Systems and methods for reducing exhaust emission visibility in gas turbine systems

Abstract

To provide a system and method for decreasing exhaust emissions and reducing corresponding visibility of such emissions in a gas turbine system.SOLUTION: An emissions control system for a gas turbine system includes an emissions control fluid supply, a sensor, a valve, and a controller. The emissions control fluid supply has conduits configured to couple to fluid pathways of the gas turbine system, which are fluidly coupled to a flow path of an exhaust gas from a combustor through a turbine of the gas turbine system. The sensor is configured to obtain feedback of parameters of the gas turbine system, which are indicative of visibility of emissions of the exhaust gas. The valve is coupled to the emissions control fluid supply. The controller is communicatively coupled to the sensor and the valve, so that, in response to the feedback, the controller adjusts the valve to adjust a flow of the reducing agent from the emissions control fluid supply so as to reduce the visibility of the emissions of the exhaust gas.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The subject matter disclosed herein relates to gas turbine systems and, more particularly, to systems and methods for reducing the visibility of exhaust emissions such as a yellow plume. [Background technology]

[0002] A gas turbine system may include a gas turbine engine having a compressor, a combustor, and a turbine driven by combustion gases from the combustor. Combustion of fuel in the combustor produces various exhaust emissions, such as nitrogen oxides (NOx), sulfur oxides (SOx), particulate matter, and other pollutants. Unfortunately, some of these exhaust emissions may be visible (e.g., a yellow plume) when emitted into the atmosphere from a gas turbine system under some operating conditions, such as during start-up, when downstream emission control systems (e.g., carbon monoxide (CO) and selective catalytic reduction (SCR) catalysts) may not be fully functional. Therefore, stricter emissions regulations and community awareness in some parts of the world require a reduction in the concentration of exhaust emissions and the corresponding visibility of such emissions emitted into the atmosphere. Summary of the Invention

[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; 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] One embodiment of the disclosed subject matter includes an emissions control system for a gas turbine system having a reductant supply source, at least one sensor, at least one valve, and a controller. The reductant supply source has one or more conduits configured to couple to one or more fluid paths of the gas turbine system, the one or more fluid paths being fluidly coupled to a flow path of exhaust gases from a combustor through a turbine of the gas turbine system. The at least one sensor is configured to obtain feedback of one or more parameters of the gas turbine system, the one or more parameters being indicative of emissions visibility in the exhaust gases. The at least one valve is coupled to the reductant supply source. The controller is communicatively coupled to the at least one sensor and the at least one valve, and in response to the feedback, the controller adjusts the at least one valve to adjust the flow of reductant to reduce emissions visibility in the exhaust gases.

[0005] One embodiment of the disclosed subject matter includes a controller configured to communicatively couple to at least one sensor and at least one valve of an emissions control system of a gas turbine system. The controller is configured to receive feedback of one or more parameters of the gas turbine system, the one or more parameters indicative of a visibility of emissions in exhaust gases from the gas turbine system. In response to the feedback, the controller adjusts at least one valve to adjust a flow of reductant from a reductant source to one or more fluid paths of the gas turbine system to reduce the visibility of emissions in the exhaust gases. The one or more fluid paths are fluidly coupled to a flow path of exhaust gases from a combustor through a turbine of the gas turbine system.

[0006] One embodiment of the disclosed subject matter includes a method that includes receiving feedback of one or more parameters of a gas turbine system via at least one sensor of an emissions control system, the one or more parameters indicative of a visibility of emissions in exhaust gases from the gas turbine system. The method also includes adjusting, via a controller of the emissions control system, at least one valve to adjust a flow of reductant from a reductant source to one or more fluid paths of the gas turbine system to reduce the visibility of emissions in the exhaust gases, the one or more fluid paths fluidly coupled to a flow path of exhaust gases from a combustor through a turbine of the gas turbine system.

[0007] These and other features, aspects, and advantages of the present system will be better understood from the following detailed description when read in conjunction with the accompanying drawings, in which like reference numerals represent like parts throughout. [Brief explanation of the drawings]

[0008] [Figure 1] FIG. 1 is a block diagram of an embodiment of a gas turbine system having an emissions control system that reduces exhaust visibility. [Figure 2] 2 is a partial cross-sectional view of an embodiment of the turbine of FIG. 1 illustrating cooling flow along fluid paths inside the turbine. [Figure 3] 2 is a diagram of an embodiment of the gas turbine system of FIG. 1 illustrating an embodiment of an emissions control system having a valve control system and a flow meter system. [Figure 4] FIG. 2 is a diagram of an embodiment of the gas turbine system of FIG. 1 illustrating an embodiment of an emissions control system with various extraction points in the compressor and injection points in the turbine and exhaust duct. [Figure 5] FIG. 2 is a diagram of an embodiment of the gas turbine system of FIG. 1 illustrating an embodiment of an emissions control system having an ammonia solution train and a reducing solution train. [Figure 6]6 is a diagram of an embodiment of the gas turbine system of FIG. 1 illustrating an embodiment of an emissions control system having the ammonia solution train and the reducing solution train of FIG. 5 coupled to a common fluid circuit. [Figure 7] 6 is a diagram of an embodiment of the gas turbine system of FIG. 1 illustrating an embodiment of an emissions control system having the ammonia solution train and the reducing solution train of FIG. 5 coupled to different fluid circuits. [Figure 8] 1 is a flow chart of an embodiment of a process for reducing exhaust emissions and exhaust emission visibility in a gas turbine system. DETAILED DESCRIPTION OF THE INVENTION

[0009] One or more specific embodiments of the present system are described below. In an effort to provide a concise description of these embodiments, not all features of an actual implementation are described herein. It is understood that in the development of an actual implementation, such as an engineering or design project, many implementation-specific decisions must be made to achieve the developer's particular objectives, including, for example, meeting system-related and business-related constraints, and that these constraints may vary from implementation to implementation. Moreover, it is understood 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 in the art having the benefit of this disclosure.

[0010] 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 element. The terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements other than the listed elements.

[0011] Disclosed embodiments are directed to systems and methods for reducing exhaust emissions and the corresponding visibility of such exhaust emissions in gas turbine systems. Exhaust emissions may include any undesirable pollutants or emissions visible in the exhaust emitted from the gas turbine system. For example, exhaust emissions may include nitrogen oxides (NOx), sulfur oxides (SOx), particulate matter, and other pollutants. Visible emissions may have various colors depending on the type and concentration of the exhaust emissions. For example, when the concentration of nitrogen oxides (e.g., nitrogen dioxide (NO2)) exceeds a threshold level, visible emissions may be yellow (e.g., a yellow plume).

[0012] Disclosed embodiments include emissions control systems and related methods that reduce the concentration and visibility of such exhaust emissions, for example, by supplying a reductant to one or more fluid paths (e.g., cooling circuits or bypass circuits) of a gas turbine engine. For example, a cooling circuit may extend through various components of a gas turbine system that typically heat up during operation and / or benefit from cooling to improve performance or extend component life. For example, a cooling circuit may include one or more cooling passages that extend along and / or through portions of a combustor (e.g., framework, combustor liner, head end, etc.), rotating components (e.g., shaft, bearings, seals, etc.), portions of a turbine (e.g., rotating turbine blades, stationary turbine vanes, turbine nozzle, turbine wheel, turbine casing, etc.), or any other component of the gas turbine system exposed to the heat of combustion or exhaust gases. A bypass circuit may include a bypass line coupled to a compressor (e.g., one or more compressor stages) and other portions of the gas turbine system (e.g., one or more turbine stages of a turbine).

[0013] The reductant flows through these fluid paths and eventually enters the exhaust gas flow path, where the reductant can then help reduce the concentration of exhaust substances and the corresponding visibility of such exhaust substances. By using the fluid paths of a gas turbine engine, emissions control systems and methods can be retrofitted to exhaust gas turbine systems by using existing fluid paths. The use of fluid paths can also improve the distribution and mixing of the reductant in the exhaust gas and can increase the residence time of the reductant in the exhaust gas upstream of one or more additional emissions control systems, such as a selective catalytic reduction (SCR) system located in the exhaust duct downstream of the turbine.

[0014] FIG. 1 is a block diagram of an embodiment of a gas turbine system 10 having an emissions control system 11 configured to reduce exhaust emission levels and exhaust emission visibility (e.g., nitrogen oxides (NOx), sulfur oxides (SOx), particulate matter, and other pollutants). In the illustrated embodiment, the gas turbine system 10 includes a turbine engine 12 coupled to a load 14, such as a generator. In one embodiment, the turbine engine 12 may be a 7FA gas turbine engine manufactured by General Electric Company of Greenville, South Carolina. The turbine engine 12 includes an air intake 16, a compressor 18, one or more fuel nozzles 20, a combustor 22, a turbine 24, and an exhaust duct 26. The exhaust duct 26 may include a horizontal duct portion 25 and a vertical stack portion 27. However, the duct 26 may extend in any direction to an exhaust outlet.

[0015] As will be appreciated, the compressor 18 may include any number of stages, e.g., 1 to 20, of compressor blades rotatable within a shroud. Similarly, the turbine 24 may include any number of stages, e.g., 1 to 20, of turbine blades rotatable within a shroud. The turbine engine 12 may also include multiple compressor 18-turbine 24 combinations, such as those found in a twin-screw aeroderivative turbine engine 12. The combustor 18 may also include a single combustor (e.g., an annular combustor) or multiple combustors (e.g., 2 to 12 combustor cans arranged circumferentially about the axis of rotation of the turbine engine 12) arranged in any manner, including different designs not mentioned herein.

[0016] During operation, the turbine engine 12 channels air 28 through the air intake 16 and the compressor 18, which generates compressed air 30 for combustion and cooling flows. In the illustrated embodiment, fuel nozzles 20 within the combustor 22 receive at least a portion of the compressed air 30 and fuel 32, which are then directed to a combustion zone of the combustor 22, as indicated by arrows 34. A portion of the compressed air 30 may also be channeled along the combustor 22 and / or turbine 24 for cooling purposes. Inside the combustor 22 (e.g., inside a combustion liner), the air 30 and fuel 32 mix and combust to generate hot combustion products, which then enter and flow through the turbine 24 and exhaust duct 26. These combustion gases drive turbine blades to rotate within the turbine 24, thereby driving a shaft 36 to rotate the compressor 18 and load 14.

[0017] The emission control system 11 includes an emission control unit 38 coupled to an emission control fluid supply system 40 and a monitoring system 42. The emission control unit 38 includes a processor 46, a memory 48, and a controller 44 having instructions 49 stored in the memory 48 and executable by the processor 46 to control the emission control fluid supply system 40 based on feedback from the monitoring system 42. The emission control fluid supply system 40 includes one or more emission control fluid sources 50, one or more flow control units 52, and one or more fluid supply conduits 54. The emission control fluid source 50 may include one or more tanks or storage containers configured to hold and supply an emission control fluid, such as a reducing agent. For example, the emission control fluid source 50 (e.g., a reducing agent source) may include a tank or storage container of a reducing agent, such as ammonia, ethanol, alcohol, and / or hydrogen. The flow control unit 52 may include one or more valves, pressure regulators, flow meters or flow regulators, or any combination thereof. The flow control unit 52 may include an electrical actuator that is controlled by the emissions control unit 38. In the following description, the flow control unit 52 may be referred to as a valve, although any reference to a valve may include other types of flow control units discussed above.

[0018] The fluid supply conduit 54 may be coupled to one or more fluid paths 56 of the gas turbine system 10 such that the emission control system 11 can supply one or more of an emission control fluid (e.g., a reductant) to the fluid paths to reduce the level and visibility of exhaust emissions. Additionally, the monitoring system 42 may include one or more sensors 58, denoted by S, configured to obtain sensor feedback of one or more parameters of the gas turbine system 10 such that the emission control system 11 can adjust (e.g., increase or decrease) the supply of the emission control fluid (e.g., a reductant) based on the sensor feedback. The sensors 58 may be distributed throughout the gas turbine system 10 at various locations, such as the compressor 18, the combustor 22, the turbine 24, and the exhaust duct 26.

[0019] The sensor feedback of the one or more operating parameters may include or be indicative of the level of exhaust emissions and / or the visibility of exhaust emissions. For example, the sensor 58 may include an exhaust emissions sensor (e.g., a NOx sensor, a SOx sensor, a particulate matter sensor, and other pollutant sensors) configured to sense the level of emissions in the exhaust gas. As a further example, the sensor 58 may include a visibility sensor, such as an opacity sensor, a color sensor, or a combination thereof. The visibility sensor 58 may be configured to sense the intensity or level of the opacity and / or color of the exhaust emissions in the exhaust gas. Additionally, the sensor 58 may include a pressure sensor, a temperature sensor (e.g., a combustion temperature sensor), a flow sensor (e.g., a fuel flow sensor), a vibration sensor, and / or a fuel composition sensor.

[0020] In response to sensor feedback from sensors 58, emission control system 11 may be configured to (A) selectively supply one or more different emission control fluids (e.g., reductant) by opening or closing flow control units 52 associated with different emission control fluid supplies 50, (B) adjust (e.g., increase or decrease) the flow of selected emission control fluids to one or more fluid paths 56 of gas turbine system 10, and (C) selectively change the target destination of selected emission control fluids within one or more fluid paths 56, as described further below. For example, emission control unit 38 may compare sensor feedback to one or more thresholds (e.g., upper and / or lower thresholds), determine whether the sensor feedback indicates compliance with the one or more thresholds (e.g., falls within or fails to meet an acceptable level), and then adjust emission control fluid supply system 40 based on the indicated compliance or lack of compliance.

[0021] For example, the one or more thresholds may include one or more visibility thresholds (e.g., opacity threshold and / or color threshold), such as a minimum or lower visibility threshold and an upper or maximum visibility threshold. If the sensed visibility (e.g., opacity or color) does not meet the minimum or lower visibility threshold, the emission control unit 38 may selectively increase the flow of emission control fluid to one or more fluid paths 56 to reduce the level of emissions in the exhaust gases and help reduce the visibility of the emissions. If the sensed visibility (e.g., opacity or color) meets the minimum or lower visibility threshold and exceeds the maximum or upper visibility threshold, the emission control unit 38 may selectively retain or reduce the flow of emission control fluid to one or more fluid paths 56 to avoid wasting emission control fluid while maintaining an acceptable level of emissions in the exhaust gases and acceptable visibility of the emissions. In certain embodiments, one or more visibility thresholds (e.g., opacity thresholds and / or color thresholds) may correspond to a yellow plume in the exhaust gas, and thus the thresholds may correspond to the opacity and / or intensity of the yellow color in the yellow plume. However, the disclosed emissions control system 11 may be used for any exhaust substance and associated color in the exhaust gas.

[0022] The fluid path 56 may include external conduits outside the gas turbine engine 12, internal passages or conduits extending through the gas turbine engine 12, or a combination thereof. For example, the fluid path 56 may include one or more compressor bleed conduits 60 coupled to one or more compressor stages of the compressor 18. In the illustrated embodiment, the compressor bleed conduit 60 is coupled to a compressor 18 driven by the gas turbine engine 12. In some embodiments, the compressor bleed conduit 60 may be coupled to a stand-alone compressor (e.g., not driven by the gas turbine engine 12). The emissions control system 11 may selectively open and close valves along the compressor bleed conduit 60 to vary the temperature and pressure of the compressor bleed air extracted from the compressor 18 depending on the extraction location (e.g., compressor stage).

[0023] Alternatively, or in addition to the compressor bleed conduits 60, the fluid path 56 may include one or more coolant sources 59, such as an air source, an inert gas source (e.g., a nitrogen gas source), a recirculated exhaust gas source, or a combination thereof. For example, the coolant source 59 may include one or more storage tanks, a compressor, a pump, or a combination thereof. In some embodiments, the coolant source 59 may include a stand-alone air compressor, such as an air compressor skid, that can supplement or replace compressor bleed air from the compressor 18. The one or more compressor bleed conduits 60 and / or the one or more coolant sources 59 are coupled to one or more distribution conduits 61 configured to fluidly couple to one or more target locations throughout the gas turbine system 10.

[0024] In certain embodiments, distribution conduit 61 includes one or more coolers 63 (e.g., heat exchangers) configured to cool the flow from compressor bleed conduit 60 and / or coolant sources 59. For example, in certain embodiments, at least one of the coolant sources 59 is configured to flow coolant through cooler 63 to transfer heat from compressor bleed air from compressor bleed conduit 60 and / or a different coolant from another of the coolant sources 59. In some embodiments, at least one of the coolant sources 59 is configured to direct coolant to compressor bleed conduit 60 with or without compressor bleed air from compressor bleed conduit 60. Thus, compressor bleed air from compressor bleed conduit 60 and / or coolant from one or more of the coolant sources 59 may be described as coolant sources for other components of gas turbine system 10.

[0025] The aforementioned coolant supplies (e.g., 59, 60) are fluidly coupled to one or more target locations within the gas turbine system 10 via distribution conduits 61, such as one or more coolant conduits 62, 66, 74, and 80, as described below. For example, the fluid path 56 may include one or more coolant conduits 62 fluidly coupled to a bearing cavity or housing having bearings 64 for the shaft 36. These bearing cavities or bearings 64 may be part of the internal cooling circuit of the gas turbine engine 12.

[0026] The fluid path 56 may include one or more coolant conduits 66 fluidly coupled to the combustor 22. For example, the coolant conduits 66 may be fluidly coupled to an internal compressed air flow passage between a combustor liner 68 and a flow sleeve 70 of the combustor 22, an internal cavity of a head end 72 of the combustor 22, an internal cavity of the fuel nozzle 20, or combinations thereof. The aforementioned flow passages or cavities of the combustor 22 may be part of an internal cooling circuit of the gas turbine engine 12.

[0027] The fluid path 56 may also include one or more coolant conduits 74 fluidly coupled to one or more turbine stages of the turbine 24. For example, the coolant conduits 74 may be fluidly coupled to an internal cooling passage between an outer casing 76 and an inner shroud 78 of the turbine 24, as well as one or more internal cooling passages through the turbine stator vanes, turbine rotor blades, turbine wheel, and / or bearing cavities. Again, the aforementioned passages of the turbine 24 may be part of an internal cooling circuit of the gas turbine engine 12.

[0028] Fluid path 56 may also include one or more conduits 80 (e.g., a bypass conduit) fluidly coupled to exhaust duct 26 downstream of turbine 24. Conduit 80 may be coupled to exhaust duct 26 at one or more emission control units 82 upstream, downstream, or inside exhaust duct 26. Exhaust duct 26 may include any number and arrangement (e.g., parallel or serial arrangement) of emission control units 82, such as emission control units 84, 86, 88, 90, and 91. In certain embodiments, emission control system 11 may include a fluid manifold 92 configured to distribute coolant from conduits 61, 80 to exhaust duct 26. Fluid manifold 92 may also be configured to inject other fluids into exhaust duct 26, such as an emission control fluid (e.g., a reductant) supplied by emission control fluid supply system 40.

[0029] Emission control units 82 (e.g., 84, 86, 88, 90, and 91) may include one or more of a heat exchanger, an evaporator, an emission control fluid injection grid, a catalyst (e.g., a selective catalytic reduction (SCR) system), or any combination thereof. For example, in certain embodiments, emission control units 84, 86, 88, 90, and 91 may each include a first injection grid, a heat exchanger (e.g., a high-pressure superheater), a second injection grid, an evaporator (e.g., a high-pressure evaporator), and an SCR system. The first and second injection grids (e.g., 84, 88) may be configured to inject the same or different emission control fluids. For example, the first injection grid (e.g., 84) may be configured to inject a first emission control fluid including ethanol, and the second injection grid (e.g., 88) may be configured to inject a second emission control fluid including ammonia. The emission control fluid may be injected into the exhaust gas in liquid form (e.g., as a spray) via an injection grid, in vapor form (e.g., vaporized with additional heat) via an evaporator, or any combination thereof. For example, the second injection grid 88 may be configured to inject ammonia (e.g., ammonia solution or anhydrous ammonia), or possibly urea, which can ultimately be hydrolyzed / decomposed to produce vaporized ammonia.

[0030] In the illustrated embodiment, the emission control system 11 is configured to supply emission control fluid directly into the exhaust gases via a fluid conduit 54 coupled to the exhaust duct 26 and / or indirectly into the exhaust gases via one or more fluid paths 56 (e.g., a coolant circuit within the gas turbine engine 12) as described above. Thus, based on analysis of sensor feedback from sensors 58 as described above, the emission control unit 38 can selectively adjust one or more flow control units 52 (e.g., valves) to vary the flow of emission control fluid (e.g., reductant) from one or more emission control fluid sources 50 to one or more fluid paths 56, ultimately leading to the exhaust gases and directly to the exhaust duct 26 via the fluid supply conduit 54. In the exhaust duct 26, the supplied emission control fluid can be injected via one or more of the emission control units 82 (e.g., 84, 86, 88, 90, and 91), such as via an injection grid and / or an evaporator as described above. The injection grid may include a plurality of conduits (e.g., parallel conduits) with injection openings or nozzles distributed throughout the exhaust flow path of the exhaust duct 26. A heat exchanger may be used to add heat to the exhaust flow path, thereby helping to evaporate the injected emission control fluid. An evaporator may be used to evaporate the emission control fluid before injecting it into the exhaust flow path. The supply of emission control fluid to one or more fluid paths 56 of the gas turbine engine 12 may improve mixing and residence time of the emission control fluid and exhaust gases, thereby helping to reduce emissions and visibility of the emissions before being discharged from the exhaust duct 26 into the atmosphere.

[0031] 2 is a partial cross-sectional view of an embodiment of the turbine 24 of FIG. 1 illustrating the cooling flow along the fluid path 56 inside the turbine 24. In the illustrated embodiment, the turbine 24 includes a rotor 100 circumferentially surrounded by a stator 102, which includes multiple axially spaced turbine stages 104. In each stage 104, the rotor 100 includes multiple turbine blades 106 mounted in a circumferential arrangement around a wheel 108, and the stator 102 includes multiple stator vanes 110 mounted in a similar circumferential arrangement around a casing 112. The illustrated casing 112 includes the outer casing 76 and the inner shroud 78, which have multiple hangers 114 that support shroud segments 116. In particular, each hanger 114 includes a pair of hooks 118 and 120 that mate with complementary hooks 122 and 124 on the respective shroud segment 116. The shroud segments 116 generally align with the turbine blades 106 of each stage 104 and define a clearance 126. During operation, hot combustion gases flow through each stage 104, thereby driving the rotation of the turbine blades 106 within the respective shroud segments 116.

[0032] In the illustrated embodiment, various components of turbine 24 (e.g., rotor 100, stator 102, blades 106, wheels 108, stator vanes 110, and casing 112) include one or more of the fluid paths 56 described above with reference to FIG. 1 . For example, fluid path 56 may extend through rotor 100, around and / or into wheels 108, and into exhaust flowpath 128, as shown by arrow 130. Fluid path 56 may also extend from rotor 100, through blades 106, and into exhaust flowpath 128, as shown by arrow 132. As indicated by arrows 134, the fluid path 56 may extend through the stator 102 between the outer casing 76 and the inner shroud 78 of the casing 112, through and / or around the shroud segments 116 into the exhaust flow path 128, through the stator vanes 110 into the exhaust flow path 128, and / or through the stator vanes 110 to the rotor 100 and then into the exhaust flow path 128.

[0033] The illustrated fluid path 56 (e.g., represented by arrows 130, 132, and 134) is used by the emission control system 11 to supply one or more emission control fluids (e.g., reductants) to the exhaust flowpath 128 upstream of the exhaust outlet 136 of the turbine 24. As mentioned above, the illustrated fluid path 56 may be part of a cooling circuit (e.g., a turbine cooling circuit) of the gas turbine engine 12. Thus, the emission control system 11 may advantageously supply one or more emission control fluids (e.g., reductants) to the cooling circuit, such that the emission control system 11 can be retrofitted to any new or existing gas turbine engine 12 (e.g., already installed in the field) to improve emission control of the gas turbine system 10.

[0034] 3 is a diagram of an embodiment of gas turbine system 10 illustrating an embodiment of emissions control system 11 having a valve control system 150 and a flow meter system 151 configured to control and monitor flow along fluid path 56. In the following description, reference may be made to an axial direction or axis 152 (e.g., along the longitudinal axis) of gas turbine engine 12, a radial direction or axis 154 extending radially away from the longitudinal axis of gas turbine engine 12, and a circumferential direction or axis 156 extending circumferentially about the longitudinal axis of gas turbine engine 12. Reference may also be made to a downstream direction 158 and an upstream direction 160 relative to the direction of flow through gas turbine engine 12.

[0035] In the illustrated embodiment, each of the compressor bleed conduits 60 coupled to the compressors 18 includes a valve 162 and a flow meter 163 communicatively coupled to the emissions control unit 38. For example, the compressor bleed conduits 60 may be coupled to extraction points 164 at different stages of the compressor 18, thereby allowing different temperatures and pressures of compressor bleed air to be extracted from the compressors 18 into the compressor bleed conduits 60.

[0036] Similarly, each of the coolant conduits 74 coupled to the turbine 24 includes a valve 166 and a flow meter 167 communicatively coupled to the emissions control unit 38. For example, the coolant conduits 74 may be coupled to injection points 168 at different stages of the turbine 24, thereby allowing the same or different coolant flows to be injected into the turbine 24 depending on the temperature at various locations in the turbine 24.

[0037] Similarly, each of the coolant conduits 80 coupled to the exhaust duct 26 includes a valve 170 and a flow meter 171 communicatively coupled to the emissions control unit 38. For example, the coolant conduits 80 can be coupled to injection points 172 at different locations (e.g., different axial locations relative to the downstream direction 158) to inject the same or different coolant flows into the exhaust duct 24 at various locations relative to the emissions control unit 82 (e.g., upstream, downstream, or directly from the unit 82). The illustrated emissions control unit 82 includes a duct burner assembly 174 having multiple duct burners 176 positioned upstream of an SCR system 178. The illustrated injection points 172 are located at a first location upstream of both the duct burner assembly 174 and the SCR system 178, a second location between the duct burner assembly 174 and the SCR system 178, and a third location downstream of both the duct burner assembly 174 and the SCR system 178.

[0038] During operation, as described above, emissions control unit 38 is configured to monitor the flow rate of the coolant stream via flow meters 163, 167, and 171 of flow meter system 151 and selectively adjust valves 162, 166, and 170 of valve control system 150 to control the flow of coolant from compressor 18 to turbine 24 and exhaust duct 26. In addition, emissions control unit 38 is configured to selectively control flow control unit 52 to supply one or more emissions-controlled fluids to one or more fluid paths 56. In certain embodiments, emissions control system 11 is configured to supply one or more emissions-controlled fluids to a common distribution conduit 61 coupled to coolant conduit 74 and / or coolant conduit 80. However, in some embodiments, emissions control system 11 is configured to supply one or more emissions-controlled fluids to separate distribution conduits 61 coupled to each of coolant conduits 74 and / or separate distribution conduits 61 coupled to each of coolant conduits 80.

[0039] Each valve 162, 166, and 170 may be a ball valve, globe valve, butterfly valve, diaphragm valve, or any other valve type that allows for rotary or sliding action to control fluid flow. In some embodiments, valves 162, 166, and / or 170 may be multi-way valves (e.g., three-way valves) or may include injection ports that supply emissions-controlled fluid to one or more fluid paths 56. Flow meters 163, 167, and 171 may include mechanical flow meters (e.g., gear flow meters, turbine flow meters, and / or jet flow meters), pressure-based flow meters (e.g., venturi meters), variable area flow meters, optical flow meters, magnetic flow meters, ultrasonic flow meters, or any combination thereof.

[0040] Valve control system 150 may be operated by controller 44 based at least in part on flow rate information sensed by flow meter system 151. For example, flow rate information obtained from flow meters 163, 167, and 171 may be analyzed by controller 44 to determine operation of valves 162, 166, and 170. In one or more embodiments, controller 44 may automatically control the position of valves 162, 166, and 170 to regulate the flow path (i.e., open the valves to allow flow and close the valves to stop flow). In one or more embodiments, controller 44 determines the flow of emission control fluid (e.g., reductant) through gas turbine system 10. Controller 44 may be located with gas turbine system 10 or may be separately located at a remote location that receives information over a network (e.g., located in an operating room that receives data over a LAN network).

[0041] 4 shows a detailed view of the extraction points 164, the injection points 168 into the turbine 24, the injection points 172 into the exhaust duct 26, and the cooling circuit 200 associated with the gas turbine engine 12. The extraction points 164 may include low-, intermediate-, and high-pressure extraction points configured to obtain a low-pressure air extraction 202, an intermediate-pressure air extraction 204, and a high-pressure air extraction 206 for use in the cooling circuit 200. The injection points 168 may include high-, intermediate-, and low-pressure injection points configured to inject extracted compressor air into a high-pressure turbine section 208, an intermediate-pressure turbine section 210, and a low-pressure turbine section 212 of the turbine 24 for use in the cooling circuit 200. In one or more embodiments, the extraction points 164 and the injection points 168 may not be limited to the pressure rating of the fluid (i.e., low, medium, and high) and may be determined, for example, by the flow rate of the fluid. Additionally, the pressure ratings may be distinct and not limited to low, medium, and high. For example, the labeling can use a particular pressure of the extraction point, a stage of the extraction point, or a combination thereof.

[0042] As described above, the emission control system 11 is configured to supply one or more emission control fluids (e.g., a reductant) to the fluid path 56 of the cooling circuit 200, thereby combining the emission control fluid with the extracted air that is supplied to the injection point 168 into the turbine 24. The cooling circuit 200 may include a series of connected pipes or tubing that interconnect the injection point 168 and the extraction point 164 via valves, fittings, open connections, or any other type of connection. The combination of air and emission control fluid passes through the fluid path 56 inside the turbine 24 (e.g., through the casing, blades, vanes, wheels, etc.) and ultimately flows through the turbine 24 and into the exhaust gases that drive the turbine 24.

[0043] Additionally, emission control system 11 is configured to supply one or more emission control fluids (e.g., reductant) to fluid pathway 56 leading directly to exhaust duct 26, such as injection points 172. In the illustrated embodiment, injection points 172 include a first injection point 214 upstream of duct burner assembly 174, a second injection point 216 between duct burner assembly 174 and SCR system 178, and a third injection point 218 downstream of SCR system 178. Again, emission control system 11 is configured to control the flow of emission control fluid to these injection points 168 and 172 to reduce the level and visibility of exhaust emissions (e.g., nitrogen oxides (NOx), sulfur oxides (SOx), particulate matter, and other pollutants).

[0044] FIG. 5 shows an expanded view of gas turbine system 10 having injection system 240 coupled to exhaust duct 26. In one or more embodiments, the injection system may provide an ammonia solution or anhydrous ammonia, or possibly urea, which may be hydrolyzed or decomposed to produce vaporized ammonia. As described above with reference to FIG. 1 , exhaust duct 24 may include one or more emissions control units 82. In the illustrated embodiment, injection system 240 is part of emissions control unit 82. For example, emissions control unit 82 of injection system 240 may include injection grids 242 and 244, which may also include an SCR system 246, a heat exchanger 248 (e.g., a high-pressure superheater), and an evaporator 250 (e.g., a high-pressure evaporator) within exhaust duct 24. In one or more embodiments, injection grids 242 and 244 may be yellow plume elimination systems (YPES). The injection grids 242 and 244 may utilize various emission control fluids (e.g., reducing agents such as ethanol, ammonia, and / or alcohol) to cool and reduce exhaust emissions in the exhaust gas 128 passing through the injection grids 242 and 244.

[0045] In one or more embodiments, the amount of emission control fluid injected is controlled by a remote operator and / or controller 44 based on sensor feedback and various thresholds as described in detail above. For example, controller 44 may adjust (e.g., increase or decrease) the flow of emission control fluid if the temperature of exhaust gas 128 exceeds or falls below one or more temperature thresholds, if the visibility of exhaust emissions exceeds or falls below one or more visibility thresholds, and / or if the level of exhaust emissions exceeds or falls below one or more emission thresholds. Injection grids 242 and 244 operate during startup, steady state, and shutdown of gas turbine system 10 to reduce or eliminate the levels of exhaust emissions (e.g., NO ) in exhaust gas 128. x , SO x or other pollutants) and the visibility of exhaust emissions.

[0046] In addition to the injection grids 242 and 244, the gas turbine system 10 may utilize an SCR system 246 to reduce the level of exhaust emissions. The SCR system 246 may be used in conjunction with the injection grids 242 and 244 or as a stand-alone system. x As contaminants such as NO flow through the SCR system 246, the catalyst reacts with vaporized ammonia as a reducing agent to produce NO. x The catalyst in the SCR system 246 converts the pollutants into nitrogen and water. The catalyst in the SCR system 246 can be made from various ceramic materials, such as titanium oxide, vanadium, molybdenum, tungsten, zeolite, or various precious metals. Each material may have advantages and disadvantages, such as operating temperature range, thermal durability, and catalytic ability. The SCR system 246 can accept an injection of a reductant to reduce pollutants. The amount of reductant (e.g., vaporized ammonia) can be controlled by the controller 44.

[0047] The SCR system 246 uses high temperatures (>400°F) to xA heat exchanger 248 is configured to add heat to the exhaust gas 128 upstream of the SCR system 246, thereby achieving a high conversion rate of NO to nitrogen and water. x In certain embodiments, the heated fluid (e.g., steam) may circulate through a heat exchanger 248 to transfer heat from the heated fluid to the exhaust gas 128. For example, the heat exchanger 248 may include a superheater (e.g., a high-pressure superheater or a steam drum) of a heat recovery steam generator (HRSG) that recovers heat from the exhaust gas 128 to generate steam for a steam turbine. The heated fluid (e.g., steam) flowing through the heat exchanger 248 may be at or above a target temperature suitable for the SCR system 246, such as a steam temperature of greater than 400°F.

[0048] The gas turbine system 10 may also include a blower 252 coupled to the exhaust duct 26 downstream of the turbine 24. The blower 252 may be an air blower that assists in dilution by providing blowback air across the compressor 18 and the turbine 24. The blower 252 may be linked to a controller 44 that monitors the gas turbine system 10. The controller 44 may adjust the operating speed of the blower 252 or turn the blower 252 on and off based on the requirements of the gas turbine system 10.

[0049] Gas turbine system 10 may also include a reducing solution system 254. The reducing solution system 254 may be connected to gas turbine system 10 via injection grids 242 and 244. In one or more embodiments, the reducing solution system 254 may be connected to gas turbine system 10 via one or more fluid paths 56, such as cooling circuit 200. The connections may be made through pipes, tubing, valves, and other mechanical connection methods. The connections may allow one or more reducing agents to be injected directly into injection grids 242 and 244, one or more fluid paths 56, cooling circuit 200, or SCR system 246. In one or more embodiments, the reducing agent may be delivered through the air cooling and / or extraction lines of gas turbine 24, for example, fluid path 56. The reducing agent may be ammonia (solution, anhydrous, or derived from urea or other ammonia compounds), ethanol, alcohol, or any other type of chemical configured to reduce exhaust emissions.

[0050] In one or more embodiments, the reducing solution system 254 can include an ammonia solution train 256 and a reducing solution train 258. The ammonia solution train 256 can include an ammonia solution tank 260, a pump 262, a valve 264, an evaporator or evaporation tank 266, electric heaters 268 and 270, an air blower 272, and a fluid conduit 274 coupled to the injection grid 244. The pump 262 and the valve 264 are controlled by the controller 44 to adjust (e.g., increase or decrease) the flow of ammonia solution from the ammonia solution tank 260 to the evaporator 266, and the air blower 272 provides an air flow to the evaporator 266. The electric heaters 268 and 270 are configured to heat the air flow and / or the ammonia solution in the evaporator 266, thereby vaporizing the ammonia solution and supplying the vaporized ammonia solution to the injection grid 244.

[0051] The reducing solution train 258 may include a reducing solution tank 280, a pump 282, a valve 284, an evaporator or evaporation tank 286, an electric heater 288, and a fluid conduit 290 coupled to the injection grid 242. The pump 282 and the valve 284 are controlled by the controller 44 to adjust (e.g., increase or decrease) the flow of reducing solution (e.g., ethanol) from the reducing solution tank 280 to the evaporator 286. The electric heater 288 is configured to heat the reducing solution in the evaporator 286, thereby vaporizing the reducing solution and supplying the evaporated reducing solution to the injection grid 242.

[0052] In addition to supplying emission control fluid to exhaust duct 26, reducing solution system 254 may be integrated with or cooperate with emission control fluid supply system 40 of emission control system 11 to supply ammonia solution and / or reducing solution to one or more fluid paths 56.

[0053] 6 is a diagram illustrating one embodiment of a reducing solution system 254 of the emissions control system 11 interacting with the gas turbine system 10. The reducing solution system 254 includes an ammonia solution train 256 and a reducing solution train 258 having tanks 260 and 280 connected to a single control valve 300. The control valve 300 may control the flow rate of each emission control fluid (e.g., ammonia and emissions reductant) through a common fluid conduit to the gas turbine system 10, which may be controlled by the controller 44. The emission control fluids are injected into the gas turbine system 10 at various portions of the fluid path 56, such as the compressor bleed conduit 60, the distribution conduit 61, the coolant conduit 74 coupled to the turbine 24, and / or the coolant conduit 80 coupled to the exhaust duct 26.

[0054] The controller 44 may monitor the exhaust gases 128 and various operating parameters of the gas turbine system 10 to determine an appropriate flow rate of the emission control fluid to reduce the level of exhaust emissions and the visibility of the exhaust emissions (e.g., the level of a yellow plume). The controller 44 may direct at least a portion of the emission control fluid to one or more fluid paths 56 (e.g., the cooling circuit 200) and may also direct at least a portion of the emission control fluid to the exhaust gases 128 in the exhaust duct 26 (e.g., via injection grids 302 and 304). In the illustrated embodiment, the injection grid 302 is disposed in the exhaust duct 26 upstream of the duct burner assembly 174, and the injection grid 304 is disposed in the exhaust duct 26 downstream of the duct burner assembly 174.

[0055] Figure 7 illustrates one embodiment of the reducing solution system 254 of the emissions control system 11 interacting with the gas turbine system 10. The embodiment of Figure 7 is substantially similar to the embodiment of Figure 6, except that a separate control valve 300 is used for each of the tanks 260 and 280, an injection grid 306 is disposed in the exhaust duct 26 downstream of the injection grids 302 and 304, and a heat exchanger 308 (e.g., 248 in Figure 5) is disposed between the injection grids 304 and 306. The controller 44 is communicatively coupled to the control valves 300 such that the controller 44 can independently control the flow of ammonia and emissions reductant from the tanks 260 and 280, respectively.

[0056] The reducing solution train 258 may be connected to a first one of the control valves 300, which is connected to a first fluid circuit 310 (e.g., a coolant circuit) that extends from one of the compressor bleed conduits 60 to a plurality of coolant conduits 74 coupled to the turbine 24 and a plurality of coolant conduits 80 coupled to the exhaust duct 26. In particular, the first fluid circuit 310 extends to the coolant conduits 80 coupled to the injection grids 302 and 304. The ammonia solution train 256 may be connected to a second one of the control valves 300, which is connected to a second fluid circuit 312 that extends from one of the compressor bleed conduits 60 to one of the coolant conduits 80 coupled to the exhaust duct 26. In particular, the second fluid circuit 312 extends to the coolant conduit 80 coupled to the injection grid 306 (e.g., an ammonia injection grid). Controller 44 can determine the appropriate amount of reducing agent and / or ammonia to reduce exhaust emission levels and exhaust emission visibility (e.g., a yellow plume) and can operate control valve 300 to route the reducing agent to first fluid circuit 310 and the ammonia to second fluid circuit 312. While this example shows a particular flow path for reducing solution system 254, control valve 300 can divert the flow of each solution train 256 and 258 in any number of ways.

[0057] 8 is a flowchart of one embodiment of a process 320 for reducing exhaust emissions and exhaust emission visibility in the gas turbine system 10. The process 320 may include instructions 49 stored in a memory 48 and executable by a processor 46 of the controller 44, as described above. In step 322, the process 320 measures one or more parameters of the gas turbine system 10. For example, the process 320 may measure (e.g., using a sensor) a parameter in the exhaust duct 26, the combustor 22, the turbine 24, or any other suitable location. The process 320 may measure the parameter during startup, steady-state operation, or shutdown of the gas turbine system 10. The measured parameter may be a NO x Level, SO xThe parameters may include the level, CO level, exhaust temperature, temperature of the catalyst in the SCR system 246, visibility level (e.g., degree of opacity and / or color), and any other parameters related to exhaust emissions.

[0058] In step 324, process 320 evaluates whether the temperature (e.g., TSCR) of the SCR system 246 is greater than 350°F. The TSCR may be the temperature of the exhaust gas 128 at the SCR system 246, the temperature of the catalyst in the SCR system 246, or a combination thereof. The controller 44 may continuously monitor the temperature of the SCR system 246 to determine the next step. If the temperature at the SCR system 246 is greater than 350°F, process 320 proceeds to step 326. If the temperature at the SCR system 246 is less than 350°F, process 320 proceeds to step 328.

[0059] In step 326, process 320 controls the reducing solution system to initiate or adjust ammonia injection via coolant conduit 80 into SCR system 246 and / or one or more fluid paths 56 (e.g., coolant conduits 62, 66, and / or 74) of gas turbine engine 12. The ammonia is injected into SCR system 246, which converts NOx using a catalyst within the SCR system. x and other emissions. The efficiency of the conversion is proportional to the temperature of the SCR system 246. Therefore, when the SCR system 246 operates above 350°F, the controller 44 selectively routes ammonia to the SCR system 246. The controller 44 can operate a control valve 300 connected to the reducing solution system to control the flow of ammonia to the SCR system 246.

[0060] In step 328, process 320 initiates or adjusts ethanol injection through the reducing solution system. Process 320 can control ethanol injection into one or more fluid paths 56 (e.g., coolant conduits 62, 66, 74, and / or 80), such as cooling circuit 200. Process 320 can selectively deliver ethanol to all or selected injection points in bearings 64, combustor 22, turbine 24, exhaust duct 26, or combinations thereof, thereby reducing emissions levels (e.g., NO ). x The controller 44 may operate a control valve 300 connected to the reducing solution system 258 to control the flow of ethanol to the gas turbine system 10. As noted above, reducing agents other than ethanol may also be used.

[0061] Although process 320 shows steps 326 and 328 as alternatives following step 324, embodiments of process 320 may use the emission control measures of both steps 326 and 328 simultaneously to adjust both ammonia injection and ethanol injection to reduce emission levels and emission visibility. In step 330, process 320 determines whether NO x The controller 44 evaluates whether the NO 2 in the turbine exhaust has been reduced below a target level (e.g., a threshold value). x Actively monitors the levels, reductant (e.g., ammonia and ethanol) flow, and operation of each component of the gas turbine system (e.g., injection point, compressor, turbine, injection grid, cooling circuit). x If the level is determined to be below the predetermined target level, the process 320 continues to maintain operation at the operating point as indicated by step 332. However, if the level is determined to be below the predetermined target level, the process 320 continues to maintain operation at the operating point as indicated by step 332. x If the level is still above the predetermined target level, the process 320 can repeat the process or proceed to optional step 334 .

[0062] In optional step 334, the controller 44 operates the blower 252 to provide bypass air to the gas turbine system 10. In optional step 336, the controller 44 operates the blower 252 to provide bypass air to the gas turbine system 10. x Another determination is made by the controller 44 to determine if the level has been reduced below the target level. x If the controller 44 determines that the level has been reduced below the target level, the process 320 continues to maintain operation at the operating point as indicated by step 332. x If the controller 44 determines that the level is not below the target level, the controller 44 may begin the process again.

[0063] A technical effect of the disclosed embodiments facilitates reducing exhaust emissions levels and the associated visibility of the exhaust emissions by injecting an emission control fluid (e.g., a reductant) into one or more fluid paths 56 of the gas turbine engine 12. The fluid paths 56 may include cooling paths (e.g., one or more cooling circuits) through the bearings 64, the combustor 22, and / or the turbine 24. The fluid paths 56 may also extend to the exhaust duct 26. However, injecting the emission control fluid into the fluid paths upstream of the exhaust outlet 136 of the turbine 24 can help improve mixing and residence time of the emission control fluid with the exhaust gases, thereby helping to reduce the exhaust emissions and the visibility of the exhaust emissions before being emitted into the atmosphere.

[0064] This written description uses examples to disclose the invention, including the best mode, and to enable any person skilled in the art to practice the invention, including making and using any device or system 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 that have no substantial differences from the literal language of the claims. [Explanation of symbols]

[0065] 10 Gas Turbine System 11 Emissions Control System 12 Gas turbine engine 14 Load 16 Air intake 18 Compressor / Combustor 20 fuel nozzle 22 Combustor 24 Turbine / Exhaust Duct 25 Horizontal duct section 26 Exhaust duct 27 Vertical stack section 28 Air 30 Compressed air 32 Fuel 34 Arrow 36 Shaft 38 Emissions Control Unit 40 Emissions Control Fluid Supply System 42 Surveillance System 44 Controller 46 processors 48 memory 49 Command 50 Emissions Control Fluid Supply 52 Flow Control Unit / Valve 54 Fluid supply conduit 56 Fluid Path 58 Sensors 59 Coolant supply source 60 Compressor bleed air duct 61 Distribution conduit 62 Coolant conduit 63 Cooler 64 bearings 66 Coolant conduit 68 Combustor liner 70 Flow Sleeve 72 Headend 74 Coolant conduit 76 Outer casing 78 Inner shroud 80 Coolant conduit 82 Emissions Control Unit 84 Emissions Control Unit / First Injection Grid 86 Emissions Control Unit 88 Emissions Control Unit / Second Injection Grid 90 Emissions Control Unit 91 Emission Control Unit 92 Fluid Manifold 100 rotors 102 Stator 104 Turbine Stage 106 Turbine Blade 108 Wheels 110 Stator vane 112 outer casing 114 Hanger 116 Shroud Segment 118 Pair of Hooks 120 pairs of hooks 122 Complementary Hooks 124 Complementary Hooks 126 Clearance 128 Exhaust flow path / exhaust gas 130 Arrow 132 Arrow 134 Arrow 136 Exhaust outlet 150 Valve Control System 151 Flow Meter System 152 Axial / Axis 154 Radial / Axis 156 Circumferential / Axial 158 Downstream direction 160 Upstream direction 162 Valve 163 Flow meter 164 Extraction point 166 Valve 167 Flow meter 168 Injection Point 170 Valve 171 Flow meter 172 Injection Point 174 Duct Burner Assembly 176 Duct Burner 178 Selective Catalytic Reduction (SCR) System 200 Cooling circuit 202 Low pressure air extraction 204 Medium pressure air extraction 206 High-Pressure Air Extraction 208 High Pressure Turbine Section 210 Intermediate Pressure Turbine Section 212 Low Pressure Turbine Section 214 First injection point 216 Second injection point 218 Third Injection Point 240 Injection System 242 Injection Grid 244 Injection Grid 246 SCR system 248 Heat exchanger 250 Evaporator 252 Blois 254 Reduction Solution System 256 Ammonia Solution Train 258 Reduced Solution Train / Reduced Solution System 260 Ammonia solution tank / storage tank 262 Pump 264 Valve 266 Evaporator / Evaporation Tank 268 Electric Heater 270 Electric heater 272 Air Blower 274 Fluid conduit 280 Reducing Solution Tank 282 Pump 284 Valve 286 Evaporator / Evaporation Tank 288 Electric Heater 290 Fluid conduit 300 Control Valve 302 Injection grid 304 Injection Grid 306 Injection Grid 308 Heat exchanger 310 first fluid circuit 312 Second fluid circuit 320 Process 322 steps 324 steps 326 steps 328 steps 330 steps 332 steps 334 steps 336 steps

Claims

1. A system (10), comprising: An emissions control system (11) configured to be coupled to a turbine engine (12), comprising: an emission control fluid supply having one or more conduits configured to couple to one or more fluid paths of the system, the one or more fluid paths being fluidly coupled to a flow path of exhaust gases from a combustor through a turbine of the turbine engine via a cooling circuit for the turbine; at least one sensor (58) configured to obtain feedback of one or more parameters of the turbine engine (12), the one or more parameters being indicative of the visibility of emissions of the exhaust gas; at least one valve (52) coupled to said emission control fluid source (50); a controller (44) communicatively coupled to the at least one sensor (58) and the at least one valve (52), wherein, in response to the feedback, the controller (44) adjusts the at least one valve (52) to adjust a flow of an emission control fluid to reduce the visibility of the emissions in the exhaust gas, the emission control fluid including a reductant; Emission control system (11) comprising A system (10) comprising:

2. The system (10) of any preceding claim, further comprising the turbine engine (12) having the combustor (22) and the turbine (24).

3. The cooling circuit (200) passes through the rotating turbine blades of the turbine (24), the cooling circuit (200) comprises one or more compressor bleed conduits (60) coupled to a compressor (18) of the turbine engine (12); The system (10) of claim 2.

4. 3. The system of claim 2, wherein the one or more fluid paths comprise a bypass circuit having one or more compressor bleed conduits coupled to a compressor of the turbine engine and one or more bypass conduits coupled to an exhaust duct downstream of the turbine.

5. 10. The system of claim 1, wherein the emission control fluid source comprises a storage tank, an evaporator, and a pump, the storage tank comprising one or more tanks of ammonia solution, anhydrous ammonia, urea, ethanol, alcohol, hydrogen, or any combination thereof.

6. 2. The system of claim 1, wherein the at least one sensor comprises an emissions sensor, an opacity sensor, or a combination thereof, and the at least one sensor is configured to obtain the feedback of the one or more parameters of the exhaust gas.

7. 3. The system of claim 2, wherein the at least one sensor comprises at least one of a pressure sensor, a vibration sensor, a fuel flow sensor, a fuel composition sensor, a combustion temperature sensor, or a combination thereof, and the at least one sensor is configured to obtain the feedback of the one or more parameters of an input to a combustion chamber of the combustor, a characteristic of combustion in the combustion chamber, or a combination thereof.

8. The system (10) of claim 2, comprising a selective catalytic reduction (SCR) system (178, 246), an injection grid (242, 244), or both, disposed in an exhaust duct (26) downstream of the turbine (24).

9. A system (10), comprising: a controller (44) configured to communicatively couple to at least one sensor (58) and at least one valve (52) of an emissions control system (11) of a turbine engine (12); Equipped with the controller (44) is configured to receive feedback of one or more parameters of the system (10); the one or more parameters indicative of exhaust gas emissions visibility from the turbine engine; the controller (44), in response to the feedback, adjusts the at least one valve (52) to regulate a flow of reductant from an emission control fluid supply (50) to one or more fluid paths (56) of the turbine engine (12) to reduce the visibility of the emissions in the exhaust gas; the one or more fluid paths (56) are fluidly coupled to a flow path of the exhaust gases from a combustor (22) through a turbine (24) of the turbine engine (12) via a cooling circuit (200) of the turbine (24). System (10).

10. 10. The system of claim 9, wherein the controller is configured to adjust the at least one valve to increase the flow of the reductant to reduce the visibility of the emissions when the visibility exceeds a visibility threshold, when the emissions exceed an emissions threshold, or a combination thereof.

11. The cooling circuit (200) passes through the rotating turbine blades of the turbine (24), the cooling circuit (200) comprises one or more compressor bleed conduits (60) coupled to a compressor (18) of the turbine engine (12); the reducing agent comprises one or more of an ammonia solution, anhydrous ammonia, urea, ethanol, alcohol, hydrogen, or any combination thereof; and the at least one sensor (58) comprises an emissions sensor, an opacity sensor, or a combination thereof. The system (10) according to claim 9.

12. A method for reducing exhaust emission visibility in a gas turbine system (10), comprising: receiving feedback of one or more parameters of the gas turbine system (10) via at least one sensor (58) of an emissions control system (11), the one or more parameters indicative of the visibility of emissions in exhaust gases from the gas turbine system (10); adjusting at least one valve (52) via a controller (44) of the emission control system (11) to adjust a flow of reductant from an emission control fluid source (50) to one or more fluid paths (56) of the gas turbine system (10) to reduce the visibility of the emissions in the exhaust gas, 6) is fluidly coupled to a flow path of the exhaust gas from the combustor (22) through a turbine (24) of the gas turbine system (10) via a cooling circuit (200) of the turbine (24). A method comprising:

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