De-icing system for gas turbine systems

Abstract

To provide an anti-icing system for a gas turbine system.SOLUTION: An anti-icing system (38) for a gas turbine system (10) includes multiple nozzle assemblies (52). Each nozzle assembly (52) of the multiple nozzle assemblies (52) includes a nozzle (40) having one or more outlets (102) that are configured to inject a heated fluid in a radially outward direction, and a cap (44) having an annular wall (112) that circumferentially surrounds at least a portion of the nozzle (40). The cap (44) is configured to direct the heated fluid to flow in an upstream direction into an airflow (34) to facilitate mixing of the heated fluid with the airflow (34).SELECTED DRAWING: Figure 1

Description

TECHNICAL FIELD

[0001] The subject matter disclosed in the present specification relates to an anti-icing system for a gas turbine system.

BACKGROUND ART

[0002] Generally, a gas turbine system combusts a mixture of compressed air and fuel to generate high-temperature combustion gas. More specifically, the gas turbine system includes a compressor that compresses air to generate compressed air. The gas turbine system also includes a combustor that mixes the compressed air and fuel to generate combustion gas. The combustion gas is directed to a turbine to drive rotation of turbine blades and a shaft coupled to the turbine blades. The rotation of the shaft can drive a load such as a generator coupled to the shaft.

SUMMARY OF THE INVENTION

[0003] Specific embodiments corresponding to the scope of the subject matter originally claimed are summarized below. These embodiments are not intended to limit the scope of the claimed subject matter; rather, these embodiments are merely intended to provide an overview of possible forms of the claimed subject matter. Indeed, the claimed subject matter may include various forms that may be similar to or different from the embodiments described below.

[0004] In one embodiment, an anti-icing system for a gas turbine system includes an anti-icing system for a gas turbine system that includes a plurality of nozzle assemblies. Each nozzle assembly of the plurality of nozzle assemblies includes a nozzle having one or more outlets configured to inject heated fluid in a radially outward direction, and a cap having an annular wall circumferentially surrounding at least a portion of the nozzle. The cap is configured to direct the heated fluid to flow in an upstream direction into the air stream to facilitate mixing of the heated fluid and the air stream.

[0005] In one embodiment, the gas turbine system includes a turbine, a combustor, and a compressor coupled to an intake system. The intake system is configured to supply a heated airflow to the compressor, and the intake system includes a filter system and an anti-icing system. The anti-icing system includes a plurality of nozzle assemblies, each nozzle assembly of the plurality of nozzle assemblies including a nozzle having one or more outlets and a cap having an annular wall surrounding one or more outlets in a circumferential direction. The nozzles are configured to inject heated fluid through one or more outlets, and the annular wall of the cap is configured to allow the heated fluid to flow upstream into the airflow, facilitating mixing of the heated fluid and the airflow to form a heated airflow upstream of the filter system.

[0006] In one embodiment, the method includes the step of receiving an airflow in a first direction into an intake conduit of an intake system of a gas turbine system. The method also includes the step of injecting a heated fluid through one or more outlets of nozzles positioned in the intake conduit. The method further includes the step of guiding the heated fluid through an annular channel defined between the nozzle and a cap positioned to circumferentially surround at least a portion of the nozzle. The method further includes the step of outputting the heated fluid in a second direction into the airflow in the intake conduit to facilitate mixing between the heated fluid and the airflow and to form a heated airflow in the intake conduit.

[0007] These and other features, aspects, and advantages of this de-icing system and method will be better understood by reading the following detailed description with reference to the attached drawings, in which the same reference numerals throughout the drawings represent the same parts. [Brief explanation of the drawing]

[0008] [Figure 1] This is a block diagram of a gas turbine system having an intake system according to one embodiment. [Figure 2]This is a schematic diagram of a part of an anti-icing system that can be used in the intake system of Figure 1, according to one embodiment. [Figure 3] This is a side view of the de-icing assembly of the de-icing system shown in Figure 2, according to one embodiment. [Figure 4] This is a cutaway side view of the nozzle assembly of the anti-icing assembly shown in Figure 3, according to one embodiment. [Figure 5] This is a side view of the nozzle assembly shown in Figure 4, according to one embodiment. [Figure 6] This is a rear perspective view of the nozzle assembly shown in Figure 4, according to one embodiment. [Figure 7] This is a front perspective view of the nozzle assembly shown in Figure 4, according to one embodiment. [Figure 8] This figure shows a series of heat maps, including a heat map showing the temperature as a function of distance for the nozzle assembly in Figure 4, according to one embodiment. [Figure 9] This is a graph showing the temperature as a function of distance for the nozzle assembly in Figure 4, according to one embodiment. [Figure 10] Figure 3 is a side view of a nozzle assembly that may be used in the de-icing assembly according to one embodiment, and the nozzle assembly is configured to be positioned upstream of the manifold. [Figure 11] Figure 3 is a perspective view of a cap that may be used as part of a nozzle assembly of an anti-icing assembly according to one embodiment, the cap including an extended length. [Figure 12] Figure 3 is a perspective view of a cap that may be used as part of the nozzle assembly of the de-icing assembly according to one embodiment, the cap defining a radially extended portion. [Figure 13] Figure 3 is a perspective view of a cap that may be used as part of a nozzle assembly of an anti-icing assembly according to one embodiment, the cap including a curved pattern formed on the radial inner surface of the annular wall portion of the cap. [Figure 14]Figure 3 is a perspective view of a cap that may be used as part of a nozzle assembly of an anti-icing assembly according to one embodiment, the cap including a linear pattern formed on the radial inner surface of the annular wall portion of the cap. [Figure 15] Figure 3 is a perspective view of a cap that may be used as part of the nozzle assembly of the de-icing assembly according to one embodiment, the cap defining a curved projection along the radial inner surface of the annular wall portion of the cap. [Figure 16] This is a rear view of the cap shown in Figure 15, according to one embodiment. [Modes for carrying out the invention]

[0009] The following describes one or more specific embodiments of this disclosure. Not all features of actual embodiments are described herein in order to provide a concise description of these embodiments. It should be understood that in the development of actual embodiments, such as engineering or design projects, many embodiment-specific decisions must be made to achieve the developer's specific objectives, such as compliance with system-related and business-related constraints, and that these constraints may differ from embodiment to embodiment. Furthermore, it should be understood that while such development efforts may be complex and time-consuming, they will still be considered by those skilled in the art who benefit from this disclosure as merely routine design, fabrication, and manufacturing efforts.

[0010] When introducing elements of the various embodiments of this disclosure, the articles “a, an,” “the,” and “said” are intended to mean that there is one or more of those elements. The terms “equip,” “include,” and “have” are intended to be inclusive, meaning that there may be further elements other than those listed.

[0011] A gas turbine system receives an airflow (e.g., ambient airflow) through an intake system that directs the airflow to the compressor of the gas turbine system. Disclosed embodiments relate to an anti-icing system configured to prevent ice buildup on a filter in the intake system. The anti-icing system includes nozzles configured to spray and mix a heated fluid (e.g., compressor discharge air) with the airflow to form a heated airflow that raises the temperature adjacent to the filter in the intake system and prevents ice buildup on the filter in the intake system. Each nozzle is coupled to a cap configured to guide the heated fluid to flow upstream (e.g., into the airflow), thereby increasing the mixing of the airflow with the heated fluid in the intake system. In this way, even under inclined conditions (e.g., ambient conditions of low temperature and / or high relative humidity), the temperature of the heated airflow flowing through the filter in the intake system can be maintained within desired limits across the surface of the filter (e.g., across all or most of the surface of the filter) to enable proper operation of the intake system and provide satisfactory performance of the gas turbine system.

[0012] While de-icing systems are generally described, for the sake of discussion, as being used to raise the temperature of an airflow by mixing it with a heated fluid during low ambient conditions (e.g., to convert an airflow into a heated airflow for de-icing purposes), it should be understood that de-icing systems may more commonly be called inlet extraction heat (IBH) systems and can also favorably mix an airflow with a heated fluid in a way that prevents extremely high temperatures (e.g., hot spots exceeding the filter's high-temperature limit) at the intake system filter during other conditions (e.g., high ambient conditions and / or IBH maximum flow conditions). Thus, de-icing systems can also protect filters from extremely high temperatures that would normally lead to premature degradation and / or damage to the filter material (e.g., burning).

[0013] As an example, under high ambient conditions and / or IBH maximum flow conditions, the de-icing system may mix the airflow with a heated fluid such that at least 50% (or at least 55, 60, 70, 80, 90, or 95%) of the filter surface is heated by a heated airflow having a temperature at least 2°C (or at least 3, 4, or 5°C) higher than the ambient temperature (e.g., the temperature of the airflow entering the intake system, under low ambient conditions). Furthermore, the de-icing system may also mix the airflow with a heated fluid such that less than 50% (or less than 40, 30, 20, 10, or 5%) of the filter surface is heated to extremely high temperatures (e.g., hot spots above 90°C will extend over less than 50% of the filter surface, or be completely eliminated, even under high ambient conditions and / or IBH maximum flow conditions, if the heated fluids mixed with the airflow have temperatures above 400°C). As a more specific example, in the case of a heated fluid with a temperature of approximately 425°C, an anti-icing system can mix the airflow with the heated fluid so that the maximum temperature of the heated airflow reaches approximately 82°C over a distance of 0.8 meters. However, a typical anti-icing system with a cap but no nozzle may require a distance of 3.8 meters or more to mix the airflow with the heated fluid so that the maximum temperature of the heated airflow reaches the target temperature of approximately 82°C. Therefore, the use of a nozzle with a cap reduces the material and assembly costs of the intake system.

[0014] Furthermore, de-icing systems generally provide better mixing, which positively impacts the compressor by reducing thermal strain on the heated airflow at the compressor inlet. It should be understood that the de-icing systems disclosed herein can be used under additional operating conditions such as non-freezing temperatures and gas turbine base loads when the de-icing system is not operating (e.g., off). In such cases, structural components of the de-icing system (e.g., flow deflectors) may generate pressure losses that are not significantly increased by the presence of the structural components (e.g., compared to a system without structural components).

[0015] Referring here to the drawings, Figure 1 is a block diagram of one embodiment of a gas turbine system 10 (e.g., a gas turbine engine). The gas turbine system 10 includes an intake system 12 having an intake conduit 13 (e.g., a housing). The gas turbine system 10 also includes a compressor 14, one or more combustors 16, and a turbine 18. The gas turbine system 10 takes in an airflow 34 (e.g., ambient air) into the intake system 12, mixes the airflow 34 with a heated fluid in the intake system 12 to form a heated airflow 35, compresses the heated airflow 35 through the compressor 14 to form a compressed airflow 23, and burns fuel with the compressed airflow 23 in one or more combustors 16. Each combustor 16 has one or more fuel nozzles 20 configured to inject liquid fuel and / or gaseous fuel (e.g., natural gas or synthesis gas) from one or more fuel supply units 22 into a combustion chamber 17. Although not shown, in some embodiments, the fuel nozzle 20 may include primary and secondary fuel nozzles that inject fuel in a primary fuel injection zone and a secondary fuel injection zone, respectively.

[0016] Each combustor 16 causes fuel injected by fuel nozzles 20 to burn in compressed air flow 23 to generate high-temperature pressurized combustion gas 24 (e.g., exhaust gas), which is then directed to turbine 18. Turbine 18 has turbine blades coupled to a shaft 26 that is coupled to a load such as a generator 28. As combustion gas 24 flows into and through turbine 18, combustion gas 24 drives rotation of the turbine blades and shaft 26, thereby driving generator 28. In some embodiments, shaft 26 may be connected to another load such as a machine, a propeller of an aircraft or a vessel, or a compressor. Eventually, combustion gas 24 exits gas turbine system 10 via exhaust section 30 (e.g., an exhaust diffuser, an exhaust duct, an exhaust stack or tower, an emission control system such as a selective catalytic reduction (SCR) system). In the illustrated embodiment, shaft 26 is coupled to the compressor shaft of compressor 14, which has compressor blades coupled to the compressor shaft in one or more stages (e.g., 1 to 30 stages at different axial positions). Rotation of the compressor blades in compressor 14 causes compression of air flow 34 from intake system 12.

[0017] Further, the gas turbine system 10 also extracts or bleeds a portion of the compressed air flow (e.g., a heated fluid or a heated fluid flow as indicated by arrow 31) from the compressor 14 through an extraction or bleed conduit 32 to an anti-icing system 38 (e.g., an inlet bleed heat [IBH] system). In particular, the anti-icing system 38 includes a plurality of nozzles 40 (e.g., anti-icing nozzles, inlet bleed heat [IBH] nozzles) and a manifold 42 (e.g., an inlet bleed heat [IBH] manifold). Each of the plurality of nozzles 40 is provided with a cap 44 (e.g., an end cap) that may be integrally formed with the body of the nozzle 40 or may be coupled to the body of the nozzle 40 (e.g., via a threaded interface or a welded joint).

[0018] During operation, the heated fluid from the bleed conduit 32 is supplied into the manifold 42, which delivers the heated fluid to the plurality of nozzles 40, and the nozzles spray the heated fluid into the air stream 34 to form a heated air stream 35. At least a portion of the cap 44 is disposed downstream of the outlet of the nozzle 40, and the cap 44 is configured to direct (e.g., turn) the heated fluid to flow into the air stream 34 to facilitate mixing of the air stream 34 and the heated fluid upstream of the filter 46 of the intake system 12. Accordingly, the nozzle 40 with the cap 44 operates to prevent ice accumulation on the filter 46, and / or generally maintain the heated air stream 35 at a temperature within desired limits across the entire face of the filter 46 (e.g., across all or most of the face of the filter 46) to enable proper operation of the intake system 12 and provide satisfactory performance of the gas turbine system 10.

[0019] The bleed conduit 32 may be one or more bleed conduits coupled to the compressor 14 at, or downstream of, each, some, or one of the one or more compressor stages. The compressor 14 increases the pressure and temperature of the compressed air stream 23 at each subsequent compressor stage, so the bleed conduit 32 can extract the compressed air stream 23 at a particular compressor stage at a pressure and temperature suitable for use in the anti-icing system 38. In certain embodiments, the anti-icing system 38 can selectively extract the compressed air stream 23 (e.g., as the heated fluid, as indicated by arrow 31) through the bleed conduit 32 based on the temperature of the air stream 34 entering the intake system 12 (e.g., monitored by one or more sensors S), the temperature of the heated air stream 35 at the filter 46, and / or the temperature of the heated air stream 35 at the compressor 14. For example, as the ambient temperature gradually decreases, the anti-icing system 38 can extract the compressed air stream through a greater number of bleed conduits 32 and / or bleed conduits 32 at progressively later compressor stages of the compressor 14.

[0020] During operation, the intake system 12 receives an airflow 34 through an air hood 36 coupled to the intake conduit 13. In some embodiments, the airflow 34 may pass through or traverse one or more additional intake components, such as a plurality of silencer baffles 48, one or more coalescers 50, nozzles 40 with caps 44, a manifold 42, and a filter 46. Together, each nozzle 40 with its cap 44 can be considered a nozzle assembly 52, and a nozzle assembly 52 with a manifold 42 can be considered an anti-icing assembly 54 (e.g., an inlet extraction heat [IBH] assembly).

[0021] As described above, the de-icing system 38 also includes a plurality of sensors S configured to monitor operating conditions such as temperature, humidity, or various conditions that promote ice formation. For example, the de-icing system 38 may include one or more sensors 56 located inside and outside the air hood 36, thereby monitoring ambient conditions for the air (e.g., ambient temperature, humidity). The de-icing system 38 may include one or more sensors 58 located in or upstream of the manifold 42, such as between the manifold 42 and the air hood 36. The de-icing system 38 may also include one or more sensors 60 located in or downstream of the manifold 42, such as between the filter 46 or between the manifold 42 and the filter 46. Furthermore, the de-icing system 38 may include one or more sensors 62 located downstream of the filter 46, such as at or upstream of the intake of the compressor 14. The de-icing system 38 may also include one or more sensors 64 located along each of the extraction conduits 32.

[0022] The de-icing system 38 also includes a controller 68 communicatively coupled to sensors 56, 58, 60, 62, and 64, valves 66 arranged along each extraction conduit 32, and various components of the gas turbine system 10 (e.g., valves that control the supply of fuel from the fuel supply unit 22 to the fuel nozzle 20). The controller 68 has a processor 70, a memory 72, and computer-readable instructions 74 stored in the memory 72 and executable by the processor 70. The controller 68 obtains sensor readings from the sensors S, and the controller 68 can use the computer-readable instructions 74 to adjust the operation of the de-icing system 38 based on these sensor readings, upper and lower temperature thresholds (e.g., desired limits or targets), a computer model, and / or user input. For example, if the temperature of one or more of the sensors falls below a lower temperature threshold (e.g., 0°C), the controller 68 can send a control signal to the actuator (e.g., an electric actuator) of the valve 66 to partially or completely open the valve 66, allowing heated fluid to flow through the extraction conduit 32 to the manifold 42. Figure 1 shows compressed air flow from the compressor 14 as heated fluid supplied to the manifold 42, but certain embodiments of the de-icing system 38 may additionally or alternatively be coupled to one or more other heated fluid sources (e.g., heated airflow, other sources of exhaust gas).

[0023] In this way, the controller 68 monitors the de-icing system 38 and controls the flow rate and / or temperature of the heated fluid to the manifold 42 and to the intake conduit 13 through the nozzle 40, thereby regulating the temperature in the intake conduit 13 to suppress and / or remove ice formation in the filter 46 or elsewhere in the intake system 12 and / or in the compressor 14. As will be described in more detail below, the cap 44 guides the heated fluid ejected by the nozzle 40 to facilitate mixing between the airflow 34 and the heated fluid, thereby regulating the temperature of the heated airflow and / or making the temperature of the heated airflow 35 more uniform (for example, between the nozzle assembly 52 and the filter 46, particularly across the surface of the filter 46) in the region of the intake conduit 13 downstream of the nozzle assembly 52.

[0024] Figure 2 is a schematic diagram of one embodiment of an anti-icing system 38 coupled to an intake system 12. For ease of explanation, the anti-icing system 38 and the intake system 12 can be described with reference to the longitudinal axis or longitudinal direction 80, the transverse axis or transverse direction 82, the vertical axis or vertical direction 84, and / or the circumferential axis or circumferential direction 86. As used herein, the downstream direction is substantially aligned with the longitudinal direction 80, while the upstream direction is substantially opposite to the longitudinal direction 80.

[0025] As shown in the illustration, the de-icing system 38 includes a de-icing assembly 54 having a manifold 42 and nozzle assemblies 52. Each nozzle assembly 52 includes a nozzle 40 and a cap 44 (only one nozzle assembly 52 is referenced for clarity in the image). The airflow 34 enters the intake system 12 through an air hood 36, which may include a plurality of inclined baffles to prevent rain or snow from entering. The airflow 34 may also pass through a plurality of silencer baffles 48 and / or coalescers 50 upstream of the nozzle assemblies 52. The silencer baffles 48 have one or more acoustic attenuation mechanisms (e.g., acoustic attenuation surface mechanisms, internal materials) to help reduce acoustic noise caused by the airflow 34 passing through the intake system 12. The coalescers 50 are configured to remove water from the airflow 34. The coalescers 50 may include mechanical coalescers, electrostatic coalescers, or a combination thereof.

[0026] After the airflow 34 mixes with the heated fluid to form a heated airflow 35, the heated airflow 35 can pass through the filter 46. The filter 46 may include any number and type of filters. The filter 46 may be configured to filter out particulate matter and moisture, however, the filter 46 may be susceptible to ice formation at certain low temperatures and / or thermal damage at certain high temperatures. The above components are shown in order within the intake conduit 13 (e.g., from upstream to downstream), but various embodiments may rearrange each of the above components in any suitable order, except that the nozzle assembly 52 remains upstream of the filter 46.

[0027] The nozzles 40 are arranged along the transverse axis 82 and the vertical axis 84 (for example, spaced apart in a grid pattern of multiple rows and multiple columns). In the illustrated embodiment, each nozzle assembly 52 is coupled to the manifold 42 downstream of the manifold 42 such that the nozzle assembly 52 is positioned between the manifold 42 and the filter 46 along the longitudinal axis 80. However, it should be understood that each nozzle assembly 52 may also be coupled to the manifold 42 upstream of the manifold 42 such that the manifold 42 is positioned between the nozzle assembly 52 and the filter 46 along the longitudinal axis 80. In either case, regardless of the relative positioning of the nozzle assembly 52 with respect to the manifold 42, the nozzle assembly 52 is positioned upstream of the filter 46 along the longitudinal axis 80.

[0028] In the illustrated embodiment, the heated fluid includes a compressed air stream extracted from the compressor 14, as described above with reference to Figure 1. The compressed air from the compressor 14 may be about 200°C to 600°C and have a pressure of about 800 to 900 kilopascals. However, the de-icing system 38 may use any one or more heated fluids directly or indirectly to raise the temperature of the air stream 34. For example, as illustrated, the heated fluid may be any suitable heated fluid that can be injected directly into the air stream 34 via the nozzle 40 to raise the temperature of the air stream 34, but is not limited to heated air or exhaust gas.

[0029] Figure 3 is a side view of one embodiment of an anti-icing assembly 54 having a manifold 42 and nozzle assemblies 52. Each nozzle assembly 52 includes a nozzle 40 and a cap 44 (only one nozzle assembly 52 is referenced for clarity in the image). Furthermore, each nozzle 40 includes a body 98 (e.g., a nozzle body, a housing with side walls). Each nozzle 40 may have a central axis 100 (e.g., parallel to the longitudinal axis 80) and may have one or more outlets 102 formed in the body 98 (e.g., extending through the side walls). The outlets 102 may have any suitable form. For example, the outlets 102 may include one or more continuous rings extending circumferentially around the nozzle 40 (as shown), or the outlets 102 may be separate openings spaced circumferentially around the nozzle 40. The outlet 102 may also be located at any suitable position between the first upstream end and the second downstream end of the nozzle 40 (for example, any suitable position along the longitudinal axis 80). Regardless of their form and / or position, the outlet 102 can eject (e.g., spray) the heated fluid radially outward from the nozzle 40 and / or intersect with the airflow 34. The cap 44 may be located close to the second downstream end of the nozzle 40, with at least a portion of the cap 44 located downstream of the outlet 102. As will be described in more detail below, the cap 44 can direct the heated fluid ejected through the outlet 102 of the nozzle 40 into the airflow 34, as indicated by arrow 104.

[0030] Figure 4 is a cutaway side view of a nozzle assembly 52 according to one embodiment. In particular, a portion of the cap 44 has been removed to show a portion of the nozzle 40 below the cap 44. Each nozzle 40 includes a body 98, a central axis 100, and one or more outlets 102 formed in the body 98 (extending, for example, through the side walls).

[0031] As shown in the figure, the cap 44 has a substantially C-shaped cross-section formed by an end portion 110 (e.g., a plate) and an annular wall portion 112. The end portion 110 and / or the annular wall portion 112 can be coupled to the body 98 of the nozzle 40 via any suitable coupler such as a screw interface or a welded joint. As described above, the cap 44 may instead be integrally formed with the body 98 of the nozzle 40 by a three-dimensional printing technique or the like. Furthermore, the cap 44 may have any suitable cross-sectional shape and / or may not have an end portion 110. For example, the cap 44 may include only an annular wall portion 112 (e.g., a ring) that guides the heated fluid and couples to the nozzle 40 to provide the operational features disclosed herein.

[0032] The annular wall portion 112 extends circumferentially around at least a portion of the body 98 of the nozzle 40 (for example, located radially outward from at least a portion of the body 98 of the nozzle 40). For example, the annular wall portion 112 extends circumferentially around one or more outlets 102 formed in the body 98 of the nozzle 40. The cap 44 defines a channel 114 (for example, an annular channel) fluidly coupled to one or more outlets 102. In particular, the channel 114 is defined between the radial inner surface 116 of the annular wall portion 112 of the cap 44 and the radial outer surface 118 of the body 98 of the nozzle 40, and the channel 114 extends circumferentially around the body 98 of the nozzle 40. In some embodiments, a portion of the channel 114 can be defined by a curved inner surface 120 which can be considered as part of the radial inner surface 116 of the annular wall portion 112.

[0033] During operation, the airflow 34 can generally flow in a first direction (e.g., downstream) from the first upstream end of the nozzle 40 toward the second downstream end of the nozzle 40. The heated fluid may be ejected in a second direction (e.g., radially outward, intersecting the first direction) from one or more outlets 102 of the nozzle 40 into the channel 114, as indicated by arrow 122. The heated fluid may be prevented from flowing in the second and / or first directions while it is inside the cap 44. Instead, the heated fluid may be directed (e.g., reversed) through the channel 114 (e.g., via contact with the radial inner surface 116 of the annular wall portion 112) to exit through the channel 114 and out through the opening 124 of the channel 114 (e.g., an annular opening). In this way, the heated fluid may be ejected in a third direction (e.g., upstream) from the second downstream end of the nozzle 40 toward the first upstream end of the nozzle 40, as indicated by arrow 126. Therefore, the heated fluid may be output in a third direction opposite to (e.g., entirely or substantially opposite to) the first direction of the airflow 34. By injecting the heated fluid into the airflow 34, the nozzle assembly 52 can facilitate mixing of the airflow 34 with the heated fluid upstream of the filter 46. Thus, the nozzle assembly 52 having nozzles 40 and caps 44 can, for example, improve the de-icing capability of the de-icing system 38, prevent the formation of cold spots that could otherwise be subjected to ice formation, prevent the formation of hot spots that could otherwise damage the filter 46, allow the use of fewer nozzles 40 with greater spacing between adjacent nozzles 40, and / or allow the use of smaller sized intake conduits 13.

[0034] Furthermore, advantageously, the cap 44 rotates the heated fluid, injecting it upstream (e.g., into the airflow 34 and away from the filter 46). Thus, initial mixing takes place upstream of one or more outlets 102, which provides more space (e.g., distance along the longitudinal axis 80, compared to the heated fluid injected into the airflow 34 at one or more outlets 102 without the cap 44) for mixing the airflow 34 with the heated fluid upstream of the filter 46. Thus, the nozzle assembly 52 can provide an efficient de-icing process within a given size of the intake conduit 13 (e.g., a size that is retrofitted, where space within the intake conduit 13 is limited) and / or allow the use of a smaller size intake conduit 13 (e.g., compared to an intake conduit without the nozzle assembly 52 with the nozzle 40 and cap 44). It should be understood that various alternative configurations are conceivable. For example, the radial inner surface 116 of the annular wall portion 112 may be inclined with respect to the longitudinal axis 80 to provide a different spread to the heated fluid (for example, to further spray radially outward around the nozzle 40) (for example, the upstream end of the radial inner surface 116 is positioned radially outward from the downstream end of the radial inner surface 116).

[0035] Figures 5 to 7 provide different illustrations of one embodiment of a nozzle assembly 52 having a nozzle 40 and a cap 44. In particular, Figure 5 is a side view of the nozzle assembly 52, Figure 6 is a rear perspective view of the nozzle assembly 52 (e.g., a downstream perspective view), and Figure 7 is a front perspective view (e.g., an upstream perspective view of the nozzle assembly 52). As shown, the nozzle 40 includes a body 98, and the cap 44 includes an end portion 110 and an annular wall portion 112. As best shown in Figure 6, the cap 44 defines a channel 114 for guiding heated fluid through an opening 124.

[0036] Figure 8 includes heatmaps illustrating the operational advantages of the nozzle assembly 52 disclosed herein. In particular, a first heatmap 150 shows the temperature of the heated airflow over distance for the nozzle assembly 52 having the nozzle 40 and the cap 44, and a second heatmap 152 shows the temperature of the heated airflow over distance for another nozzle (e.g., the same or similar nozzle as nozzle 40) without the cap 44. In the “base” design where the nozzle 40 does not have the cap 44, the second heatmap 152 shows that the heated fluid is sprayed downstream into the airflow, resulting in a high-temperature region downstream of each nozzle. In contrast, in the “c-cap” design of the nozzle 40 with the cap 44, the cap 44 redirects the flow upstream to mix with the airflow. Thus, the heated fluid and the airflow begin to mix in the region upstream of the nozzle assembly 52, and the mixing between the heated fluid and the airflow effectively reduces the temperature and / or provides a more uniform temperature downstream of the nozzle assembly 52.

[0037] Figure 9 is a graph 160 that corresponds to the first heatmap 150 in Figure 8 and has a first line 162 representing the temperature over distance for a nozzle assembly 52 including the nozzle 40 and cap 44. Graph 160 also corresponds to the second heatmap 152 in Figure 8 and shows a second line 164 representing the temperature over distance for another nozzle without the cap 44. As shown, in the case of a heated fluid (e.g., at a temperature of about 425°C), the nozzle assembly 52 with the nozzle 40 and cap 44 can mix the airflow and the heated fluid such that the maximum temperature of the heated airflow reaches about 82°C over a distance of 0.8 meters (e.g., point 166). However, the other nozzle without the cap 44 can mix the airflow and the heated fluid such that the maximum temperature of the heated airflow reaches about 82°C over a distance of 3.8 meters (e.g., point 168). Therefore, the nozzle assembly 52 having the nozzle 40 and cap 44 can advantageously regulate the temperature of the heated airflow in a desired manner (e.g., to a desired temperature and / or more uniformly) at a position further upstream of the filter 46 along the longitudinal axis 80 (see Figures 1 and 2), thereby reducing damage to the filter 46 (e.g., due to ice accumulation and / or hot spots). Thus, by using the nozzle 40 with cap 44, the de-icing system 38 can be easily retrofitted to the space constraints of existing intake systems, and in the case of new structures, a shorter intake system 12 can be used than one using a capless nozzle, thereby saving capital costs.

[0038] Figure 10 is a side view of one embodiment of a nozzle assembly 180 that can be used in an anti-icing system for a gas turbine system, such as the anti-icing system 38 of the gas turbine system 10 in Figure 1. As shown, the nozzle assembly 180 includes a nozzle 182 and a cap 184. The nozzle assembly 180 is located upstream of a manifold 186 that distributes heated fluid to the nozzle assembly 180.

[0039] The cap 184 may be positioned close to the first upstream end of the nozzle 182, and at least a portion of the cap 184 is positioned downstream of one or more outlets 188 of the nozzle 182. Thus, the heated fluid ejected from one or more outlets 188 of the nozzle 182 is guided by the cap 184 to flow upstream into the airflow 34. The cap 184 may have any of the features of the cap 44 described with respect to Figures 1 to 9 (e.g., a c-shaped cross-sectional shape, a channel) to enable the cap 184 to guide the heated fluid in order to facilitate mixing between the heated fluid and the airflow 34 and form a heated airflow 35.

[0040] Placing the nozzle assembly 180 upstream of the manifold 186, and / or placing the outlet 188 and cap 184 close to the first upstream end of the nozzle 182, can provide more space (e.g., distance along the longitudinal axis 80; compared to when the nozzle assembly 180 is located downstream of the manifold 186 and / or outlet 188, and the cap 184 is located close to the second downstream end) for mixing the airflow 34 with the heated fluid upstream of the filter 46 of the intake system 12.

[0041] Figures 11 to 16 show various features, such as surface features, of a cap 44 that can be used as part of a nozzle assembly 52. ​​It should also be understood that these various features may be utilized for a cap 184 as part of a nozzle assembly 180. With this in mind, Figure 11 is a perspective view of one embodiment of a cap 44, which includes an extended length along the longitudinal axis 80 (for example, compared to the cap 44 shown in Figures 1 to 9, or compared to the cap 184 shown in Figure 10). Additional segments 190 and end segments 192 are depicted in Figure 11 to facilitate explanation and better illustrate the extended length, but it should be understood that the cap 44 may be formed as a single, integrated structure, as shown in Figures 1 to 9, having any suitable length along the longitudinal axis 80. However, the additional segments 190 and end segments 192 may be separate parts connected to each other (e.g., via threads and / or welds), thereby configured to allow adjustment of the overall length of the cap 44 (e.g., by connecting the additional segments 190, which may be available in various lengths, to the end segments 192). Nevertheless, it should be understood that the extended length may be any appropriate length relative to the body 98 of the nozzle 40. For example, the extended length may be chosen to cover or extend 10, 20, 30, 40, 50, or 60% or more of each length of the body 98 of the nozzle 40. The extended length may be chosen to provide an appropriate or desired flow of the heated fluid within the cap 44.

[0042] Figure 12 is a perspective view of one embodiment of a cap 44 having a radially extended portion 194 according to one embodiment. The radially extended portion 194 is defined by a radially extending radial inner surface 116 of the annular wall portion 112. In particular, the radius of the radial inner surface 116 increases in the upstream direction (for example, the radius is smaller at the downstream end and larger at the upstream end by the opening 124). As described above, the cap 44 is positioned around the body 98 of the nozzle 40 to facilitate the flow of heated fluid through a channel 114 defined between the radial inner surface 116 and the body 98 of the nozzle 40.

[0043] Figure 13 is a perspective view of one embodiment of a cap 44 having a curved pattern 196 formed on the radial inner surface 116 of the annular wall portion 112 of the cap 44. Figure 14 is a perspective view of one embodiment of a cap 44 having a straight pattern 198 formed on the radial inner surface 116 of the annular wall portion 112 of the cap 44. The curved pattern 196 and the straight pattern 198 may include surface textures such as circumferentially spaced alternating grooves and protrusions around the radial inner surface 116 of the annular wall portion 112 of the cap 44. The curved pattern 196 may be configured to induce swirling of the heated fluid as the heated fluid moves through a channel 114 defined between the radial inner surface 116 and the body 98 of the nozzle 40. The curved pattern 196 and the straight pattern 198 have a substantially low profile and can eliminate the smoothness of the radial inner surface 116.

[0044] Figure 15 is a perspective view of one embodiment of a cap 44 having curved projections 200 extending along the radial inner surface 116 of the annular wall portion 112 of the cap 44, and Figure 16 is a rear view. As shown, the curved projections 200 are circumferentially spaced around the radial inner surface 116 of the annular wall portion 112 of the cap 44. The curved projections 200 may be configured to induce swirling of the heated fluid as it moves through a channel 114 defined between the radial inner surface 116 and the body 98 of the nozzle 40. The curved projections 200 have a substantially high profile (compared to, for example, a curved pattern 196 and a straight pattern 198) and eliminate the smoothness of the radial inner surface 116. For example, each of the curved projections 200 may extend radially over 10, 20, 30, 40, 50, 60% or more of the channel 114.

[0045] Figures 11 to 16 show various features including surface features (e.g., a curved pattern 196, a straight pattern 198, a curved projection 200), but it should be understood that other features including other surface features may be provided as part of the cap 44. For example, the cap 44 may have a nearly high profile and include a straight projection extending linearly along the radial inner surface 116. Furthermore, features including surface features may be provided as part of the body 98 of the nozzle 40, such as along the radial outer surface 118 of the body 98 of the nozzle 40. For example, the body 98 of the nozzle 40 may include the same features as the cap 44 (e.g., both may have a curved projection extending into the channel 114). Furthermore, features including surface features can be combined in any suitable way (e.g., a curved pattern 196 or a straight pattern 198 can be used in combination with a radially extended portion 194).

[0046] The technical effects of the de-icing technology disclosed herein include providing more effective mixing of the airflow and heated fluid in the intake system. Under certain conditions (e.g., low ambient conditions), the mixing can result in more effective removal, reduction and / or prevention of ice buildup and / or more effective reduction and / or prevention of hot spots on the filter of the intake system of a gas turbine system compared to conventional systems. The cap of the nozzle assembly of the de-icing assembly may include various mechanisms (e.g., shape, arrangement) to facilitate mixing of the airflow and heated fluid in order to provide more effective removal, reduction and / or prevention of ice buildup and / or prevention of hot spots on the filter of the intake system of a gas turbine system. Under certain conditions (e.g., high ambient conditions and / or maximum IBH flow rate), the mixing can result in more effective reduction and / or prevention of hot spots on the filter of the intake system of a gas turbine system compared to conventional systems. De-icing assemblies can be cost-effective in that their components can be configured to fit into and / or join with existing de-icing systems and / or existing intake systems (e.g., retrofitted).

[0047] This specification uses examples to disclose embodiments of the disclosure, including best modes, and to enable any person skilled in the art to practice embodiments of the disclosure, including the fabrication and use of any device or system and the implementation of any incorporated methods. The patentable scope of the disclosure is defined by the claims and may include other examples that a person skilled in the art may conceive. Such other examples shall be within the claims if they have structural elements that are not different from the language of the claims, or if they include equivalent structural elements that are substantially different from the language of the claims. [Explanation of Symbols]

[0048] 10 Gas Turbine Systems 12 Intake System 13 Intake conduit 14 Compressor 16 Combustor 17 Combustion chamber 18 Turbine 20 Fuel Nozzles 22 Fuel supply section 23 Compressed air flow 24. Combustion gases, pressurized combustion gases 26 shafts 28 Generators 30 Exhaust Section 31 Arrow 32 Extraction conduit 34 Airflow 35 Heated airflow 36 Air Hood 38. Anti-icing system 40 nozzles 42 Manifold 44 caps 46 filters 48 Silencer baffle 50 Coalessa 52 Nozzle Assembly 54 Anti-icing assembly 56 sensors 58 sensors 60 sensors 62 sensors 64 sensors 66 valves 68 Controllers 70 processors 72 memory 74 Computer-readable instructions 80 Longitudinal direction, longitudinal axis 82 Lateral direction, lateral axis 84 Vertical, vertical axis 86 Circumferential direction, circumferential axis 98 Main Unit 100 center axis 102 Exit 104 Arrow 110 End section 112 Annular wall section 114 channels 116 Radial inner surface 118 Radial outer surface 120 Inner self 122 Arrow 124 Opening 126 Arrows 150 First Heatmap 152 Second Heatmap 160 graphs 162 First line 164 The second line 166 points 168 points 180 Nozzle Assembly 182 nozzles 184 Cap 186 Manifold 188 Exit 190 additional segments 192 End Segments 194 Radially extended portion 196 Curved Pattern 198 Straight Line Pattern 200 curved protrusions

Claims

1. An anti-icing system (38) for a gas turbine system (10), wherein the anti-icing system (38) is It comprises multiple nozzle assemblies (52), and each of the multiple nozzle assemblies (52) is A nozzle (40) including one or more outlets (102) configured to inject a heated fluid radially outward, A cap (44) including an annular wall (112) that surrounds at least a portion of the nozzle (40) in the circumferential direction, and An anti-icing system (38) comprising a cap (44) having an opening (124) facing upstream, and configured to allow the heated fluid to flow out of the opening (124) upstream into the airflow (34) in order to promote mixing of the heated fluid and the airflow (34).

2. The de-icing system (38) according to claim 1, wherein the plurality of nozzle assemblies (52) are arranged as a two-dimensional grid.

3. The de-icing system (38) according to claim 1, comprising a manifold (42) configured to distribute the heating fluid to the plurality of nozzle assemblies (52).

4. The de-icing system (38) according to claim 3, wherein the plurality of nozzle assemblies (52, 180) are arranged upstream of the manifold (42, 186).

5. The anti-icing system (38) according to claim 1, wherein the cap (44) includes a c-shaped cross-sectional shape.

6. The de-icing system (38) according to claim 1, wherein the radial outer surface (118) of the body (98) of the nozzle (40) and the radial inner surface (116) of the annular wall (112) of the cap (44) define an annular channel (114) that is fluidly coupled to the one or more outlets (102).

7. The anti-icing system (38) according to claim 6, wherein the radial inner surface (116) of the annular wall (112) of the cap (44) includes one or more surface feature portions.

8. The de-icing system (38) according to claim 1, wherein the cap (44) includes an end portion (110) that prevents the heated fluid from flowing downstream.

9. The anti-icing system (38) according to claim 1, wherein the annular wall (112) surrounds the one or more outlets (102) in a circumferential direction.

10. The de-icing system (38) according to claim 1, wherein the nozzle (40) and the cap (44) are connected to each other.

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