Non-optical flame detector and method

Abstract

To provide a flame detection method and system in a gas turbine.SOLUTION: There is provided a method of detecting a flame state of a combustor of a turbine engine. The method includes: determining at least one of a first derivative and a second derivative of a compressor discharge pressure (40) of a compressor of the turbine engine; determining at least one of a first derivative and a second derivative of a gas turbine exhaust gas temperature (30) of exhaust gases (70) output by the turbine engine; determining at least one of a first derivative and a second derivative of a gas turbine shaft / rotor speed of the turbine engine; determining at least one of a first derivative and a second derivative of a combustor dynamic pressure; and determining a flame state of the combustor of the turbine engine based on the combustor dynamic pressure, the determined derivatives of the combustion dynamics, compressor discharge pressure (40), gas turbine shaft / rotor speed, and gas turbine exhaust gas temperature (30) of the exhaust gases (70).SELECTED DRAWING: Figure 5

Description

Technical Field

[0001] The present disclosure generally relates to flame detection methods and systems. In particular, the present disclosure relates to flame detection methods and systems in gas turbines.

Background Art

[0002] Turbine engines typically include a flame detector that monitors the state of the flame within the combustor of the turbine engine. Most flame state detectors are optical detectors. Unfortunately, most such optical detectors have difficulty withstanding the extreme operating conditions within or adjacent to the combustor of the turbine engine without some cooling. These optical detectors that can withstand extreme operating conditions without cooling are very expensive.

[0003] Many optical flame state detectors require water or liquid cooling to operate within or adjacent to the combustor of the turbine engine. Unfortunately, leakage of the cooling fluid can cause significant damage to surrounding components. Thus, even providing cooling to the optical flame state detector can be somewhat risky.

Summary of the Invention

[0004] All aspects, examples, and features described below can be combined in any technically possible way.

[0005] One aspect of the present disclosure provides a method for determining the flame state of a combustor of a turbine engine, comprising the steps of: determining at least one primary and secondary derivative of the compressor discharge pressure of the compressor of the turbine engine; determining at least one primary and secondary derivative of the gas turbine exhaust gas temperature of the exhaust gas output by the turbine engine; determining at least one primary and secondary derivative of the gas turbine shaft / rotor speed of the turbine engine; determining a combustor dynamic pressure monitoring state; and determining the flame state of the combustor of the turbine engine based on the combustor dynamic pressure monitoring state, as well as the determined derivatives of the compressor discharge pressure, the gas turbine shaft / rotor speed, and the gas turbine exhaust gas temperature of the exhaust gas.

[0006] Another aspect of the present disclosure includes any of the preceding aspects, wherein the step of determining the flame state of a combustor includes determining whether a flame has been ignited in the combustor based on whether at least two of the primary derivatives of the compressor discharge pressure, the gas turbine exhaust gas temperature, and the gas turbine shaft / rotor speed are positive for a given period of time, and whether at least one of the primary derivatives of the compressor discharge pressure, the exhaust gas temperature, and the gas turbine shaft / rotor speed is greater than a threshold.

[0007] Another aspect of the present disclosure includes any of the preceding aspects, wherein the step of determining the flame state of a combustor includes determining that a flame has been ignited in the combustor based on whether at least two of the following are positive for at least a portion of a given period: the primary derivative of the compressor discharge pressure of the compressor, the primary derivative of the exhaust gas temperature, and the primary derivative of the gas turbine shaft / rotor speed, wherein the gas turbine shaft / rotor speed is greater than a preset threshold, the primary derivative of the compressor discharge pressure of the compressor is greater than a first threshold, and the primary derivative of the exhaust gas temperature is greater than a second threshold for a given period.

[0008] Another aspect of the present disclosure includes any of the preceding aspects, wherein the step of determining the flame state of a combustor includes determining whether a flame has been ignited in the combustor based on whether at least two of the primary derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed are positive for at least a portion of the same predetermined period.

[0009] Another aspect of the present disclosure includes any of the preceding aspects, wherein the step of determining the flame state of a combustor includes determining that a flame has been ignited in the combustor based on whether the first derivative of the compressor discharge pressure of the compressor is positive during a first part of a predetermined period and whether the first derivative of the exhaust gas temperature of the exhaust gas is positive during a second part of a predetermined period, the second part following the first part.

[0010] Another aspect of the present disclosure includes any of the preceding aspects, wherein a first determination step includes determining the primary and secondary derivatives of the compressor discharge pressure of a compressor; a second determination step includes determining the primary and secondary derivatives of the exhaust gas temperature of the exhaust gas output by the turbine engine; a third determination step includes determining the primary and secondary derivatives of the gas turbine shaft / rotor speed; and a step of determining the flame state of the combustor of the turbine engine is based on the determined primary and secondary derivatives of the compressor discharge pressure, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed.

[0011] Another aspect of the present disclosure includes any of the preceding aspects, wherein the step of determining the flame state of a combustor includes determining that a flame has been ignited in the combustor based on whether at least two of the primary and secondary derivatives of the compressor discharge pressure of the compressor, the primary and secondary derivatives of the exhaust gas temperature of the exhaust gas, and the primary and secondary derivatives of the gas turbine shaft / rotor speed are positive for a portion of a predetermined period.

[0012] Another aspect of the present disclosure includes any of the preceding aspects, wherein the step of determining the flame state of a combustor includes determining that a flame has been ignited in the combustor based on whether the primary and secondary derivatives of the compressor discharge pressure of the compressor are positive and above a threshold during a first part of a predetermined period, and whether the primary and secondary derivatives of the exhaust gas temperature of the exhaust gas are positive and above a threshold during a second part of a predetermined period.

[0013] Another aspect of the present disclosure includes any of the preceding aspects, wherein the step of determining the flame state of a combustor includes determining that the flame has been extinguished in the combustor based on whether at least two of the primary and secondary derivatives of the compressor discharge pressure of the compressor and the primary and secondary derivatives of the exhaust gas temperature of the exhaust gas are negative for at least a portion of a given period of time.

[0014] Another aspect of the present disclosure includes any of the preceding aspects, wherein the step of determining the flame state of a combustor includes determining whether the flame has been extinguished in the combustor based on whether at least two of the first derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed are negative for a portion of a given period, and whether at least one of the first derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed is below a threshold.

[0015] Another aspect of the present disclosure includes any of the preceding aspects, wherein the step of determining the flame state of a combustor includes determining that the flame has been extinguished in the combustor based on whether at least two of the primary derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed are negative for part of a predetermined period, whether the primary derivative of the compressor discharge pressure of the compressor is less than a first threshold for part of a predetermined period, and whether the primary derivative of the exhaust gas temperature of the exhaust gas is less than a second threshold for part of a predetermined period.

[0016] One aspect of the present disclosure provides a system for determining the flame state of a combustor of a turbine engine, comprising: a pressure change determination unit; a temperature change determination unit; a gas turbine shaft / rotor speed unit; a combustor dynamic pressure monitoring unit; a flame state determination unit; and a non-temporary computer-readable medium containing computer-executable instructions for operating a gas turbine, wherein the instructions determine at least one primary and secondary derivative of the compressor discharge pressure of the compressor of the turbine engine; at least one primary and secondary derivative of the exhaust gas temperature of the exhaust gas output by the turbine engine; at least one primary and secondary derivative of the combustion gas turbine shaft / rotor speed; at least one primary and secondary derivative of the combustor dynamic pressure; and the non-temporary computer-readable medium containing instructions for determining the flame state of the combustor of the turbine engine based on the determined derivatives of the combustor dynamic pressure, the compressor discharge pressure of the compressor, the determined exhaust gas temperature of the exhaust gas, and the determined derivatives of the gas turbine shaft / rotor speed.

[0017] One aspect of the present disclosure provides a system for determining the flame state of a combustor of a turbine engine, comprising: a pressure change determination unit for determining at least one of the primary and secondary derivatives of the compressor discharge pressure of the compressor of the turbine engine; a temperature change determination unit for determining at least one of the primary and secondary derivatives of the exhaust gas temperature of the exhaust gas output by the turbine engine; a gas turbine shaft / rotor speed unit for determining at least one of the primary and secondary derivatives of the gas turbine shaft / rotor speed; a combustor dynamic pressure monitoring unit for determining at least one of the primary and secondary derivatives of the combustion dynamics; and a flame state determination unit for determining the flame state of the combustor of the turbine engine based on the outputs of the pressure change determination unit, the temperature change determination unit, the gas turbine shaft / rotor speed unit, and the combustor dynamic pressure monitoring unit.

[0018] Another aspect of the present disclosure includes any of the preceding aspects, wherein the flame state determination unit determines that a flame has been ignited in the combustor based on whether at least two of the first derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed are positive for at least a portion of a given period, and whether at least one of the first derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed is greater than a threshold.

[0019] Another aspect of the present disclosure includes any of the preceding aspects, wherein the flame state determination unit determines that a flame has been ignited in the combustor based on whether at least two of the primary derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed are positive for at least a portion of a given period, whether the primary derivative of the compressor discharge pressure of the compressor is greater than a first threshold, whether the primary derivative of the exhaust gas temperature of the exhaust gas is greater than a second threshold, and whether the primary derivative of the gas turbine shaft / rotor speed is greater than a third threshold.

[0020] Another aspect of the present disclosure includes any of the preceding aspects, wherein the flame state determination unit determines that the flame has been extinguished in the combustor based on whether at least two of the primary derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed are negative for at least a portion of a given period, and whether at least one of the primary derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed is below a threshold.

[0021] Another aspect of the present disclosure includes any of the preceding aspects, wherein the flame state determination unit determines that the flame has been extinguished in the combustor based on whether at least two of the primary derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature of the exhaust gas, and the gas turbine shaft / rotor speed are negative for at least part of a given period, whether the primary derivative of the compressor discharge pressure of the compressor is below a first threshold for part of a given period, and whether the primary derivative of the exhaust gas temperature of the exhaust gas is below a second threshold for part of a given period.

[0022] Another aspect of the present disclosure includes any of the preceding aspects, wherein the pressure change determination unit also determines the primary and secondary derivatives of the compressor discharge pressure of the compressor; the temperature change determination unit determines both the primary and secondary derivatives of the exhaust gas temperature of the exhaust gas; and the flame state determination unit determines the flame state of the combustor of the turbine engine based on the determined primary and secondary derivatives of the compressor discharge pressure of the compressor, the exhaust gas temperature, and the gas turbine shaft / rotor speed.

[0023] Another aspect of the present disclosure includes any of the preceding aspects, wherein the flame state determination unit determines that a flame has been ignited in the combustor based on whether at least two of the primary and secondary derivatives of the compressor discharge pressure of the compressor, the primary and secondary derivatives of the exhaust gas temperature of the exhaust gas, and the primary and secondary derivatives of the gas turbine shaft / rotor speed are positive for at least a portion of a given period.

[0024] Another aspect of the present disclosure includes any of the preceding aspects, wherein the flame state determination unit determines that the flame has been extinguished in the combustor based on whether at least two of the primary and secondary derivatives of the compressor discharge pressure of the compressor, the primary and secondary derivatives of the exhaust gas temperature of the exhaust gas, and the primary and secondary derivatives of the gas turbine shaft / rotor speed are negative for at least a portion of a given period.

[0025] Two or more aspects described in this disclosure, including those described in this summary section, can be combined to form embodiments not specifically described herein.

[0026] The details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims.

[0027] Exemplary aspects of the disclosure are designed to solve the problems described herein and / or other problems not discussed.

[0028] These and other features of the disclosure will be more readily understood from the following detailed description of the various aspects of the disclosure in conjunction with the accompanying drawings that illustrate various embodiments of the disclosure.

Brief Description of the Drawings

[0029] [Figure 1] A diagram showing how the output pressure of a compressor, the first and second derivatives of the output pressure of the compressor, the temperature of the exhaust gas of a turbine engine, and the first and second derivatives of the temperature of the exhaust gas of the turbine engine change when a flame is ignited in a combustor of the turbine engine, embodied by the present disclosure. [Figure 2] A diagram showing how the output pressure of a compressor, the first and second derivatives of the output pressure, the temperature of the exhaust gas of a turbine engine, and the first and second derivatives of the temperature of the exhaust gas of the turbine engine change when a flame is extinguished in a combustor of the turbine engine, embodied by the present disclosure. [Figure 3] A block diagram showing elements of a system that can be used to determine the flame state of a combustor of a turbine engine, embodied by the present disclosure. [Figure 4] A diagram showing elements of a flame state determination unit that can determine the flame state of a combustor of a turbine engine, embodied by the present disclosure. [Figure 5] This is an illustrative flowchart illustrating the steps of a method for determining the flame state of a turbine engine combustor, as embodied in this disclosure. [Figure 6] Further block diagrams illustrating the elements of a system embodied in this disclosure that can be used to determine the ignition declaration of a turbine engine combustor. [Figure 7] Further block diagrams illustrating the elements of a system embodied in this disclosure that can be used to determine the loss of flame declaration of a turbine engine combustor. [Modes for carrying out the invention]

[0030] Please note that the drawings in this disclosure are not to scale. The drawings are intended to illustrate only typical embodiments of this disclosure and should not be considered to limit the scope of this disclosure. In the drawings, similar reference numerals represent similar elements between drawings.

[0031] As a first issue, in order to clearly describe the current technology, it is necessary to select specific technical terms when referring to and describing the relevant mechanical components within a gas turbine, including its control. Wherever possible, common industrial terminology will be used and utilized in the same sense as its accepted meaning. Unless otherwise stated, such terminology should be given a broad interpretation consistent with the context of this application and the appended claims. Those skilled in the art will understand that in many cases, certain components may be referred to using several different or overlapping terms. What may be described herein as a single component may include and be referred to in another context as consisting of multiple components. Or, what may be described herein as consisting of multiple components may be referred elsewhere as a single component.

[0032] In addition, as described below, several descriptive terms may be used in accordance with the rules. 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 any individual component.

[0033] The technical terms used herein are for the sole purpose of describing specific embodiments and are not intended to limit this disclosure. Where used herein, the singular forms “a,” “an,” and “the” are intended to include the plural unless otherwise specified. Where used herein, the terms “comprise” and / or “comprising” express the existence of the described features, integers, steps, actions, elements, and / or components, but do not exclude the existence or addition of one or more other features, integers, steps, actions, elements, components, and / or sets thereof. “Optional” or “optional” means that the events or circumstances described later may or may not occur, and this statement includes both instances in which the event occurs and instances in which it does not.

[0034] When an element or layer is referred to as “on top of,” “engaged with,” “connected to,” or “joined with” another element or layer, it may be directly engaged with, connected to, or joined to the other element or layer, or there may be an intervening element or layer. Conversely, when an element is referred to as “directly on top of,” “directly engaged with,” “directly connected to,” or “directly joined with” another element or layer, there may be no intervening element or layer. Other words used to describe relationships between elements should be interpreted similarly (e.g., “between” versus “directly between,” “adjacent to” versus “directly adjacent to.”). As used herein, the term “and / or” includes any combination of one or more of the related enumerated items.

[0035] As embodied in this disclosure, in certain embodiments, the characteristics of the compressor output pressure and exhaust temperature can be used to determine whether the flame has been ignited in the combustor or whether the flame has been extinguished ("flame extinction"). Thus, in certain embodiments of the embodiments, it becomes possible to understand the optical flame conditions by monitoring these values ​​and making appropriate judgments about their characteristics.

[0036] Figure 1 shows how the compressor output pressure of a turbine engine, the exhaust gas temperature of a turbine engine, and the first and second derivatives of both of these values ​​change during a flame ignition event. The line identified as reference number 10 in Figure 1 shows how the exhaust gas temperature of the turbine engine changes over time when the flame is first ignited in the combustor of the turbine engine. The line identified as reference number 20 shows how the compressor output pressure changes over time when the flame is first ignited in the turbine engine. The line identified as reference number 30 in Figure 1 shows the rate of change or first derivative of the exhaust gas temperature during the flame ignition event, and the line identified as reference number 40 shows the rate of change or first derivative of the compressor output pressure during ignition. The line identified as reference number 50 shows the second derivative (i.e., the rate of change of the rate of change) of the exhaust gas temperature, and the line identified as reference number 60 shows the second derivative of the compressor output pressure.

[0037] As is clear from Figure 1, the compressor output pressure 20 increases rapidly as soon as the flame is ignited. Also, as is clear from Figure 1, the exhaust gas temperature 10 steadily rises after flame ignition. The rise in exhaust gas temperature 10 does not begin until a short time delay has elapsed after flame ignition. However, the rise in exhaust gas temperature 10 continues for a long time even after flame ignition occurs.

[0038] The primary and secondary derivatives of exhaust temperature 30 and compressor discharge pressure 40 have a specific relationship with each other during normal turbine operation. They have a different relationship during ignition and flame extinction.

[0039] During normal turbine operation, in certain embodiments of the model, when the rate of change or first derivative of exhaust gas temperature 30 may increase, the rate of change or first derivative of compressor discharge pressure 40 may decrease. In other words, during normal turbine operation, when the rate of change or first derivative of exhaust gas 30 may decrease, the rate of change or first derivative of compressor discharge pressure 40 may increase. This relationship is reflected in the portion of the lines identified by reference numerals 30 and 40 in Figure 1, which occurs after flame ignition. The relationship between the second derivative of exhaust gas temperature and the second derivative of compressor output pressure follows the same trend.

[0040] However, during a flame ignition event, both the rate of change (first derivative) of exhaust gas temperature 30 and the rate of change (first derivative) of compressor output pressure 40 increase. This relationship is reflected in the sections of the lines identified by reference numbers 30 and 40 at the time of and immediately after the flame ignition event. Since both rates of change only increase during flame ignition, whenever it is detected that both rates of change (first derivatives) are positive and relatively high immediately afterward, it can be determined that a flame ignition has occurred.

[0041] The same applies to the second derivatives of exhaust gas temperature and compressor output pressure. In other words, if both the second derivatives of exhaust gas temperature and compressor output pressure are determined to be positive and relatively high over a short period, it can be determined that a flame ignition event has occurred.

[0042] Figure 2 shows how the compressor output pressure and exhaust gas temperature, as well as their first and second derivatives, change during a flame extinguishing or flame ignition event. The line identified as reference number 70 shows how the exhaust gas temperature changes over time as the flame in the combustor is extinguished. The line identified as reference number 80 shows how the compressor output pressure changes over time as the flame is extinguished. The line identified as reference number 90 shows the rate of change of exhaust gas temperature, which is the first derivative of exhaust gas temperature 70, and the line identified as reference number 100 shows the rate of change of compressor output pressure, which is the first derivative of compressor output pressure 80. The line identified as reference number 110 shows the second derivative of exhaust gas temperature 70, and the line identified as reference number 120 shows the second derivative of compressor output pressure 80.

[0043] In certain embodiments of the model, when the flame is extinguished, both the primary and secondary derivatives of the exhaust gas temperature and the compressor output pressure are decreasing or negative. Therefore, when it is detected that both the primary and / or secondary derivatives of the exhaust gas temperature and the compressor output pressure are decreasing or negative and below a certain threshold, it can be determined that the flame has been extinguished ("flame extinguished").

[0044] A system and method for determining when a flame in a turbine engine combustor was first ignited or extinguished monitors the characteristics of the combustor dynamic pressure, compressor output pressure, and exhaust gas temperature. The first and second derivatives of these values ​​are also determined. When simultaneous indications (as described herein) of these monitored characteristics coincide, an indication of flame ignition or flame extinction (or misfire) can be generated, as described below. Furthermore, the system and method embodied in this disclosure can provide an indication of flame ignition or flame extinction (or misfire). This indication can also be provided during partial speed events. The method and system embodied in this disclosure seeks trends that coincide with the patterns shown in Figures 1 and 2.

[0045] Figure 3 illustrates a system embodied by this disclosure capable of determining when a combustor flame is ignited or extinguished ("flame extinction"). In one embodiment, the system includes a combustor flame state determination unit 310, which is operably coupled to one or more compressor discharge pressure (CPD) sensors 302 and one or more exhaust gas temperature (TTXM) sensors 304. The combustor flame state determination unit 310 is further operably coupled to a combustion dynamics monitor (CDM) 305. In addition, the combustor flame state determination unit 310 may also be operably coupled to one or more turbine shaft / rotor speed (TNH) sensors 306 and / or other sensors. The shaft / rotor speeds can be calculated in terms of their absolute values, radial values, and / or any conceivable formula.

[0046] The compressor discharge pressure sensor 302 can detect the pressure of compressed air at the compressor output or in one or more stages within the compressor. Alternatively or additionally, one or more sensors can be provided in the combustor of the turbine engine to receive the compressed air produced by the compressor. Multiple signals from multiple pressure sensors can be operably coupled to the combustor flame state determination unit 310, which can use these multiple input signals to calculate the compressor output pressure. Alternatively, the signals from multiple pressure sensors can be processed by a sensor system to provide a single compressor output pressure value to the combustor flame state determination unit 310.

[0047] The combustion dynamics analyzed by the combustion dynamics monitor 305 refer to the combustion process within the combustion "boiler" and "liner." When fuel burns, pressure can increase. Depending on the design of the combustor, fuel nozzle, liner, and other high-temperature gas path components of the gas turbine, the combustion process may be subject to pressure oscillations or pulsations. In fact, the combustion process can be nonlinear and generate dynamic pressure oscillations, especially when confined to a fixed volume, such as in the gas turbine combustion boiler / combustion chamber. The amplitude of dynamic pressure oscillations can be low or relatively high. These dynamic oscillations or pulsations may cause or even indicate flame outage (LOF).

[0048] Similarly, a single exhaust gas temperature sensor may be provided, or multiple exhaust gas temperature sensors 304 may be positioned at various different locations. If multiple sensors are provided, they can all be operably connected to the combustor flame state determination unit 310. The combustor flame state determination unit 310 can calculate the average or central exhaust gas temperature from the signals generated by the sensors. Alternatively, an average or central exhaust gas temperature signal generated from data generated by multiple sensors may be provided to the combustor flame state determination unit 310.

[0049] Some elements of the combustor flame state determination unit 310 are shown in Figure 4. The combustor flame state determination unit 310 can be implemented using software that runs on a general-purpose computer. In this case, the modules or units within the combustor flame state determination unit 310 are implemented as various software modules. Alternatively, one or more units can be implemented as a combination of software and specific circuit elements. In yet another embodiment, some or all of the modules or units of the combustor flame state determination unit 310 may be implemented as circuits or application-specific integrated circuits.

[0050] As shown in Figure 4, the combustor flame state determination unit 310 includes a pressure change determination unit 312. The pressure change determination unit 312 monitors the compressor output pressure and determines whether the compressor output pressure is increasing or decreasing over time. The pressure change determination unit 312 can also calculate the first and second derivatives of the compressor output pressure.

[0051] Similarly, the gas turbine exhaust temperature change determination unit 314 monitors the exhaust gas temperature and determines whether the exhaust gas temperature is increasing or decreasing over time. The temperature change determination unit 314 can also calculate the first and second derivatives of the exhaust gas temperature.

[0052] The combustor flame state determination unit 310 also includes a combustor dynamic pressure monitoring unit 315. The combustor dynamic pressure monitoring unit 315 monitors the state of the gas turbine combustion process. The combustion process may be subject to pressure dynamic oscillations or pulsations.

[0053] In addition, the combustor flame state determination unit 310 includes a turbine shaft / rotor speed determination unit 306. The turbine shaft / rotor speed determination unit 306 monitors the turbine shaft / rotor speed and determines whether it is below a threshold of 90% of its desired value. Furthermore, the turbine shaft / rotor speed determination unit 306 can also calculate the first and second derivatives of the turbine shaft / rotor speed.

[0054] Furthermore, the combustor flame state determination unit 310 is provided with a composite or simplified indicator SMP307. The indicator SMP307 can provide indications directly associated with sensor monitoring. The indicator SMP307 refers to the compressor pressure discharge, gas turbine exhaust temperature, and the negative derivative of the gas turbine shaft / rotor speed (and when the gas turbine shaft / rotor speed is less than 90% of its desired value) to indicate the possibility of flame extinction or flame loss.

[0055] The indicator SMP307 is a sensor-based indicator, and in practice, a multi-sensor-based indicator. The indicator SMP307 embodied in this disclosure can provide flame state indication when one or more sensors are inoperable or when a sensor is facing a low signal-to-noise ratio event, such as partial velocity loss. For example, without limiting the embodiments, the SMP307 can provide LOF indication in a partial velocity instance with a low signal-to-noise ratio event. The SMP307 can also provide LOF indication in a partial velocity instance using the negative derivatives of CPD, TTXM, and THN.

[0056] Referring to Figure 4, the combustor flame state determination unit 310 further includes a flame state determination unit 320. The flame state determination unit 320 determines whether the gas turbine flame is bright, ignited, or whether flame extinction is occurring. The flame state determination unit 320 makes decisions regarding the flame state using information generated by some of the compressor pressure change determination unit 312, turbine shaft / rotor speed determination unit 306, gas turbine exhaust temperature change determination unit 314, combustor dynamic pressure monitoring unit 315, and / or gas turbine shaft / rotor speed sensors 306, as described below.

[0057] As used herein, flame state means, but is not limited to, whether the flame is ignited, ignited in the combustor, or extinguished. The flame state determination unit 320 can use information in indicator SMP 307 having first and second derivatives, such as those determined from information generated by some of the above-described compressor pressure change determination unit 312, turbine shaft / rotor speed determination unit 306, gas turbine exhaust temperature change determination unit 314, combustor dynamic pressure monitoring unit 315, and / or gas turbine shaft / rotor speed sensor 306. The flame state determination unit 320 can use predetermined logical rules to make decisions regarding the flame state, as will be described in more detail below.

[0058] Figure 6 is a schematic diagram of the ignition indicator factor analysis being processed for ignition declaration. In Figure 6, ignition indicators from the compressor discharge pressure sensor 302, one or more exhaust gas temperature sensors 304, and the combustor dynamic pressure monitor (CDM) 305 are provided to the pressure change determination unit 312. If the pressure change determination unit 312 determines that any two of the compressor discharge pressure sensor 302, one or more exhaust gas temperature sensors 304, and the combustor dynamic pressure monitor (CDM) 305 generate simultaneous ignition indicators, the system provides an overall indicator of "ignition declaration".

[0059] Figure 7 shows a diagram of the ignition indicator factor analysis being processed for a flame extinction (LOF) declaration. In Figure 6, ignition indicators from the compressor discharge pressure sensor 302, one or more exhaust gas temperature sensors 304, combustor dynamic pressure monitor (CDM) 305, one or more turbine shaft / rotor speed sensors 306, and indicator SMP 307 are provided to the pressure change determination unit 312. If the pressure change determination unit 312 determines that any two of the compressor discharge pressure sensor 302, one or more exhaust gas temperature sensors 304, and combustor dynamic pressure monitor (CDM) 305, one or more turbine shaft / rotor speed sensors 306, and indicator SMP 307 generate a simultaneous ignition indicator, the system provides an overall "flame extinction" indication.

[0060] Figure 5 provides a flowchart of the operating methodology according to an embodiment of the present disclosure. As shown in Figure 5, the method begins in process S502, in which the combustor flame state determination unit 310 receives and processes information regarding combustion dynamics, compressor discharge pressure, gas turbine shaft / rotor speed, and gas turbine exhaust gas temperature. As described above, the combustor flame state determination unit 310 receives and processes information that may include the received combustor dynamic pressure, compressor discharge pressure, gas turbine shaft / rotor speed, and gas turbine exhaust gas temperature, as well as the calculated first and second derivatives of those values.

[0061] In process S504, patterns in the received information are examined and compared to logical rules. For example, if any two of the primary and / or secondary derivatives of combustor dynamic pressure, compressor discharge pressure, gas turbine shaft / rotor speed, and gas turbine exhaust gas temperature are simultaneously pointing in opposite directions, this can indicate that the turbine is operating with flame extinction and / or without ignition. However, if any two of the primary and / or secondary derivatives of combustor dynamic pressure, compressor discharge pressure, gas turbine shaft / rotor speed, and gas turbine exhaust gas temperature are negative over the same predetermined period, this indicates that the flame in the combustor has been extinguished. Similarly, if the primary and / or secondary derivatives of combustor dynamic pressure, compressor discharge pressure, gas turbine shaft / rotor speed, and gas turbine exhaust gas temperature are positive over the same predetermined period, this indicates that a flame ignition event has occurred.

[0062] Finally, in process S506, the flame state determination unit 320 determines, based on the analysis results performed in process S504, whether the flame was ignited in the combustor or extinguished in the combustor. As described above, other information from other elements, including the indicator SMP307 and the combustor dynamic pressure monitoring unit, can also be used to make such a determination.

[0063] The logical rules used by the flame state determination unit 320 to determine whether the flame has just been ignited or extinguished in the combustor are based on how the characteristics of the compressor discharge pressure, gas turbine shaft / rotor speed, and gas turbine exhaust gas temperature change during the flame ignition and flame extinguishing events, as shown in Figures 1 and 2.

[0064] The determination of whether a flame ignition event has occurred can be based on both the fact that the primary and / or secondary derivatives of the combustor dynamic pressure, compressor discharge pressure, gas turbine shaft / rotor speed, and gas turbine exhaust gas temperature are increasing, and whether the absolute values ​​of the derivatives are above a threshold. Similarly, the determination that the flame has been extinguished can be based on the fact that the primary and / or secondary derivatives of the combustor dynamic pressure, compressor discharge pressure, gas turbine shaft / rotor speed, and gas turbine exhaust gas temperature are negative, and whether the values ​​of the primary and secondary derivatives are below a threshold.

[0065] As described above, by monitoring the characteristics of combustor dynamic pressure, compressor discharge pressure, gas turbine shaft / rotor speed, combustor dynamic pressure, and gas turbine exhaust gas temperature, it is possible to determine the flame state in the combustor of a turbine engine without using optical detectors. Furthermore, the determination of the flame state can be performed using information about the turbine engine that has already been monitored. Therefore, there is no need to add additional sensors or sensor-based equipment to replace the optical sensors that have been eliminated.

[0066] Further embodiments of this disclosure provide a determination of a lack of ignition (LOF) indicator. Figure 6 shows a system capable of determining the flame state, including an ignition indicator, as embodied in this disclosure, and Figure 7 shows a system capable of determining a lack of ignition (LOF), as embodied in this disclosure. In one embodiment, the system embodied in this disclosure includes a combustor flame state determination unit 310, which is operably coupled to one or more compressor discharge pressure sensors 302 and one or more exhaust gas temperature sensors 304. The combustor flame state determination unit 310 is further operably coupled to a combustor dynamic pressure monitor (CDM) 305. In this embodiment, a determination can be made if two or more of the combustor flame state determination unit 310, compressor discharge pressure sensors 302, and combustion dynamics monitor 305 provide simultaneous indication of a lack of ignition and / or a possible lack of flame.

[0067] In another embodiment shown in Figure 7, as embodied by this disclosure, the combustor flame state determination unit 310 is operably coupled to one or more compressor discharge pressure sensors 302, one or more exhaust gas temperature sensors 304, one or more combustor dynamic pressure monitors 305, and also operably coupled to one or more turbine shaft / rotor speed sensors 306, and an indicator SMP 307. To indicate flame outage, the characteristics / values ​​of combustion dynamics, exhaust gas temperature, turbine shaft / rotor speed, and compressor discharge pressure are analyzed together with the indicator SMP 307. Thus, if any two of these characteristics (e.g., combustion dynamics, exhaust gas temperature, compressor discharge pressure, HP rotor / shaft speed, etc.) and the indicator SMP 307 simultaneously indicate the possibility of ignition failure and flame outage (LOF), a determination can be made that flame outage (LOF) has occurred.

[0068] As can be understood, the methodologies and systems embodied by this disclosure can be provided as systems and / or methods utilizing the combustor flame state determination unit 310. As embodied by this disclosure, the combustor flame state determination unit 310 may include a computer program product. Furthermore, the combustor flame state determination unit 310 may take the form of a complete hardware embodiment, a complete software embodiment (including firmware, resident software, microcode, etc.), or an embodiment combining software and hardware. Furthermore, as embodied by this disclosure, the combustor flame state determination unit 310 may include a computer program product embodied in any tangible medium of representation having computer-readable program code embodied in a medium for carrying out a process.

[0069] As embodied in this disclosure, the process is described below with reference to the system (Figure 3) and the flowchart (Figure 5), figures, and / or block diagrams. It will be understood that each block in the flowchart and / or block diagrams, and combinations of blocks in the flowchart and / or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to the processor of a general-purpose computer, a dedicated computer, or other programmable data processing device for manufacturing the machine, thereby providing a means for these instructions, executed via 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.

[0070] 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, thereby manufacturing a product that includes instruction means to perform functions / operations specified in one or more blocks of a flowchart and / or block diagram. Computer program instructions can also be loaded into a computer or other programmable data processing device to generate a computer implementation process by having the computer or other programmable device perform a series of operational steps, thereby providing a process for performing functions / operations specified in one or more blocks of a flowchart and / or block diagram.

[0071] As described herein, various systems and components are described as “acquiring” data for determination and discovery, as embodied herein. It is understood that the corresponding data can be acquired using any solution. For example, a corresponding system / component may generate data and / or be used to generate data, retrieve data from one or more data storage devices (e.g., databases), and receive data from another system / component. When data is not generated by a particular system / component, it is understood that another system / component may be implemented, separate from the illustrated system / component, to generate and provide data to the system / component and / or store data for access by the system / component.

[0072] The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible embodiments of the systems, methods, and computer program products according to various embodiments of the present disclosure. In this regard, each block in the flowchart or block diagram may represent a module, segment, or portion of code that includes one or more executable instructions for realizing a specified logical function. It should also be noted that in some alternative embodiments, the functions described in the blocks may be performed in an order different from the order shown in the figures. For example, two blocks shown consecutively may actually be executed substantially simultaneously, or sometimes in reverse order depending on the functionality they contain. It should also be noted that each block in the block diagram and / or flowchart, as well as any combination of blocks in the block diagram and / or flowchart, may be realized by a dedicated hardware-based system or a combination of dedicated hardware and computer instructions that performs a specified function or operation.

[0073] As used herein and throughout 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. Thus, values ​​modified by terms such as “approximately,” “about,” and “substantially” are not limited to the exact value stated. In at least some examples, the approximation language may correspond to the precision of the instrument used to measure the value. As used herein, “about” indicates a range of + / - 10% of the stated 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 both ends of the range and, unless particularly dependent on the precision of the instrument used to measure the value, indicate a range of + / - 10% of the stated value.

[0074] 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 elements. The descriptions in this disclosure are presented for illustrative and explanatory purposes and are not intended to be exhaustive or to limit the disclosure to the forms disclosed herein. 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 embodiments with various modifications to suit specific intended uses. [Explanation of Symbols]

[0075] 10 Exhaust gas temperature 20 Compressor output pressure 30 Exhaust gas temperature, exhaust temperature 40 Compressor discharge pressure, compressor output pressure 70 Exhaust gas temperature 80 Compressor output pressure 302 Compressor Discharge Pressure (CPD) Sensor 304 Exhaust Gas Temperature (TTXM) Sensor 305 Combustion Dynamics Monitor, Combustor Dynamic Pressure Monitor 306 Turbine Shaft / Rotor Speed ​​(TNH) Sensor, Turbine Shaft / Rotor Speed ​​Determination Unit 307 Indicator SMP 310 Combustor Flame State Determination Unit 312 Compressor pressure change determination unit 314 Gas Turbine Exhaust Temperature Change Determination Unit 315 Combustor Dynamic Pressure Monitoring Unit 320 Flame state determination unit S502 Process S504 Process S506 Process

Claims

1. A method for determining the flame state of a combustor in a turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the compressor discharge pressure (40) of the compressor of the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed of the turbine engine, A step of determining the first derivative and at least one of the second derivatives of the combustor dynamic pressure (305), A step of determining the flame state of the combustor of the turbine engine based on the combustor dynamic pressure (305), compressor discharge pressure (40), gas turbine shaft / rotor speed, and the gas turbine exhaust gas temperature (30) of the exhaust gas (70). Includes, A method for determining the flame state of the combustor, comprising the step of determining whether a flame has been ignited in the combustor, based on whether at least two of the first derivative of the compressor discharge pressure (40) of the compressor, the first derivative of the gas turbine exhaust gas temperature (30), and the first derivative of the gas turbine shaft / rotor speed are positive for a predetermined period of time, and whether at least one of the first derivative of the compressor discharge pressure (40) of the compressor, the first derivative of the exhaust gas temperature (30), and the first derivative of the gas turbine shaft / rotor speed is greater than a threshold.

2. A method for determining the flame state of a combustor of a turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the compressor discharge pressure (40) of the compressor of the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed of the turbine engine, A step of determining the first derivative and at least one of the second derivatives of the combustor dynamic pressure (305), A step of determining the flame state of the combustor of the turbine engine based on the combustor dynamic pressure (305), compressor discharge pressure (40), gas turbine shaft / rotor speed, and the gas turbine exhaust gas temperature (30) of the exhaust gas (70). Includes, The step of determining the flame state of the combustor includes determining that a flame has been ignited in the combustor based on whether at least two of the following are positive for at least a portion of a predetermined period: the first derivative of the compressor discharge pressure (40) of the compressor, the first derivative of the gas turbine exhaust gas temperature (70) of the exhaust gas, and the first derivative of the gas turbine shaft / rotor speed, wherein the gas turbine shaft / rotor speed is greater than a preset threshold, the first derivative of the compressor discharge pressure (40) of the compressor is greater than a first threshold, and the first derivative of the exhaust gas temperature (30) is greater than a second threshold for the predetermined period.

3. A method for determining the flame state of a combustor of a turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the compressor discharge pressure (40) of the compressor of the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed of the turbine engine, A step of determining the first derivative and at least one of the second derivatives of the combustor dynamic pressure (305), A step of determining the flame state of the combustor of the turbine engine based on the combustor dynamic pressure (305), compressor discharge pressure (40), gas turbine shaft / rotor speed, and the gas turbine exhaust gas temperature (30) of the exhaust gas (70). Includes, A method for determining the flame state of the combustor, comprising the step of determining whether a flame has been ignited in the combustor, based on whether at least two of the following are positive during at least a portion of the same predetermined period: the first derivative of the compressor discharge pressure (40) of the compressor, the first derivative of the exhaust gas temperature (30) of the exhaust gas (70), and the first derivative of the gas turbine shaft / rotor speed.

4. A method for determining the flame state of a combustor of a turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the compressor discharge pressure (40) of the compressor of the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed of the turbine engine, A step of determining the first derivative and at least one of the second derivatives of the combustor dynamic pressure (305), A step of determining the flame state of the combustor of the turbine engine based on the combustor dynamic pressure (305), compressor discharge pressure (40), gas turbine shaft / rotor speed, and the gas turbine exhaust gas temperature (30) of the exhaust gas (70). Includes, The step of determining the flame state of the combustor includes determining that a flame has been ignited in the combustor, based on whether the first derivative of the compressor discharge pressure (40) of the compressor is positive during a first part of a predetermined period, and whether the first derivative of the exhaust gas temperature (30) of the exhaust gas (70) is positive during a second part of the predetermined period, the second part of which follows the first part.

5. A method for determining the flame state of a combustor of a turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the compressor discharge pressure (40) of the compressor of the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed of the turbine engine, A step of determining the first derivative and at least one of the second derivatives of the combustor dynamic pressure (305), A step of determining the flame state of the combustor of the turbine engine based on the combustor dynamic pressure (305), compressor discharge pressure (40), gas turbine shaft / rotor speed, and the gas turbine exhaust gas temperature (30) of the exhaust gas (70). Includes, A method comprising the first determining step of determining the primary and secondary derivatives of the compressor discharge pressure (40) of the compressor, the second determining step of determining the primary and secondary derivatives of the exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, and the third determining step of determining the primary and secondary derivatives of the gas turbine shaft / rotor speed, wherein the step of determining the flame state of the combustor of the turbine engine is based on the determined primary and secondary derivatives of the compressor discharge pressure (40), the exhaust gas temperature (30) of the exhaust gas (70), and the gas turbine shaft / rotor speed.

6. The method according to claim 5, wherein the step of determining the flame state of the combustor includes determining that a flame has been ignited in the combustor based on whether at least two of the primary and secondary derivatives of the compressor discharge pressure (40) of the compressor, the primary and secondary derivatives of the exhaust gas temperature (30) of the exhaust gas (70), and the primary and secondary derivatives of the gas turbine shaft / rotor speed are positive for a portion of a predetermined period.

7. The method according to claim 5, wherein the step of determining the flame state of the combustor includes determining that a flame has been ignited in the combustor, based on whether the primary and secondary derivatives of the compressor discharge pressure (40) of the compressor are positive and above a threshold during a first portion of a predetermined period, and whether the primary and secondary derivatives of the exhaust gas temperature (30) of the exhaust gas (70) are positive and above a threshold during a second portion of the predetermined period.

8. The method according to claim 5, wherein the step of determining the flame state of the combustor includes determining that the flame has been extinguished in the combustor, based on whether at least two of the primary and secondary derivatives of the compressor discharge pressure (40) of the compressor and the primary and secondary derivatives of the exhaust gas temperature (30) of the exhaust gas (70) are negative for at least a portion of a predetermined period.

9. A method for determining the flame state of a combustor of a turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the compressor discharge pressure (40) of the compressor of the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed of the turbine engine, A step of determining the first derivative and at least one of the second derivatives of the combustor dynamic pressure (305), A step of determining the flame state of the combustor of the turbine engine based on the combustor dynamic pressure (305), compressor discharge pressure (40), gas turbine shaft / rotor speed, and the gas turbine exhaust gas temperature (30) of the exhaust gas (70). Includes, A method for determining the flame state of the combustor, comprising the step of determining that the flame has been extinguished in the combustor, based on whether at least two of the primary derivatives of the compressor discharge pressure (40) of the compressor, the exhaust gas temperature (30) of the exhaust gas (70), and the gas turbine shaft / rotor speed are negative for part of a predetermined period, and whether at least one of the primary derivatives of the compressor discharge pressure (40) of the compressor, the exhaust gas temperature (30) of the exhaust gas (70), and the gas turbine shaft / rotor speed is below a threshold.

10. A method for determining the flame state of a combustor of a turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the compressor discharge pressure (40) of the compressor of the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, The steps include determining the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed of the turbine engine, A step of determining the first derivative and at least one of the second derivatives of the combustor dynamic pressure (305), A step of determining the flame state of the combustor of the turbine engine based on the combustor dynamic pressure (305), compressor discharge pressure (40), gas turbine shaft / rotor speed, and the gas turbine exhaust gas temperature (30) of the exhaust gas (70). Includes, A method for determining the flame state of the combustor, comprising the step of determining that the flame has been extinguished in the combustor, based on whether at least two of the primary derivatives of the compressor discharge pressure (40) of the compressor, the exhaust gas temperature (30) of the exhaust gas (70), and the gas turbine shaft / rotor speed are negative for part of a predetermined period, whether the primary derivative of the compressor discharge pressure (40) of the compressor is less than a first threshold for part of the predetermined period, and whether the primary derivative of the exhaust gas temperature (30) of the exhaust gas (70) is less than a second threshold for part of the predetermined period.

11. A system for determining the flame state of a turbine engine combustor, A pressure change determination unit (312) that determines at least one of the first derivative and second derivative of the compressor discharge pressure (40) of the compressor of the turbine engine, A temperature change determination unit (314) that determines at least one of the first derivative and second derivative of the exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, A gas turbine shaft / rotor speed unit that determines the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed, A combustor dynamic pressure monitoring unit (315) that determines at least one of the first and second derivatives of the combustion dynamics, A flame state determination unit (320) determines the flame state of the combustor of the turbine engine based on the output of the pressure change determination unit (312), the temperature change determination unit (314), the gas turbine shaft / rotor speed unit, and the combustor dynamic pressure monitoring unit (315). Equipped with, A system in which the flame state determination unit (320) determines that a flame has been ignited in the combustor based on whether at least two of the primary derivatives of the compressor discharge pressure (40) of the compressor, the primary derivative of the exhaust gas temperature (30) of the exhaust gas (70), and the primary derivative of the gas turbine shaft / rotor speed are positive for at least a portion of a predetermined period, and whether at least one of the primary derivatives of the compressor discharge pressure (40) of the compressor, the primary derivative of the exhaust gas temperature (30) of the exhaust gas (70), and the primary derivative of the gas turbine shaft / rotor speed is greater than a threshold.

12. A system for determining the flame state of a combustor of a turbine engine, A pressure change determination unit (312) that determines at least one of the first derivative and second derivative of the compressor discharge pressure (40) of the compressor of the turbine engine, A temperature change determination unit (314) that determines at least one of the first derivative and second derivative of the exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, A gas turbine shaft / rotor speed unit that determines the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed, A combustor dynamic pressure monitoring unit (315) that determines at least one of the first and second derivatives of the combustion dynamics, A flame state determination unit (320) determines the flame state of the combustor of the turbine engine based on the output of the pressure change determination unit (312), the temperature change determination unit (314), the gas turbine shaft / rotor speed unit, and the combustor dynamic pressure monitoring unit (315). Equipped with, A system in which the flame state determination unit (320) determines that a flame has been ignited in the combustor based on whether at least two of the following are positive for at least a portion of a predetermined period: the first derivative of the compressor discharge pressure (40) of the compressor, the first derivative of the exhaust gas temperature (30) of the exhaust gas (70), and the first derivative of the gas turbine shaft / rotor speed; whether the first derivative of the compressor discharge pressure (40) of the compressor is greater than a first threshold; whether the first derivative of the exhaust gas temperature (30) of the exhaust gas (70) is greater than a second threshold; and whether the first derivative of the gas turbine shaft / rotor speed is greater than a third threshold.

13. A system for determining the flame state of a combustor of a turbine engine, A pressure change determination unit (312) that determines at least one of the first derivative and second derivative of the compressor discharge pressure (40) of the compressor of the turbine engine, A temperature change determination unit (314) that determines at least one of the first derivative and second derivative of the exhaust gas temperature (30) of the exhaust gas (70) output by the turbine engine, A gas turbine shaft / rotor speed unit that determines the first derivative and at least one of the second derivatives of the gas turbine shaft / rotor speed, A combustor dynamic pressure monitoring unit (315) that determines at least one of the first and second derivatives of the combustion dynamics, A flame state determination unit (320) determines the flame state of the combustor of the turbine engine based on the output of the pressure change determination unit (312), the temperature change determination unit (314), the gas turbine shaft / rotor speed unit, and the combustor dynamic pressure monitoring unit (315). Equipped with, A system in which the flame state determination unit (320) determines that a flame has been extinguished in the combustor based on whether at least two of the primary derivatives of the compressor discharge pressure (40) of the compressor, the exhaust gas temperature (30) of the exhaust gas (70), and the gas turbine shaft / rotor speed are negative for at least a portion of a predetermined period, and whether at least one of the primary derivatives of the compressor discharge pressure (40) of the compressor, the exhaust gas temperature (30) of the exhaust gas (70), and the gas turbine shaft / rotor speed is below a threshold.

Images