Gas turbine mass differential detection system and method

Abstract

A gas turbine differential mass sensing system and method is provided. [Solution] A method for detecting a mass difference in a hot gas path component of a gas turbine includes monitoring an operating condition of the gas turbine, determining whether a change in wheelspace temperature of the gas turbine has occurred, determining whether the wheelspace temperature has changed by comparing the wheelspace temperature to at least one of a compressor inlet temperature and a compressor discharge temperature indicative of a temperature change, determining whether a gas turbine exhaust temperature indicates a simultaneous change in temperature while the wheelspace temperature is compared to the at least one of the compressor inlet temperature and the compressor discharge temperature, and / or a gas turbine vibration change, and / or indicating a mass change in the hot gas path component of the gas turbine in response to the simultaneous change in the gas turbine exhaust temperature and / or the gas turbine vibration change.

Description

Technical Field

[0001] The present disclosure generally relates to systems and methods for detecting mass changes or mass differences in gas turbines. In particular, the present disclosure relates to systems and methods for detecting mass changes or mass differences in components of the hot gas path of a gas turbine.

Background Art

[0002] Detecting a mass change in a component of a gas turbine (such as, but not limited to, a component of the hot gas path of a gas turbine) is useful for avoiding missile events, blade damage and separation, and substantial mass changes related to fatigue when the change is not so large and a warning has been issued for the change. Recognizing and detecting a slight mass difference during the monitoring of a gas turbine can warn the operator of the gas turbine that there is a risk of an impending failure. Thus, for example, by monitoring mass differences related to erosion, cracking, spoiling, adhesion, accumulation of released particles, and other causes, it is possible to reduce further damage to the gas turbine components.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

[0004] A first aspect of the present disclosure provides a method for detecting mass differences of components in a high-temperature gas path of a gas turbine. The method includes monitoring the operating state of the gas turbine; determining whether a change in the wheelspace temperature of the gas turbine has occurred; determining whether the wheelspace temperature has changed by comparing the wheelspace temperature with at least one of the compressor inlet temperature and compressor discharge temperature indicating a temperature change; determining, in response to the determination that a temperature change has occurred in the wheelspace temperature, that the exhaust temperature of the gas turbine has changed simultaneously with the temperature change while the wheelspace temperature is being compared with at least one of the compressor inlet temperature and compressor discharge temperature, and that at least one of the vibration changes of the gas turbine is occurring; and indicating a variation in the mass of components in the high-temperature gas path of the gas turbine in response to the simultaneous change in the exhaust temperature of the gas turbine and the occurrence of at least one of the vibration changes of the gas turbine.

[0005] A second aspect of this disclosure provides a gas turbine control device for a gas turbine. The control device monitors and detects the mass difference of components in the high-temperature gas path of the gas turbine. The control device includes at least one sensor that monitors the operating conditions of a gas turbine, the at least one sensor that monitors one or more of the following: shaft speed, gas turbine load, wheelspace temperature, vibration, gas turbine exhaust temperature, compressor inlet temperature, and compressor discharge temperature; and a non-temporary computer-readable medium containing computer-executable instructions for operating the gas turbine, the instructions including instructions for monitoring the parameters and operating conditions of the gas turbine, determining whether a change has occurred in the wheelspace temperature of the gas turbine, determining whether the wheelspace temperature indicates a temperature change, determining whether the wheelspace temperature indicates a temperature change, and determining whether the gas turbine exhaust temperature is changing simultaneously with the temperature change while the wheelspace temperature is being compared to at least one of the compressor inlet temperature and the compressor discharge temperature, and determining whether the vibration change of the gas turbine is at least one of the vibration changes of the gas turbine, and indicating a variation in the mass of the components of the high-temperature gas path of the gas turbine in response to at least one of the vibration changes of the gas turbine.

[0006] Exemplary embodiments of this disclosure are designed to solve problems described herein and / or other problems not described herein. [Brief explanation of the drawing]

[0007] These and other features of the Disclosure will be more readily apparent from the following detailed description of various aspects of the Disclosure, used in conjunction with the accompanying drawings illustrating various embodiments of the Disclosure. [Figure 1] This is a schematic diagram of an exemplary combustion gas turbine engine in which embodiments of the present invention can be used, as embodied by this disclosure. [Figure 2] This is a cross-sectional view of the compressor in the combustion gas turbine engine shown in Figure 1, which is materialized by this disclosure. [Figure 3] This is a cross-sectional view of the gas turbine in the combustion gas turbine engine shown in Figure 1, which is materialized by this disclosure. [Figure 4] A flowchart illustrating one aspect of the process embodied by this disclosure is shown. [Figure 5] An exemplary control device and associated computer for detecting mass differences in components of the high-temperature gas path of a gas turbine are shown, and this includes monitoring gas turbine parameters and operating conditions.

[0008] Please note that the drawings in this disclosure are not scaled to the same degree. The drawings are intended to illustrate only typical aspects of this disclosure and should not be considered to limit the scope of this disclosure. In the drawings, similar numbers represent similar elements throughout the drawings. [Modes for carrying out the invention]

[0009] First, in order to clearly describe the current technology, it is necessary to select specific terminology when referring to and describing the relevant mechanical components within a gas turbine, particularly those within the high-temperature gas path portion of the gas turbine. Wherever possible, common industry terms will be used and adopted in a manner consistent with their accepted meanings in that industry. Unless otherwise specified, the above terms should be given a broad interpretation consistent with the context and claims of this application. Those skilled in the art will understand that, in many cases, certain components may be referred to using several different or redundant terms. What is described as a single part herein may, in another context, comprise multiple components and be referred to as comprising multiple components. Or, what is described herein as comprising multiple components may, elsewhere, be referred to as a single part.

[0010] Furthermore, certain descriptive terms may be used regularly in this specification, and it is beneficial to define these terms at the beginning of each mode for carrying out the invention. Unless otherwise specified, these terms and their definitions are as follows: In this specification, “downstream” and “upstream” are terms that indicate the direction of fluid flow, such as the working fluid flowing through a turbine engine, or the direction of air flow through a combustor or the flow of a cooling medium through one of the multiple component systems of a gas turbine. The term “downstream” corresponds to the direction of fluid flow, and the term “upstream” represents the direction opposite to that fluid flow. Unless otherwise specified, the terms “forward” and “rear” refer to the direction of the front of the engine or the compressor end, and “rear” refer to the direction of the rear of the engine or the gas turbine end.

[0011] It is often required to describe components positioned at different radial locations relative to the central axis. The term “radial” refers to movement or position perpendicular to the axis. For example, if a first component is closer to the axis than a second component, it may be described as “radially inward” or “inboard” of the second component. Conversely, if a first component is further from the axis than a second component, it may be described as “radially outward” or “outboard” 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 is understood that such terms may be applied in relation to the central axis of a turbine.

[0012] Furthermore, in this specification, several descriptive terms may be used regularly, as described below. The terms “First,” “Second,” and “Third” may be used interchangeably to distinguish one component from another and are not intended to imply the position or importance of individual components.

[0013] The terminology used in this specification is intended to describe only specific embodiments and is not intended to limit the disclosure. In this specification, “a,” “an,” and “the” are intended to be plural unless the context clearly indicates that they are plural. The terms “contains” and / or “contains,” as used herein, state that the mentioned feature, integer, process, operation, element, and / or component exists, but are not intended to exclude the existence and addition of one or more other features, integers, processes, operations, elements, components, and / or groups thereof. “Any” or “optionally” means that the event or situation described thereafter may or may not occur, and that the description includes examples in which the event occurs or the component exists, and examples in which the event does not occur or the component does not exist.

[0014] When an element or layer is referred to as “present,” “engaged,” “connected,” or “joined” with another element or layer, it may be in direct contact with, directly engaged with, connected to, or joined to the other element or layer, or an intervening element or layer may exist. In contrast, when an element is referred to as “directly present,” “directly joined,” “directly connected,” or “directly joined” with another element or layer, there is no intervening element or layer. Other words used to describe the relationship between elements should be interpreted in a similar manner (e.g., “between” and “directly between,” “adjacent” and “directly adjacent”). In this specification, the term “and / or” includes any item from the enumerated related items and all combinations of one or more items from the items.

[0015] Referring to the drawings, Figures 1 to 3 show exemplary combustion gas turbine engines in which embodiments of the present invention can be utilized. Those skilled in the art will understand that these embodiments are not limited to this type of use. As described above, these embodiments can be used in combustion gas turbine engines such as engines used for power generation and aircraft, steam gas turbine engines, and other types of rotary engines.

[0016] Figure 1 shows an exemplary combustion gas turbine engine in which an embodiment of the present invention can be utilized. Those skilled in the art will understand that this embodiment is not limited to use in this type of combustion gas turbine engine. As stated above, this embodiment can be used in combustion gas turbine engines such as engines used for power generation and aircraft, steam gas turbine engines, and other types of rotary engines, but is not limited thereto. Generally, a combustion gas turbine engine operates by extracting energy from a pressurized flow of hot gas produced by the combustion of fuel in a compressed airflow. As shown in Figure 1, the combustion gas turbine engine system 10 may consist of an axial flow compressor 11 mechanically coupled to a downstream gas turbine section or combustion gas turbine engine 13 (hereinafter, "gas turbine") by a common shaft or rotor, and a combustor 12 positioned between the compressor 11 and the gas turbine 13.

[0017] Figure 2 shows an exemplary and non-limiting multistage axial flow compressor 11 that can be used in the gas turbine 13 of Figure 1. As shown, the compressor 11 may include multiple stages. Each stage may include a row of compressor rotor blades 14 followed by a row of compressor stator nozzles 15. Thus, the first stage may include a row of compressor rotor blades 14 that rotate around a central shaft, followed by a row of compressor stator nozzles 15 that remain stationary during operation. The compressor stator nozzles 15 are generally spaced apart from each other in the circumferential direction and fixed around the axis of rotation. The compressor rotor blades 14 are mounted on the shaft at circumferential spacing relative to the shaft. As the shaft rotates during operation, the compressor rotor blades 14 rotate with the shaft. As the compressor rotor blades 14 rotate around the shaft, they impart kinetic energy to the air or fluid flowing through the compressor 11. The compressor 11 may have other stages besides those shown in Figure 2. The additional stage may include a plurality of compressor rotor blades 14 spaced apart in the circumferential direction, followed by a plurality of compressor stator nozzles 15 spaced apart in the circumferential direction.

[0018] Figure 3 shows a non-limiting partial view of an exemplary gas turbine section or gas turbine 13 that can be used in the combustion gas turbine engine of Figure 1. The gas turbine 13 may also include multiple stages. Three exemplary gas turbine stages are shown, but these are merely illustrative and non-limiting and are not intended to limit the embodiments in any way. Therefore, more or fewer gas turbine stages may be present in the gas turbine 13. A first gas turbine stage includes a plurality of gas turbine buckets or a plurality of gas turbine rotor blades 16 (hereinafter, "blades") that rotate around a shaft during operation, and a plurality of nozzles or a plurality of gas turbine stator blades 17 (hereinafter, "nozzles") that remain stationary during operation. The plurality of nozzles 17 are generally spaced circumferentially and fixed around a rotation axis. The gas turbine rotor blades 16 may be mounted on a gas turbine wheel or disc (not shown) so as to rotate with the gas turbine shaft 50. A second stage of the gas turbine 13 is also shown. The second gas turbine stage similarly includes a plurality of nozzles 17 spaced circumferentially, followed by a plurality of gas turbine rotor blades 16 spaced circumferentially, which are also mounted to the gas turbine wheel so as to be rotatable. A third gas turbine stage is also illustrated and similarly includes a plurality of nozzles 17 and a plurality of rotor blades 16. It is understood that the gas turbine nozzles 17 and rotor blades 16 are in the hot gas path of the gas turbine 13. The direction of the hot gas flow in the gas turbine hot gas path is indicated by arrows. The gas turbine 13 may have other stages besides the stage shown in Figure 3. Each additional gas turbine stage may include a row of gas turbine nozzles 17 followed by a row of gas turbine rotor blades 16.

[0019] In a non-limiting description of use, when the compressor rotor blades 14 in the axial flow compressor 11 rotate, the air flow can be compressed. In the combustor 12, when the compressed air is mixed with fuel and ignited, energy can be released. Next, the high-temperature gas flow obtained from the combustor 12 (which can be called the working fluid) is guided to the gas turbine rotor blades 16, and the flow of the working fluid induces the rotation of the gas turbine rotor blades 16 and the shaft 50. Thereby, the energy of the flow of the working fluid is converted into the mechanical energy of the rotating blades, and since the rotor blades and the shaft are connected, the shaft 50 rotates. Next, the mechanical energy of the shaft 50 can be used to rotationally drive the compressor rotor blades 14, the required compressed air is supplied, and, for example, a generator generates electricity.

[0020] The operation of the gas turbine can be monitored by several sensors 26 detecting various operating conditions of the gas turbine, the generator, and the balance of the plant (including the operating conditions of the surrounding environment of the gas turbine). FIG. 1 shows various positions where the sensors 26 can be arranged to obtain various parameters and operating conditions. As embodied by the present disclosure, these positions are not intended to limit the embodiments in any way, and the position of the sensor 26 can be any position within the gas turbine 13 or the gas turbine system (a known position or a position defined below) where the parameters and operating conditions can be determined.

[0021] As embodied by the present disclosure, at least one sensor 26 is arranged in the wheel space 51, inside the wheel space, on the wall surface of the wheel space, or communicates with the wheel space to measure the wheel space temperature (WSTemp). In one aspect of the embodiment, a plurality of sensors 26 can be arranged in the same wheel space 51. The plurality of sensors 26 that can be arranged in the same wheel space 51 are arranged at intervals in the radial direction so as to obtain a plurality of wheel space temperatures (WSTemp).

[0022] Furthermore, evaluate WSTemp to detect the mass difference (increase or decrease) of components in the high-temperature gas path. Further, as embodied by the present disclosure, other sensors 26 may be provided to obtain various parameters and operating conditions of the gas turbine, and these parameters and operating conditions can be evaluated to detect the mass difference (increase or decrease) of components in the high-temperature gas path. Examples of operating conditions include shaft speed (TNH), load (DWATT), shaft vibration, gas turbine exhaust temperature (TTXM), bearing vibration, changes in the total output and efficiency of the gas turbine, compressor inlet temperature and compressor discharge temperature (CTIM and CTD respectively), and any other gas turbine parameters and operating conditions known or determined hereinafter that are desirable for gas turbine operation monitoring, but are not limited thereto.

[0023] As embodied by the present disclosure, the temperature sensor 26 can monitor the ambient temperature of the gas turbine 13, the compressor discharge temperature, the exhaust gas temperature of the gas turbine, and other temperature measurements of the gas flow through the gas turbine 13.

[0024] The sensor 26 may include a flow sensor, a speed sensor, rotor (or shaft) vibration, a flame detector sensor, a valve position sensor, a guide vane angle sensor, etc., for determining various parameters related to the operation of the gas turbine 13. In the present specification, the operating conditions represent items that can be used to represent a given operating condition of the gas turbine and can be used to define the parameters (temperature, pressure, flow rate, etc.) of the gas turbine at a defined position within the gas turbine.

[0025] One embodiment of the invention includes detecting an increase or decrease in the mass of components in the high-temperature gas path of a gas turbine. As embodied by this disclosure, the detection may include detecting a decrease due to separation and / or mass loss events in the high-temperature gas path of a gas turbine (events that result in only slight mass loss). Events resulting in only slight mass loss may include the separation of material from components in the high-temperature gas path of a gas turbine (including, but not limited to, at least one of the nozzles and blades).

[0026] Furthermore, a further embodiment embodied by this disclosure includes detecting an increase in the mass of components in the high-temperature gas path of a gas turbine. According to an embodiment of this disclosure, an increase in the mass of components in the high-temperature gas path of a gas turbine may be due to deposits within the high-temperature gas path of the gas turbine, either stationary or rotating components of the high-temperature gas path (including, but not limited to, at least one of the nozzles and blades).

[0027] As used herein, the term “components of the high-temperature gas path of a gas turbine” includes, but is not limited to, combustion liners, transition components, turbine nozzles and turbine blades, end caps, fuel nozzle assemblies, crossfire tubes, turbine stationary shrouds, and turbine blades (buckets), which are typically exposed to high-temperature gases. These components of the high-temperature gas path of a gas turbine may be stationary components (such as nozzle assemblies and combustion liners) or rotating components (such as blades), and may be cooled by secondary airflow within the gas turbine system.

[0028] As embodied by this disclosure, detecting an increase or decrease in the mass of components in the high-temperature gas path of a gas turbine includes monitoring changes in turbine operating parameters (such as wheelspace temperature, vibration, exhaust temperature, exhaust diffusion, compressor discharge temperature, and various other operating conditions of the gas turbine). A further aspect of detection embodied by this disclosure includes determining various operating conditions in real time using on-site monitoring (OSM) data, and subsequently using the real-time operating conditions to determine an increase or decrease in the mass of components in the high-temperature gas path of a gas turbine.

[0029] According to some embodiments of the invention, real-time monitoring of changes and fluctuations in various parameters and operating conditions using on-site monitoring (OSM) data can indicate an increase (accumulation) or decrease (separation / mass loss) in at least one of the stationary or rotating components of the high-temperature gas path of a gas turbine. As embodied in this disclosure, a change in wheel space temperature is at least one key indicator of an increase or decrease in mass of at least one of the stationary or rotating components of the high-temperature gas path of a gas turbine. As described above, at least one sensor 26 can measure the wheel space temperature, and therefore the temperature change in the wheel space.

[0030] Depending on whether an upward or downward trend or behavior is observed, wheelspace temperature data can be normalized by the turbine inlet temperature. The normalized wheelspace temperature can be used in conjunction with at least one of the following: changes in rotor vibration (typically used only to determine abnormalities in the rotating components of the high-temperature gas path of a gas turbine) and the spread of gas turbine exhaust temperature to determine the value when an abnormality occurs in at least one of the stationary and rotating components of the high-temperature gas path of a gas turbine. An abnormality in at least one of the stationary and rotating components of the high-temperature gas path of a gas turbine may represent a decrease or increase in mass.

[0031] As embodied by this disclosure, the processes described below utilize diagnostics that analyze multiple combinations of parameter changes to detect whether a mass variation is present. In certain embodiments of this disclosure, the mass variation is an increase or decrease in the mass of at least one of the stationary and rotating components of the high-temperature gas path of a gas turbine. Furthermore, the processes and diagnostics embodied by this disclosure are effective in determining that the mass of at least one of the stationary or rotating components of the high-temperature gas path of a gas turbine has increased or decreased slightly. Here, the term “slightly” refers to a mass difference related, for example, to erosion, cracking, spalling, fouling, or accumulation of emitted particulate matter.

[0032] As shown in Figure 4, a process 100 is described for detecting whether there is a mass fluctuation (such as an increase or decrease in mass due to combustion of at least one of the stationary and rotating components of the high-temperature gas path of the gas turbine) by utilizing diagnostics that analyze multiple combinations of condition changes. The combustion gas turbine 10 is equipped with a sensor 26 that can transmit real-time parameters and operating conditions of the gas turbine to a computer or control device 200 (hereinafter, "control device") in step 110. The control device 200 may include or consist of a computer, as described below, and detects whether there is a mass fluctuation (such as an increase or decrease in mass of at least one of the stationary and rotating components of the high-temperature gas path of the gas turbine) by utilizing diagnostics that analyze various combinations of real-time parameter and operating condition changes of the gas turbine.

[0033] Monitoring in the control unit 200 is provided in real time, and monitoring includes calculations and analyses that can be performed in real time, dynamically, and automatically. Therefore, the operator of the control unit 200 does not need to reprogram the algorithms repeatedly. In this specification, real time means that it occurs within a sufficiently short period after an input affecting the result (e.g., calculation using a computer) has changed. In an exemplary embodiment, the calculation is updated in real time with a periodicity determined by the scan time and clock speed of the control unit 200.

[0034] Process 100 then continues, in step 115, the control device 200 receives various real-time parameters and operating conditions of the gas turbine. These real-time parameters and operating conditions of the gas turbine include, but are not limited to, wheelspace temperature (WSTemp), 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 changes, and compressor inlet temperature and compressor discharge temperature (CTIM&CTD), as well as any other gas turbine parameters and operating conditions known or determined below as desirable for gas turbine operation monitoring.

[0035] Next, in step 120, the control device 200 determines whether the real-time parameters and operating conditions of the gas turbine are sufficient to determine whether an increase or decrease in the mass of the components of the high-temperature gas path section of the gas turbine has been detected. If it is determined that the real-time parameters and operating conditions of the gas turbine are insufficient (for example, some data is unavailable or more data is needed), the control device 200 generates a notification in step 121 to make other real-time parameters and operating conditions of the gas turbine, additional parameters and operating conditions, or appropriate parameters and operating conditions available.

[0036] If sufficient real-time parameters and operating conditions for the gas turbine are provided, process 100 proceeds to step 125, where at least one of the compressor inlet temperature and compressor discharge temperature (CTIM and CTD) is normalized and analyzed according to the wheelspace temperature (WSTemp). These real-time parameters and operating conditions are evaluated to determine whether the WS temperature is increasing or decreasing. If no increasing or decreasing trend is observed in the WS temperature, it indicates that there are no separation and / or mass loss events in the high-temperature gas path of the gas turbine, and there are no deposits on stationary or rotating components in the high-temperature gas path of the gas turbine, so monitoring continues in step 126.

[0037] If, in step 125, the process 100 determines that the WS temperature is increasing or decreasing, in step 130, it analyzes at least one of the gas turbine exhaust temperature (TTXM) and the TTXM difference between the monitoring events, and in step 135, it continues to analyze the changes in vibration amplitude with respect to the real-time parameters and operating conditions of the gas turbine 13. These two steps 130 and 135 may be performed in parallel, one step at a time, one step first, or any other way in which steps 130 and 135 are performed to provide the control device 200 with the indication that a change has been observed.

[0038] In step 130, as embodied by the present disclosure, if the TTXM, or the TTXM difference between multiple monitoring events, shows an increasing or decreasing trend in the TTXM or TTXM difference, and this occurs simultaneously with an increasing or decreasing trend in WSTemp, the control device 200 generates a mass fluctuation alarm in step 175. The mass fluctuation alarm in step 175 indicates either a mass loss or a mass increase in a stationary or rotating component within the high-temperature gas path of the gas turbine.

[0039] In step 130, if there is no increasing or decreasing trend in TTXM or TTXM difference that occurs simultaneously with the increasing or decreasing trend in WS temperature, the control device 200 instructs process 100 to continue monitoring the real-time parameters and operating conditions of the gas turbine in step 140. The control device 200 continues monitoring because it has not received any information indicating separation and / or mass loss events of components in the high-temperature gas path of the gas turbine, and there are no deposits in the components within the high-temperature gas path of the gas turbine.

[0040] If it is determined in step 125 that the WS temperature is increasing or decreasing, process 100 may proceed to step 135. In step 135, the control device 200 analyzes the monitored real-time parameters and operating conditions of the gas turbine to determine whether the vibration amplitude of the gas turbine is changing simultaneously with the increase or decrease in WS temperature. Changes in vibration amplitude include, but are not limited to, vibrations of the bearings, shafts, or any other components of the gas turbine that the sensor 26 can indicate. If, in process 100, a vibration difference occurs during the monitoring process that coincides with an increasing or decreasing trend in WS temperature, the control device 200 generates a mass fluctuation alarm in step 175. The mass fluctuation alarm in step 175 indicates either a mass loss or mass increase of a stationary or rotating component in the high-temperature gas path of the gas turbine.

[0041] As described above, and as further embodied in this disclosure, if in step 135 there is no upward or downward trend in vibrations occurring simultaneously with an upward or downward trend in WS temperature, the control device 200 causes the process 100 to continue monitoring the real-time parameters and operating conditions of the gas turbine in step 140. As described above, continued monitoring indicates that there are no separation and / or mass loss events in the high-temperature gas path of the gas turbine, and also indicates that there are no deposits in the components within the high-temperature gas path of the gas turbine.

[0042] Referring to Figure 5, as will be understood by those skilled in the art, the methods and systems embodied in this disclosure can be provided as systems and / or methods utilizing the control device 200. As embodied in this disclosure, the control device 200 may include a computer program product. Thus, the control device 200 may take the form of a purely hardware embodiment, a purely software embodiment (including firmware, resident software, microcode, etc.), or a combined software and hardware embodiment. Furthermore, as embodied in this disclosure, the control device 200 may include a computer program product embodied in any tangible medium having program code usable by a computer embodied in the medium to perform a process.

[0043] As embodied by this disclosure, process 100 is described below with reference to a flowchart (see Figure 4), illustrations, and / or block diagrams. It is understood that 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 implemented by such a computer or computer program instructions. These computer program instructions can be implemented in the processor of a general-purpose computer, a dedicated computer, or other programmable data processing device that generates a machine, thereby creating means for instructions executed by the processor of the computer or other programmable data processing device to implement the functions / operations specified in one or more blocks of the flowchart and / or block diagrams.

[0044] These computer program instructions can also be stored in a computer-readable medium that can instruct a computer or other programmable data processing device to function in a particular way, and the instructions stored in the computer-readable medium generate a product that includes instruction means for implementing the functions / operations specified in one or more blocks of a flowchart and / or block diagram. Furthermore, the computer program instructions can be loaded into a computer or other programmable data processing device, causing the computer to generate a process in which a series of operational steps to be executed by the computer or other programmable device are implemented, providing a process for the instructions executed by the computer or other programmable device to implement the functions / operations specified in one or more blocks of a flowchart and / or block diagram.

[0045] In this case, the control device 200 may include a computer infrastructure 102 capable of performing various process steps described herein for detecting mass differences of components in the high-temperature gas path of a gas turbine, or the control device 200 may be included as the computer infrastructure 102. In particular, the computer infrastructure 102 is shown to include a computing device 104 having a system 106, thereby enabling the computing device 104 and the control device 200 to detect mass differences of components in the high-temperature gas path of a gas turbine by performing the process steps of the disclosure.

[0046] The control 200 shown in Figure 5 includes memory 112, a processor (PU) 114, an input / output (I / O) interface 116, and a bus 118. Furthermore, it is illustrated that the computing device 104 communicates with the sensor 26. As is known in the art, generally, the processor 114 executes computer program code (such as system 106) which can be stored in memory 112 and / or storage device 122. While executing the computer program code, the processor 114 can read data (but not limited to) such as the operating conditions of a gas turbine from memory 112, storage device 122, and / or I / O interface 116 and / or write data to memory 112, storage device 122, and / or I / O interface 116. The bus 118 provides communication links between each of the components within the computing device 104. The I / O device 118 may include any device that allows a user to interact with the computing device 104, or any device that allows the computing device 104 to communicate with one or more other computing devices. Input / output devices (including, but not limited to, keyboards, displays, and pointing devices) can be connected to the system directly or through an intermediary I / O controller.

[0047] In any case, computing device 104 may include any general-purpose computer product (e.g., a personal computer, server, handheld device, etc.) capable of executing computer program code installed by a user. However, it should be understood that computing device 104 and system 106 merely represent various conceivable equivalent computing devices capable of performing the various process steps of this disclosure. In this regard, in other embodiments, computing device 104 may include any specific-purpose computer product including hardware and / or computer program code for performing a particular function, or any computer product including a combination of specific-purpose and general-purpose hardware / software. In any case, the program code and hardware may be created using standard programming and engineering techniques, respectively.

[0048] Similarly, computer infrastructure 102 is merely an example of various types of computer infrastructure for implementing the Disclosure. For example, in one embodiment, computer infrastructure 102 includes two or more computing devices (e.g., a server cluster) communicating by any type of wired and / or wireless communication link, such as shared memory or a network, to perform various process steps of the Disclosure. Where 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 be coupled to the system so that the data processing system can connect to other data processing systems or remote printers or storage devices through an intervening private or public network. 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.

[0049] As described herein, various systems and components are described as “acquiring” data for measurement and detection, as embodied herein. It is understood that the corresponding data can be acquired using any solution. For example, the corresponding system / component can perform tasks such as generating data and / or being used to generate data, retrieving data from one or more data stores (e.g., databases), and / or receiving data from another system / component. If data is not generated by a particular system / component, it is understood that, apart from the illustrated system / component, other systems / components can be implemented, which generate data, provide that data to the illustrated system / component, and / or store that data so that it can be accessed by the illustrated system / component.

[0050] Throughout this specification and the claims, the approximation language may be applied to modify any quantitative expression that may vary to a reasonable extent without altering the fundamental function of the expression. Therefore, values ​​modified by terms such as “approximately,” “about,” and “substantially” are not limited to the exact values ​​specified. In at least some examples, the approximation language may correspond to the precision of the instrument used to measure the value. Herein, and throughout this specification and the claims, range limitations are interchangeable and / or substitutable, and unless the context or wording specifically indicates otherwise, such ranges are identified and include all subranges encompassed therein. “About,” applied to a particular value within a range, may apply to values ​​at both ends of that range and, unless particularly dependent on the precision of the instrument used to measure the value, may indicate + / - 10% of the stated value.

[0051] All corresponding structures, materials, actions, and equivalents of all elements of means-plus-function or step-plus-function in the following claims are intended to encompass all structures, materials, or actions for performing that function in combination with any other specifically claimed claimed elements. The descriptions in this disclosure are presented for illustrative and explanatory purposes only and are not intended to include all possible elements 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 this disclosure. These embodiments have been selected and described in order to best illustrate the principles and practical applications of this disclosure and to enable others skilled in the art to understand this disclosure in terms of various modifications to suit specific intended uses. [Explanation of symbols]

[0052] 11 Compressor 13 Gas Turbine 26 sensors 50 Gas turbine shaft 51 Wheel Spacers 200 Control device

Claims

1. A method for detecting the mass difference of components in the high-temperature gas path of a gas turbine (13), To monitor the operating state of the gas turbine (13), To determine whether a change in the wheel space (51) temperature of the gas turbine (13) has occurred, To determine whether the wheelspace (51) temperature has changed based on the wheelspace (51) temperature normalized by at least one of the compressor (11) inlet temperature and the compressor (11) discharge temperature, In response to the determination that the wheelspace (51) temperature indicates that a temperature change has occurred, The gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheel space (51) temperature tends to increase or decrease, such that the gas turbine (13) exhaust temperature changes simultaneously with the temperature change of the wheel space (51) temperature, and Vibration changes in relation to real-time parameters and operating conditions of the gas turbine (13) Determining whether at least one of the simultaneous change and the vibration change is present, and the determination of the simultaneous change and the vibration change is made by 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 occurrence of at least one of the aforementioned simultaneous changes and vibration changes, the mass of the components of the high-temperature gas path of the gas turbine (13) is shown to fluctuate. Methods that include...

2. The operation status of the gas turbine (13) is monitored, Based on the aforementioned monitoring, A change occurred in the wheel space (51) temperature of the gas turbine (13). The wheel space (51) temperature indicates that a temperature change has occurred, and The gas turbine (13) exhaust temperature changes simultaneously with the temperature change of the wheel space (51) temperature, such that the tendency for the gas turbine (13) exhaust temperature to increase or decrease occurs simultaneously with the tendency for the wheel space (51) temperature to increase or decrease, and at least one of the real-time parameters and vibration changes of the gas turbine (13) with respect to operating conditions. To determine whether information is available to make that determination. The method according to claim 1, including the method described in claim 1.

3. The method according to claim 1, wherein determining whether the gas turbine (13) exhaust temperature exhibits a co-occurring change with the temperature change of the wheelspace (51) temperature such that the gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheelspace (51) temperature increases or decreases, and determining whether at least one of the real-time parameters and operating conditions of the gas turbine (13) is present, includes determining whether the gas turbine (13) exhaust temperature exhibits a co-occurring change with the temperature change of the wheelspace (51) temperature such that the gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheelspace (51) temperature increases or decreases.

4. The method according to claim 1, wherein showing the variation in mass of the components of the high-temperature gas path of the gas turbine (13) includes showing the difference due to a decrease in mass of the components of the high-temperature gas path.

5. The method according to claim 4, wherein showing the variation in mass of the components of the high-temperature gas path of the gas turbine (13) includes showing the difference due to an increase in the mass of the components of the high-temperature gas path.

6. The method according to claim 1, wherein determining whether the gas turbine (13) exhaust temperature exhibits a co-occurring change with the temperature change of the wheel space (51) such that the gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheel space (51) temperature increases or decreases, and whether at least one of the vibration changes with respect to the real-time parameters and operating conditions of the gas turbine (13) is present, is further comprising determining whether the gas turbine (13) exhaust temperature exhibits a co-occurring change with the temperature change of the wheel space (51) such that the gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheel space (51) temperature increases or decreases, and whether at least one of the vibration changes with respect to the real-time parameters and operating conditions of the gas turbine (13) is present.

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

8. A gas turbine (13) control device (200) for a gas turbine (13), wherein the control device (200) monitors and detects the mass difference of the components of the high-temperature gas path of the gas turbine (13), and the control device (200) At least one sensor (26) for monitoring the operating conditions of the gas turbine (13), wherein the at least one sensor (26) monitors one or more of the following: shaft (50) speed, gas turbine (13) load, wheel space (51) temperature, vibration, gas turbine (13) exhaust temperature, compressor (11) inlet temperature, and compressor (11) discharge temperature. A non-temporary computer-readable medium containing computer-executable instructions for operating a gas turbine (13), wherein the instructions are: To monitor the parameters and operating conditions of the gas turbine (13), To determine whether a change in the wheel space (51) temperature of the gas turbine (13) has occurred, To determine whether the wheelspace (51) temperature shows a temperature change, To determine whether the wheel space (51) temperature indicates that a temperature change has occurred, and In response to the determination that the wheelspace (51) temperature is showing a temperature change, The gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheel space (51) temperature tends to increase or decrease, such that the gas turbine (13) exhaust temperature changes simultaneously with the temperature change of the wheel space (51) temperature, and Vibration changes in relation to real-time parameters and operating conditions of the gas turbine (13) Determining whether at least one of the simultaneous change and the vibration change is present, and the determination of the simultaneous change and the vibration change is made by 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 occurrence of at least one of the aforementioned simultaneous changes and vibration changes, the mass of the components of the high-temperature gas path of the gas turbine (13) is shown to fluctuate. Non-temporary computer-readable media containing instructions for executing and A gas turbine (11) control device (200), including a gas turbine (11).

9. The gas turbine (11) control device (200) according to claim 8, wherein the gas turbine (13) exhaust temperature exhibits a co-occurring change with the temperature change of the wheel space (51) such that the gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheel space (51) temperature tends to increase or decrease, and whether at least one of the real-time parameters and operating conditions of the gas turbine (13) is present, includes determining whether the gas turbine (13) exhaust temperature exhibits a co-occurring change with the temperature change of the wheel space (51) such that the gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheel space (51) temperature tends to increase or decrease.

10. The gas turbine (13) control device (200) according to claim 9, wherein showing the variation in mass of the components of the high-temperature gas path of the gas turbine (13) includes showing the difference due to a decrease in the mass of the components of the high-temperature gas path.

11. The gas turbine (13) control device (200) according to claim 9, wherein showing the variation in mass of the components of the high-temperature gas path of the gas turbine (13) includes showing the difference due to an increase in the mass of the components of the high-temperature gas path.

12. Determining whether the gas turbine (13) exhaust temperature exhibits a co-occurring change with the wheel space (51) temperature, such that the gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheel space (51) temperature increases or decreases, and whether at least one of the vibration changes with respect to the real-time parameters and operating conditions of the gas turbine (13) is present, is a gas turbine (11) control device (13) according to claim 9, comprising determining whether the gas turbine (13) exhaust temperature exhibits a co-occurring change with the wheel space (51) temperature, such that the gas turbine (13) exhaust temperature tends to increase or decrease at the same time as the wheel space (51) temperature increases or decreases, and whether at least one of the vibration changes with respect to the real-time parameters and operating conditions of the gas turbine (13) is present.

13. The gas turbine (13) control device (200) according to claim 12, wherein showing the variation in mass of the components of the high-temperature gas path of the gas turbine (13) includes showing the difference due to a decrease in the mass of the components of the high-temperature gas path.

14. The gas turbine (13) control device (200) according to claim 12, wherein showing the variation in mass of the components of the high-temperature gas path of the gas turbine (13) includes showing the difference due to an increase in the mass of the components of the high-temperature gas path.

15. No change in the wheel space (51) temperature of the gas turbine (13) has occurred. The wheel space (51) temperature does not show any change in temperature, and The gas turbine (13) exhaust temperature shows no change, and there is no change in vibration. The control device (200) for the gas turbine (13) according to claim 8, which continues to monitor the gas turbine (13) if at least one of the following conditions is met.

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