U.S. patent application number 13/933869 was filed with the patent office on 2015-01-15 for systems and methods for advanced closed loop control and improvement of combustion system operation.
The applicant listed for this patent is General Electric Company. Invention is credited to Richard Joseph Mitchell, Jonathan Carl Thatcher.
Application Number | 20150017591 13/933869 |
Document ID | / |
Family ID | 52277357 |
Filed Date | 2015-01-15 |
United States Patent
Application |
20150017591 |
Kind Code |
A1 |
Mitchell; Richard Joseph ;
et al. |
January 15, 2015 |
SYSTEMS AND METHODS FOR ADVANCED CLOSED LOOP CONTROL AND
IMPROVEMENT OF COMBUSTION SYSTEM OPERATION
Abstract
A system includes an analytics system including a processor
configured to receive an indication of a detectable radiation
associated with a combustion system. The detectable radiation
includes multidimensional granular data associated with an
operation of the combustion system. The processor is configured to
determine a first value of one or more operational characteristics
of the combustion system based at least in part on the indication
of the detectable radiation, and to derive an output. The output
includes a second value derived based on the first value of the one
or more operational characteristics to adjust the first value
thereto.
Inventors: |
Mitchell; Richard Joseph;
(Simpsonville, SC) ; Thatcher; Jonathan Carl;
(Pendleton, SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Family ID: |
52277357 |
Appl. No.: |
13/933869 |
Filed: |
July 2, 2013 |
Current U.S.
Class: |
431/75 ;
702/33 |
Current CPC
Class: |
F23N 5/242 20130101;
F05D 2270/804 20130101; F23N 2229/00 20200101; F05D 2270/083
20130101; F01K 5/02 20130101; F23N 5/082 20130101; F05D 2300/607
20130101; F23N 5/16 20130101 |
Class at
Publication: |
431/75 ;
702/33 |
International
Class: |
F23M 11/04 20060101
F23M011/04 |
Claims
1. A system, comprising: an analytics system, comprising: a
processor configured to: receive an indication of a detectable
radiation associated with a combustion system, wherein the
detectable radiation comprises multidimensional granular data
associated with an operation of the combustion system; determine a
first value of one or more operational characteristics of the
combustion system based at least in part on the indication of the
detectable radiation; and derive an output, wherein the output
comprises a second value derived based on the first value of the
one or more operational characteristics to adjust the first value
thereto.
2. The system of claim 1, comprising a sensor configured to detect
the radiation and to transmit the indication of the radiation to
the processor.
3. The system of claim 2, wherein the sensor comprises an
electromagnetic radiation detector.
4. The system of claim 2, wherein the sensor is configured to
detect the radiation within an x-ray frequency range, an
ultraviolet frequency range, a visible light frequency range, an
infrared frequency range, a gamma frequency range, a microwave
frequency range, a radio frequency (RF) frequency range, a
millimeter wave frequency range, or any combination thereof.
5. The system of claim 1, wherein the processor is configured to
determine the first value of the one or more operational
characteristics of the combustion system by analyzing a plurality
of frequency components of the indication of the detectable
radiation.
6. The system of claim 1, wherein the processor is configured to
derive the output when the first value is above or below a
configurable threshold value.
7. The system of claim 1, wherein the processor is configured to:
utilize a spectral analysis technique to analyze frequency
components of the indication of the detectable radiation, wherein
the frequency components comprise indications of an intensity of a
flame of the combustion system as the first value; and derive the
output as a fuel flow value as the second value.
8. The system of claim 1, wherein the combustion system is
configured to couple to a gas turbine system, a boiler system, or a
combination thereof.
9. The system of claim 1, comprising a controller configured to
receive the output and to execute a control action for controlling
at least one component coupled to the combustion system based on
the output.
10. The system of claim 9, wherein the controller is configured to
execute the control action comprising actuating an actuator, and
wherein the actuator is configured to control a flow of fuel into
the combustion system.
11. A non-transitory computer-readable medium having computer
executable code stored thereon, the code comprising instructions
to: receive an indication of a detectable radiation associated with
a combustion system, wherein the detectable radiation comprises
multidimensional granular data associated with an operation of the
combustion system; determine a first value of one or more
operational characteristics of the combustion system based at least
in part on the indication of the detectable radiation; and derive
an output, wherein the output comprises a second value derived
based on the first value of the one or more operational
characteristics to adjust the first value thereto.
12. The non-transitory computer-readable medium of claim 11,
wherein the code comprises instructions to receive the indication
of the detectable radiation within an x-ray frequency range, an
ultraviolet frequency range, a visible light frequency range, an
infrared frequency range, a gamma frequency range, a microwave
frequency range, a radio frequency (RF) frequency range, a
millimeter wave frequency range, or any combination thereof.
13. The non-transitory computer-readable medium of claim 11,
wherein the code comprises instructions to determine the first
value of the one or more operational characteristics of the
combustion system by analyzing a plurality of frequency components
of the indication of the detectable radiation.
14. The non-transitory computer-readable medium of claim 11,
wherein the code comprises instructions to derive the output when
the first value is above or below a configurable threshold
value.
15. The non-transitory computer-readable medium of claim 11,
wherein the code comprises instructions to: utilize a spectral
analysis technique to analyze frequency components of the
indication of the detectable radiation, wherein the frequency
components comprise indications of an intensity of a flame of the
combustion system as the first value; and derive the output as a
fuel flow value as the second value.
16. The non-transitory computer-readable medium of claim 11,
wherein the code comprises instructions to transmit the output to a
controller.
17. The non-transitory computer-readable medium of claim 16,
wherein the code comprises instructions to instruct the controller
to execute a control action for controlling at least one component
coupled to the combustion system.
18. A system, comprising: a plurality of sensors configured to
detect electromagnetic radiation associated with a combustor of a
turbine system; a data analytics system configured to: receive an
indication of the electromagnetic radiation, wherein the indication
of the electromagnetic radiation comprises multidimensional
granular data associated with an operation of the combustor;
determine a first value of one or more operational characteristics
of the combustor based at least in part on the indication of the
electromagnetic radiation; and derive an output, wherein the output
comprises a second value derived based on the first value of the
one or more operational characteristics to adjust the first value
thereto; and a controller configured to receive the output and to
generate a control command based at least in part on the
output.
19. The system of claim 18, wherein the plurality of sensors
comprises a plurality of optical detectors configured to detect
electromagnetic radiation associated with a flame of the
combustor.
20. The system of claim 18, wherein the controller is configured to
generate the control command to adjust an inlet airflow, an exit
airflow, an exit pressure, an inlet fuel flow, or a combination
thereof, of the turbine system.
Description
BACKGROUND
[0001] The invention relates generally to combustion systems, and
more specifically to systems and methods for improved and advanced
control of combustion systems.
[0002] Combustion systems within gas turbine systems, boiler
systems (e.g., coal fired boiler systems), or other similar systems
may include a number of sensors to measure and/or detect the
various operating parameters of the combustion systems, and by
extension, the operating parameters of the systems (e.g., gas
turbine systems, boiler systems, and so forth) including the
combustion systems. However, these sensors may be limited in
detecting certain data of the combustion systems. Moreover, the
data detected by more advanced sensors may require more advanced
data converters and/or data processors. It may be useful to provide
systems to improve data detection and control of combustion
systems.
BRIEF DESCRIPTION
[0003] Certain embodiments commensurate in scope with the
originally claimed invention are summarized below. These
embodiments are not intended to limit the scope of the claimed
invention, but rather these embodiments are intended only to
provide a brief summary of possible forms of the invention. Indeed,
the invention may encompass a variety of forms that may be similar
to or different from the embodiments set forth below.
[0004] A system includes an analytics system including a processor
configured to receive an indication of a detectable radiation
associated with a combustion system. The detectable radiation
includes multidimensional granular data associated with an
operation of the combustion system. The processor is configured to
determine a first value of one or more operational characteristics
of the combustion system based at least in part on the indication
of the detectable radiation, and to derive an output. The output
includes a second value derived based on the first value of the one
or more operational characteristics to adjust the first value
thereto.
[0005] A non-transitory computer-readable medium having code stored
thereon, the code includes instructions to receive an indication of
a detectable radiation associated with a combustion system. The
detectable radiation includes multidimensional granular data
associated with an operation of the combustion system. The code
includes instructions to determine a first value of one or more
operational characteristics of the combustion system based at least
in part on the indication of the detectable radiation, and to
derive an output. The output includes a second value derived based
on the first value of the one or more operational characteristics
to adjust the first value thereto.
[0006] A system includes a plurality of sensors configured to
detect electromagnetic radiation associated with a combustor of a
turbine system, and a data analytics system configured to receive
an indication of the electromagnetic radiation. The indication of
the electromagnetic radiation includes multidimensional granular
data associated with an operation of the combustor. The data
analytics system is configured to determine a first value of one or
more operational characteristics of the combustor based at least in
part on the indication of the electromagnetic radiation, and to
derive an output. The output includes a second value derived based
on the first value of the one or more operational characteristics
to adjust the first value thereto. The system includes a controller
configured to receive the output and to generate a control command
based at least in part on the output.
DRAWINGS
[0007] These and other features, aspects, and advantages of the
present invention will become better understood when the following
detailed description is read with reference to the accompanying
drawings in which like characters represent like parts throughout
the drawings, wherein:
[0008] FIG. 1 is a block diagram of an embodiment of a gas turbine
system including a combustion system, in accordance with present
embodiments;
[0009] FIG. 2 is a diagram of an embodiment of the system of FIG.
1, including an analytics system, in accordance with present
embodiments; and
[0010] FIG. 3 is a flowchart illustrating an embodiment of a
process useful in providing improved control of operational
parameters of the combustion system of FIG. 1, in accordance with
present embodiments.
DETAILED DESCRIPTION
[0011] One or more specific embodiments of the invention will be
described below. In an effort to provide a concise description of
these embodiments, all features of an actual implementation may not
be described in the specification. It should be appreciated that in
the development of any such actual implementation, as in any
engineering or design project, numerous implementation-specific
decisions must be made to achieve the developers' specific goals,
such as compliance with system-related and business-related
constraints, which may vary from one implementation to another.
Moreover, it should be appreciated that such a development effort
might be complex and time consuming, but would nevertheless be a
routine undertaking of design, fabrication, and manufacture for
those of ordinary skill having the benefit of this disclosure.
[0012] When introducing elements of various embodiments of the
invention, the articles "a," "an," "the," and "said" are intended
to mean that there are one or more of the elements. The terms
"comprising," "including," and "having" are intended to be
inclusive and mean that there may be additional elements other than
the listed elements.
[0013] Present embodiments relate to systems and methods useful in
providing improved control of combustion systems (e.g., combustions
systems in gas turbine systems) in real-time. Specifically, one or
more electromagnetic detectors (e.g., optical detectors,
transducers, spectrometers, and so forth) in conjunction with an
analytics system may be provided as part of a closed-loop control
system. The electromagnetic detectors in conjunction with the
analytics system may allow for improved control of gas turbine
and/or combustion system operational parameters of interest such as
the combustion dynamics (e.g., pressure, flame intensity), heat
rate, gas emission dynamics, maintenance factor, and so forth to
improve the operational characteristics of the gas turbine and/or
combustion system. The electromagnetic detectors in conjunction
with the analytics system may also provide for better prognostics
and diagnostics of the gas turbine and/or combustion systems that
may be otherwise unavailable using only observational devices such
as infrared cameras. Although discussed primarily in relation to a
gas turbine system, it should be appreciated that the present
embodiments may be applicable to any system including combustion
systems and/or burner systems such as coal-fired boiler systems or
other similar systems.
[0014] With the foregoing in mind, it may be useful to describe an
embodiment of a gas turbine system, such as an example gas turbine
system 10 illustrated in FIG. 1. In certain embodiments, the gas
turbine system 10 may include a gas turbine 12, a control system
14, and a fuel supply system 16. As illustrated, the gas turbine 12
may include a compressor 20, combustion chambers 22, fuel nozzles
24, a turbine 26, and an exhaust section 28. During operation, the
gas turbine 12 may take in air 30 into the compressor 20. The
compressor 20 may then compress and move the air 30 to the
combustion chambers 22 (e.g., chambers including a number of
combustors or burners).
[0015] In certain embodiments, the combustion chambers 22, using
the fuel nozzles 24, may take in fuel 31 that mixes with the now
compressed air 30 creating an air-fuel mixture. The air-fuel
mixture may combust within the combustion chambers 22 to generate
hot combustion gases, which flow downstream into the turbine 26 to
drive the turbine 26. For example, the combustion gases may move
through the turbine 26 to drive one or more stages of blades of the
turbine 26, which may in turn drive rotation of a shaft 32. The
shaft 32 may connect to a load 34, which may include, for example,
a generator to convert the output of the shaft 32 into electric
power. In certain embodiments, upon passing through the turbine 26,
the hot combustion gases may vent into the environment as exhaust
gases 36 via the exhaust section 28. The exhaust gas 36 may include
major species such as, for example, carbon dioxide (CO.sub.2),
nitrogen (N.sub.2), water vapor (H.sub.2O), and oxygen (O.sub.2),
as well as minor species (e.g., pollutants) such as, for example,
carbon monoxide (CO), nitrogen oxides (NO.sub.x), unburned
hydrocarbons (UHC), and sulfur oxides (SO.sub.x).
[0016] In certain embodiments, the control system 14 may include a
controller 38 communicatively coupled to an analytics system 40,
and a number of sensors 42. The analytics system 40 may receive
data relating to one or more components of the gas turbine system
12 from the sensors 42, and generate and transmit outputs to the
controller 38 based on an analysis of the sensor 42 data. For
example, as will be further appreciated, the analytics system 40
may use the sensor 42 data to determine, for example, CO.sub.2
levels in the exhaust gas 36, pollutant (e.g., CO, NO.sub.x, UHC,
SO.sub.x) levels in the exhaust gas 36, carbon content in the fuel
31, temperature of the fuel 31, temperature, pressure, clearance
(e.g., distance between stationary and rotating components), flame
temperature or intensity, vibration, combustion dynamics (e.g.,
fluctuations in pressure, flame intensity, and so forth), and load
data from load 34.
[0017] Turning now to FIG. 2, which illustrates an embodiment of
the control system 14. In certain embodiments, the sensors 42 may
include any of a number of electromagnetic radiation detectors
(e.g., antennas, transducers, spectrometers, optical detectors, and
so forth) that may be used to detect radiation 43 (e.g., flame
and/or light radiation, intensity, and so forth) of the combustion
chambers 22 and/or the fuel nozzles 24 and individual combustors
(e.g., can combustors, burners) of the combustion chambers 22. For
example, in certain embodiments, the sensors 42 may include
photodetectors (e.g., colorimeters, flame sensors, wavefront
sensors, photodiodes, infra-red sensors, and so forth), antennas
(e.g., single-element, linear array, phased array), acoustic
transducers (e.g., ultrasonic transducers), or any such devices
useful in detecting the radiation 43. Thus, the sensors 42 may be
useful in sensing the radiation 43 across various frequency ranges
(e.g., across the electromagnetic spectrum) including, for example,
frequencies within the x-ray, ultraviolet, visible, infrared,
microwave, radio frequency (RF), gamma, millimeter wave ranges, and
the like.
[0018] As further illustrated in FIG. 2, in certain embodiments,
the radiation 43 detected by the sensors 42 may be transmitted to
the analytics system 40, in which certain operational
characteristics and/or parameters may be determined by the
analytics system 40 based on the output of the sensors 42. For
example, based on the output of the sensors 42, the analytics
system 40 may derive chemical composition of gases of the exhaust
gas 36, wear patterns inside of the combustion chambers 22, thermal
distribution, physical geometry, pollutant levels in the exhaust
gas 36, carbon content in the fuel 31, temperature of the fuel 31,
temperature, pressure, flame temperature, vibration, combustion
dynamics such as fluctuations in pressure, flame intensity, and so
forth, of the combustion chambers 22 and/or the exhaust section 28.
Specifically, by including the sensors 42 to detect the radiation
43, the sensors 42 may provide multidimensional granular data
(e.g., three-dimensional data) of the combustion chambers 22 to the
analytics system 40. Specifically, while certain
non-electromagnetic sensors may provide a bulk average of data and
other associated operational properties, the sensors 42 may provide
granular data to, for example, the analytics system 40. The
analytics system 40 may parse and delineate various regions of a
field of the granular data (e.g., specific data of interest
extracted from a larger portion of data). In this manner, the
analytics system 40 may generate an output to the controller 38 to
control one or more operational parameters of particular interest.
For example, should one burner (e.g., can combustor) of the
combustion chambers 22 burn much hotter than other burners of the
combustion chambers 22, the analytics system 40 may identify the
problematic burner before the burner is allowed to adversely impact
the operation of the gas turbine system 12. Such multidimensional
granular data may be otherwise undetectable when using less optimal
devices such as infrared cameras or other similar devices (e.g.,
devices incapable of measuring the radiation 43).
[0019] Indeed, the analytics system 40 may be any hardware system,
or a combination of a hardware and software system, suitable for
analyzing, deriving, and/or modeling combustion data, exhaust
emissions data, and/or other data relating to the combustion
chambers 22 of the gas turbine 12. As illustrated, the analytics
system 40 may include one or more processors 44, a memory 46 (e.g.,
storage), input/output (I/O) ports (e.g., one or more network
interfaces 48), and so forth, useful in implementing the techniques
described herein. Particularly, the analytics system 40 may include
code or instructions stored in a non-transitory machine-readable
medium (e.g., the memory 46 and/or storage) and executed, for
example, by the one or more processors 44 that may be included in
the analytics system 40. Additionally, the analytics system 40 may
include a network interface 48, which may allow communication
between the analytics system 40 and the controller 38 and sensors
42 via a personal area network (PAN), a local area network (LAN)
(e.g., Wi-Fi), a wide area network (WAN), a physical connection
(e.g., an Ethernet connection), and/or the like.
[0020] In certain embodiments, the analytics system 40 may receive
and/or derive granular three-dimensional (3-D) data (e.g.,
combustion data, exhaust emissions data, or other data relating to
non-homogenous phenomena) based on the inputs received from the
sensors 42. For example, as previously noted, the analytics system
40 may used the data collected by the sensors 42 to derive certain
composition of gases of the exhaust gas 36, wear patterns inside of
the combustion chambers 22, thermal distribution of the flame of
the combustion chambers 22, inner geometry of the individual
combustors (e.g., individual can combustors), pollutant levels in
the exhaust gas 36, carbon content in the fuel 31, temperature of
the fuel 31, flame temperature, combustion dynamics such as
fluctuations in pressure, flame intensity, and so forth.
[0021] Thus, in certain embodiments, the analytics system 40 may
use Fourier analysis (e.g., Fast Fourier Transforms [FFTs],
spectral analysis), image recognition techniques (e.g., pattern and
gradient matching, optical character recognition), digital
filtering techniques (e.g., Kalman filtering and/or other adaptive
filtering), and similar signal processing techniques to extract
and/or derive real-time or near real-time data from the input
signals of the sensors 42 relating to the operation of the
combustion chambers 22, and by extension, the operation of the gas
turbine 12. Specifically, the analytics system 40 may perform
various spectral analyses of the frequency components (e.g.,
frequency harmonics, power, frequency and/or signal distortion, and
similar spectral components) to derive certain operational
characteristics and/or parameters of the combustion chambers 22
and/or the gas turbine system 12. For example, in one embodiment,
based on the inputs received via the sensors 42, the analytics
system 40 may provide for improved detection and analysis of
pollutant (e.g., CO, NO.sub.x, UHC, SO.sub.x) levels in the flame
of the combustion chambers 22 and/or exhaust section 28, which, if
left to persist, may result in undesirable variations in exhaust
section 28 temperature, the power output of the gas turbine 12, as
well as the heat rate of the gas turbine 12. Specifically, by the
analytics system 40 deriving the pollutant (e.g., CO, NO.sub.x,
UHC, SO.sub.x) levels in the flame of the combustion chambers 22,
certain operating conditions such as, for example, lean blowouts
(LBOs) (e.g., loss of flame due to a decrease in air-fuel ratio) in
one or more individual combustors (e.g., can combustors) of the
combustion chambers 22 may be detected with a higher degree a
certainty.
[0022] Similarly, in other embodiments, the analytics system 40 may
use probabilistic techniques, such as statistical methods (e.g.,
linear regression, non-linear regression, ridge regression, data
mining) and/or artificial intelligence models (e.g., expert
systems, fuzzy logic, support vector machines [SVMs], logic
reasoning systems) to improve certainty in prognosis and/or
diagnostics of the operating conditions of the combustion chambers
22, and by extension, the gas turbine 12. For example, certain
knowledge of the gas turbine system 12 exhaust section 28 plane
emissions may be analyzed to detect conditions possibly leading to
an LBO, such as detecting that an outlying combustor of the
combustion chambers 22 is not synchronized with other combustors of
the combustion chambers 22.
[0023] As further illustrated in FIG. 2, in certain embodiments,
the analytics system 40 may derive one or more outputs (e.g., in
real-time or near real-time) based upon the operational
characteristics and/or parameters derived from the data received
via the sensors 42. The one or more outputs may include, for
example, data values (e.g., target values, setpoint values) to vary
(e.g., in real-time or near real-time) the operational
characteristics of the combustion chambers 22 derived by the
analytics system 40. In some embodiments, the analytics system 40
may derive an output to correct any of a number of non-homogeneous
phenomena (e.g., fluctuations in pressure and flame intensity, heat
rate, pollutant levels in the flame, thermal radiation, and so
forth) associated with the combustion chambers 22. The analytics
system 40 may transmit the one or more outputs to the controller 38
to execute one or more control actions. For example, the controller
38 may output a control signal to control one or more control
elements 50 (e.g., actuators, valves, trim valves) to execute a
control action to alter operating parameters including, for
example, compressor 20 inlet airflow, compressor 20 exit airflow,
flow of fuel 31 to the combustion chambers 22, and so forth, to
adjust and stabilize the flame output of the combustion chambers
22, and by extension, the power output of the gas turbine 12.
[0024] Turning now to FIG. 3, a flow diagram is presented,
illustrating an embodiment of a process 52 useful in providing
improved control of combustion systems in real-time, by using, for
example, the analytics system 40 in conjunction with the controller
38 included in the gas turbine system 10 depicted in FIG. 1. The
process 52 may include code or instructions stored in a
non-transitory computer-readable medium (e.g., the memory 46) and
executed, for example, by the one or more processors 44 included in
the analytics system 40 and/or processors included within the
controller 38. The process 52 may begin with the analytics system
40 receiving (block 54) system operating parameters of the gas
turbine 12. As previously discussed, the analytics system 40 may
receive one or more indications of the operating parameters of the
combustion chambers 22 detected via the sensors 42 (e.g.,
electromagnetic radiation detectors). For example, as previously
discussed, the sensors 42 may detect the radiation 43 (e.g.,
electromagnetic radiation) emitted, for example, by the flame of
the combustion chambers 22.
[0025] The process 52 may then continue with the analytics system
40 analyzing (block 56) and/or deriving from, the system operating
parameters for specific parameters of interest. For example, as
noted above with respect to FIG. 2, the analytics system 40 may
derive from the radiation 43 detected by the sensors 42 operational
characteristics and/or parameters including, for example, CO.sub.2
levels in the exhaust gas 36, pollutant (e.g., CO, NO.sub.x, UHC,
SO.sub.x) levels in the flame of the combustion chambers 22 and/or
exhaust gas 36, carbon content in the fuel 31, temperature of the
fuel 31, certain combustion dynamics (e.g., fluctuations in
pressure, flame intensity) of the combustion chamber 22, heat rate
of the gas turbine 12, maintenance factor (e.g., maintenance
intervals) of the gas turbine 12, and so forth. The analytics
system 40 may then calculate (block 58) one or more outputs based
on the analysis and/or derivation of the specific operating
parameters of interest. Specifically, the analytics system 40 may
calculate one or more target data values and/or setpoint values for
the specific operating parameters of interest to be adjusted
thereto. That is, the analytics system 40 may parse and delineate
various regions of a field of data and derive an output to correct
any of number non-homogeneous phenomena associated with the
combustion chambers 22 with a high degree of specificity. In this
manner, the analytics system 40 may generate an output derived
and/or characterized to reflect one or more operational parameters
of particular interest based on the data received via the sensors
42. As previously noted, such techniques may not be possible when
using less optimal devices such as infrared cameras, less advanced
controllers, or other similar devices (e.g., devices incapable of
measuring and processing the radiation 43).
[0026] The calculated one or more outputs may be then used by the
controller 38 to generate (block 59) and execute one or more
corresponding control commands. Indeed, the one or more calculated
outputs may be used by the controller 38 to adjust (block 60) one
or more control elements (e.g., final control elements such as
actuators, valves, and the like) coupled to the combustion chambers
22 or other components of the gas turbine 12. For example, one or
more actuator and/or control valve signals may be generated by the
controller 38 to control, for example, the fuel flow to the
combustion chambers 22, and by extension, the fuel (e.g., fuel 31)
flow to the gas turbine system 12.
[0027] Technical effects of the present embodiments include systems
and methods useful in providing improved control of combustion
systems (e.g., combustions systems in gas turbine systems) in
real-time. Specifically, one or more electromagnetic detectors
(e.g., optical detectors, transducers, spectrometers, and so forth)
in conjunction with an analytics system may be provided as part of
a closed-loop control system. The electromagnetic detectors in
conjunction with the analytics system may allow for improved
control of gas turbine and/or combustion system operational
parameters of interest such as the combustion dynamics (e.g.,
pressure, flame intensity), heat rate, gas emission dynamics,
maintenance factor, and so forth to improve the operational
characteristics of the gas turbine and/or combustion system. The
electromagnetic detectors in conjunction with the analytics system
may also provide for better prognostics and diagnostics of the gas
turbine and/or combustion systems that may be otherwise unavailable
using only observational devices such as infrared cameras.
[0028] This written description uses examples to disclose the
invention, including the best mode, and also to enable any person
skilled in the art to practice the invention, including making and
using any devices or systems and performing any incorporated
methods. The patentable scope of the invention is defined by the
claims, and may include other examples that occur to those skilled
in the art. Such other examples are intended to be within the scope
of the claims if they have structural elements that do not differ
from the literal language of the claims, or if they include
equivalent structural elements with insubstantial differences from
the literal language of the claims.
* * * * *