreasing WS Temp. Changes in vibration amplitude include, but are not limited to, vibrations from bearings, shafts, or any other components indicated by the gas turbine sensor 26. Depending on whether process 100 indicates a vibration difference between monitoring steps (i.e., simultaneous with an increasing or decreasing trend in WS Temp), control device 200 generates a mass deviation alarm at step 175. The mass deviation alarm at step 175 indicates a mass loss or increase in mass in the stationary or rotating gas turbine hot gas path components within the gas turbine hot gas path section.

[0046] Similar to the above, and as embodied in this disclosure, depending on whether there is an increasing or decreasing vibration trend simultaneously with the increasing or decreasing WS Temp trend at step 135, the control device 200 causes process 100 to continue monitoring the real-time parameters and operating conditions of the gas turbine at step 140. As mentioned above, this continued monitoring is an indication of the absence of release and / or mass loss events in the gas turbine hot gas path section, and also an indication of the absence of deposits on the gas turbine hot gas path section.

[0047] refer to Figure 5As those skilled in the art will understand, the methods and systems embodied in this disclosure can be provided as systems and / or methods utilizing control device 200. As embodied in this disclosure, control device 200 may include a computer program product. Therefore, control device 200 may take the form of a completely hardware implementation, a completely software implementation (including firmware, resident software, microcode, etc.), or a combination of software and hardware. Furthermore, control device 200 may include a computer program product embodied in any tangible medium, having computer-usable program code embodied in the medium to perform the processes embodied in this disclosure.

[0048] As illustrated in this disclosure, the following reference flowchart ( Figure 4 The process 100 is described using diagrams and / or block diagrams. It should be understood that each block in the flowchart diagrams and / or block diagrams, and combinations of blocks in the flowchart diagrams and / or block diagrams, can be implemented by computer program instructions, and the control device 200 can be embodied by such a computer or computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, special-purpose computer, or other programmable data processing device to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing device, create means for implementing the function / action specified in one or more blocks of the flowchart and / or block diagram.

[0049] These computer program instructions may also be stored in a computer-readable medium, which directs a computer or other programmable data processing apparatus to function in a particular manner, causing the instructions stored in the computer-readable medium to produce an article of writing including instruction means that implement the functions / actions specified in one or more blocks of a flowchart and / or block diagram. The computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process, such that the instructions, which execute on the computer or other programmable apparatus, provide a process for implementing the functions / actions specified in one or more blocks of a flowchart and / or block diagram.

[0050] In this regard, control device 200 may include or be included as computer infrastructure 102, which is capable of performing the various process steps described herein for determining mass variations in the hot gas path components of a gas turbine. Specifically, computer infrastructure 102 is shown to include computing device 104, which includes system 106 that enables computing device 104 and control device 200 to determine mass variations in the hot gas path components of a gas turbine by performing the process steps of this disclosure.

[0051] Control device 200 Figure 5The device shown includes a memory 112, a processor (PU) 114, an input / output (I / O) interface 116, and a bus 118. Furthermore, the computing device 104 is shown communicating with a sensor 26. As is known in the art, generally, the processor 114 executes computer program code, such as system 106, that can be stored in the memory 112 and / or storage system 122. When executing the computer program code, the processor 114 can read and / or write data (such as, but not limited to, operating conditions of a gas turbine) to / from the memory 112, storage system 122, and / or I / O interface 116. The bus 118 provides a communication link between each component in the computing device 104. The I / O device 118 may include any device that enables a user to interact with the computing device 104 or any device that enables the computing device 104 to communicate with one or more other computing devices. Input / output devices (including, but not limited to, keyboards, displays, pointing devices, etc.) may be coupled to the system directly or via an intermediate I / O controller.

[0052] In any case, computing device 104 may include any general-purpose computing article capable of executing computer program code installed by a user (e.g., a personal computer, server, handheld device, etc.). However, it should be understood that computing device 104 and system 106 merely represent various possible equivalent computing devices capable of performing the various processing steps of this disclosure. In this regard, in other embodiments, computing device 104 may include any special-purpose computing article having hardware and / or computer program code for performing specific functions, any computing article including combinations of special-purpose and general-purpose hardware / software, etc. In each case, the program code and hardware may be created using standard programming and engineering techniques, respectively.

[0053] Similarly, computer infrastructure 102 only illustrates various types of computer infrastructure used to implement this disclosure. For example, in one embodiment, computer infrastructure 102 includes 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 this disclosure. When the communication link includes a network, the network may 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 may also be coupled to the system to enable the data processing system to be coupled to other data processing systems or remote printers or storage devices via intermediary private or public networks. Modems, cable modems, and Ethernet cards are just a few of the types of network adapters currently available. In any case, communication between computing devices can utilize any combination of various types of transmission technologies.

[0054] As discussed herein, various systems and components are described as “acquired” data for identification and detection, as embodied in this disclosure. It should be understood that any solution can be used to acquire the corresponding data. For example, a corresponding system / component may generate and / or be used to generate data, retrieve data from one or more data storage devices (e.g., a database), receive data from another system / component, etc. When data is not generated by a particular system / component, it should be understood that, in addition to the system / component shown, another system / component may be implemented that generates data and provides it to the system / component and / or stores data for access by the system / component.

[0055] As used throughout the specification and claims, approximate language can be used to modify any quantitative expression that allows for variation without causing a change in its underlying function. Therefore, values ​​modified by one or more terms (such as “about,” “approximately,” and “substantially”) are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value. Range limitations may be combined and / or interchanged herein and throughout the specification and claims; unless otherwise indicated by context or language, these ranges are identified and include all subranges contained therein. The term “about” applied to a specific value within a range applies to both endpoints and may indicate + / - 10% of the value, unless otherwise dependent on the precision of the instrument measuring that value.

[0056] All means or steps plus functional elements in the following claims are intended to include any structure, material, action, and equivalent for performing a function in conjunction with other claimed elements of a particular claim. This disclosure has been described for purposes of illustration and description, but it is not intended to be exhaustive or to limit the disclosure to the forms disclosed. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of this disclosure. Embodiments have been selected and described to best explain the principles and practical application of this disclosure and to enable others skilled in the art to understand various embodiments of this disclosure with various modifications suitable for the intended particular use.

Claims

1. A method for determining mass differences in a hot gas path component of a gas turbine (13), the method comprising: Monitor the operating conditions of the gas turbine (13); The following steps are used to determine whether the temperature of the impeller space (51) of the gas turbine (13) has changed: The impeller space (51) temperature is compared with at least one of the compressor (11) inlet temperature and compressor (11) discharge temperature for normalization, the normalized impeller space temperature is analyzed, and the trend of increasing or decreasing normalized impeller space temperature is determined. In response to the normalized impeller space temperature trend indicating an increase or decrease: Determine if at least one of the following exists: The gas turbine (13) exhaust temperature indicator shows the simultaneous change in gas turbine (13) exhaust temperature with the trend of increasing or decreasing normalized impeller space temperature, and... The gas turbine (13) vibrates, wherein the simultaneous change and the determination of the vibration change occur in at least one of the following: determining the simultaneous change and the vibration change in parallel; determining the simultaneous change before determining the vibration change; and determining the vibration change before determining the simultaneous change. In response to the presence of at least one of the simultaneous change and the vibration change, a mass deviation in the hot gas path component of the gas turbine (13) is indicated.

2. The method according to claim 1, further comprising: Monitor the operating conditions of the gas turbine (13) and determine if there is any information from the monitoring that can be used to determine: Temperature changes have occurred in the impeller space (51) of the gas turbine (13); The temperature indicator of the impeller space (51) indicates that a temperature change has occurred, and The gas turbine (13) exhaust temperature indicates the simultaneous change of the gas turbine (13) exhaust temperature with the trend of increasing or decreasing normalized impeller space temperature; and at least one of the gas turbine (13) vibration change.

3. The method of claim 1, wherein the mass deviation in the hot gas path component of the gas turbine (13) comprises: This indicates a decrease in mass difference within the hot gas path component.

4. The method of claim 3, wherein the mass deviation in the hot gas path component of the gas turbine (13) comprises: This indicates an increase in mass difference in the hot gas path components.

5. The method according to claim 1, wherein the method is performed in real time.

6. A gas turbine (13) control device (200) for a gas turbine (13), the control device (200) monitoring and determining mass differences in hot gas path components of the gas turbine (13), the control device (200) comprising: At least one sensor (26) monitors the operating conditions of the gas turbine (13), the at least one sensor (26) monitoring one or more of the following: shaft (50) speed, gas turbine (13) load, impeller space (51) temperature, vibration, gas turbine (13) exhaust temperature, compressor (11) inlet temperature, and compressor (11) discharge temperature; and A non-transitory computer-readable medium comprising computer-executable instructions for operating a gas turbine (13), the instructions including instructions for the following operations: Monitor the parameters and operating conditions of the gas turbine (13); The following steps are used to determine whether the temperature of the impeller space (51) of the gas turbine (13) has changed: The impeller space (51) temperature is compared with at least one of the compressor (11) inlet temperature and compressor (11) discharge temperature for normalization. The normalized impeller space temperature is analyzed, and the trend of increasing or decreasing normalized impeller space temperature is determined. Then In response to a normalized impeller space temperature trend indicating an increase or decrease, determine whether at least one of the following exists: The gas turbine (13) exhaust temperature indicator shows the simultaneous change in gas turbine (13) exhaust temperature with the trend of increasing or decreasing normalized impeller space temperature; and The gas turbine (13) vibrates, wherein the simultaneous change and the determination of the vibration change occur in at least one of the following: determining the simultaneous change and the vibration change in parallel; determining the simultaneous change before determining the vibration change; and determining the vibration change before determining the simultaneous change. In response to the presence of at least one of the simultaneous change and the vibration change, a mass deviation in the hot gas path component of the gas turbine (13) is indicated.

7. The gas turbine (13) control device (200) according to claim 6, wherein indicating mass deviation in the hot gas path component of the gas turbine (13) includes indicating mass reduction difference in the hot gas path component.

8. The gas turbine (13) control device (200) according to claim 6, wherein indicating mass deviation in the hot gas path component of the gas turbine (13) includes indicating mass increase difference in the hot gas path component.

9. The gas turbine (13) control device (200) according to claim 6, wherein at least one of the following exists: The temperature of the impeller space (51) of the gas turbine (13) did not change; The temperature of the impeller space (51) does not indicate temperature changes; and The gas turbine (13) exhaust temperature does not show any change and there is no vibration change. Continue to monitor the gas turbine (13).

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