Patent Description:
In general, a gas turbine system combusts a mixture of compressed air and fuel to produce hot combustion gases. More particularly, the gas turbine system includes a compressor that compresses air to generate the compressed air. The gas turbine system also includes a combustor that mixes the compressed air and the fuel to produce combustion gases. The combustion gases are directed into a turbine to drive rotation of turbine blades and a shaft that is coupled to the turbine blades. The rotation of the shaft may drive a load, such as an electrical generator that is coupled to the shaft.

<CIT> and <CIT> describe known anti-icing systems for gas turbine systems.

These embodiments are not intended to limit the scope of the claimed subject matter, but rather these embodiments are intended only to provide a brief summary of possible forms of the claimed subject matter. Indeed, the claimed subject matter may encompass a variety of forms that may be similar to or different from the embodiments set forth below.

An anti-icing system for a gas turbine system in accordance with the invention as hereinafter claimed includes the features of claim <NUM> below.

These and other features, aspects, and advantages of the present anti-icing system and method will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:.

Moreover, it should be appreciated that such a development effort might be complex and time consuming but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure.

A gas turbine system receives an airflow (e.g., ambient airflow) through an air intake system, which directs the airflow to a compressor of the gas turbine system. The disclosed embodiments relate to an anti-icing system that is configured to block a buildup of ice on a filter within the air intake system. The anti-icing system includes nozzles that are configured to spray a heated fluid (e.g., compressor discharge air) to mix with the airflow in order to form a heated airflow that increases a temperature adjacent to the filter within the air intake system and that blocks the buildup of ice on the filter within the air intake system. The anti-icing system also includes a flow-deflector assembly with multiple plates (e.g., baffles) that are positioned to distribute (e.g., spread, disperse) the airflow upstream of the nozzles to thereby increase the mixing of the airflow and the heated fluid within the air intake system. In this way, even in inclement conditions (e.g., cold and/or high relative humidity ambient conditions), the temperature of the heated airflow that flows through the filter within the air intake system may be maintained within desirable limits across a face of the filter (e.g., across all or most of the face of the filter) to enable proper operation of the air intake system and to provide satisfactory performance of the gas turbine system.

While the anti-icing system is generally described as being used to mix the airflow and the heated fluid to increase the temperature of the airflow (e.g., to turn the airflow into the heated airflow for anti-icing functionality) during cold ambient conditions to facilitate discussion, it should be appreciated that the anti-icing system may be more generally referred to as an inlet bleed heat (IBH) system and may also advantageously mix the airflow and the heated fluid in a manner that blocks extremely high temperatures (e.g., hot spots that exceed a high temperature limit for the filter) at the filter of the air intake system during other conditions (e.g., hot ambient conditions and/or IBH maximum flow conditions). Thus, the anti-icing system may also protect the filter from the extremely high temperatures that may otherwise result in early degradation of material of the filter and/or damage (e.g., burn) the material of the filter.

For example, the anti-icing system may mix the airflow and the heated fluid such that at least <NUM> percent (or at least <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, or <NUM> percent) of the face of the filter is heated by the heated airflow having a respective temperature that is at least <NUM> degrees Celsius (or at least <NUM>, <NUM>, or <NUM> degrees Celsius) greater than an ambient temperature (e.g., the temperature of the airflow upon entry into the air intake system; during cold ambient conditions), and the anti-icing system may also mix the airflow and the heated fluid such that less than <NUM> percent (or less than <NUM>, <NUM>, <NUM>, <NUM>, or <NUM> percent) of the face of the filter is heated to the extremely high temperatures (e.g., hot spots of more than <NUM> degrees Celsius extend across less than <NUM> percent of the filter face of the filter or are completely eliminated, even when the heated fluid that mixes with the airflow has a respective temperature that is greater than <NUM> degrees Celsius; during hot ambient conditions and/or IBH maximum flow conditions).

Furthermore, the anti-icing system generally provides better mixing, which provides a positive impact on the compressor by reducing thermal distortion of the heated airflow at an inlet of the compressor. It should be appreciated that the anti-icing system disclosed herein may be used in additional operating conditions, such as at non-icing temperatures and gas turbine base load with the anti-icing system inactivated (e.g., turned off). In such cases, the structural components of the anti-icing system (e.g., flow deflectors) may generate pressure loss that is not increased significantly due to the presence of the structural components (e.g., as compared to systems without the structural components).

Turning now to the drawings, <FIG> is a block diagram of an embodiment of a gas turbine system <NUM> (e.g., gas turbine engine). The gas turbine system <NUM> includes an air intake system <NUM> having an air intake conduit <NUM> (e.g., housing). The gas turbine system <NUM> also includes a compressor <NUM>, one or more combustors <NUM>, and a turbine <NUM>. The gas turbine system <NUM> intakes an airflow <NUM> (e.g., ambient air) into the air intake system <NUM>, mixes the airflow <NUM> with a heated fluid within the air intake system <NUM> to form a heated airflow <NUM>, compresses the heated airflow <NUM> through the compressor <NUM> to form a compressed airflow <NUM>, and combusts a fuel with the compressed airflow <NUM> in the one or more combustors <NUM>. Each combustor <NUM> has one or more fuel nozzles <NUM> configured to inject a liquid fuel and/or a gaseous fuel (e.g., natural gas or syngas) from one or more fuel supplies <NUM> into a combustion chamber <NUM>. Although not shown, in some embodiments, the fuel nozzles <NUM> may include primary and secondary fuel nozzles that inject fuel at a primary fuel injection zone and a secondary fuel injection zone, respectively.

Each combustor <NUM> combusts the fuel injected by the fuel nozzles <NUM> with the compressed airflow <NUM> to create hot, pressurized combustion gases <NUM> (e.g., exhaust gas), which is then directed into the turbine <NUM>. The turbine <NUM> has turbine blades coupled to a shaft <NUM>, which is coupled to a load such as an electric generator <NUM>. As the combustion gases <NUM> flow into and through the turbine <NUM>, the combustion gases <NUM> drive rotation of the turbine blades and the shaft <NUM>, thereby driving the electric generator <NUM>. In some embodiments, the shaft <NUM> may be connected to another load, such as machinery, a propeller of an aircraft or ship, or a compressor. Eventually, the combustion gases <NUM> exit the gas turbine system <NUM> via an exhaust section <NUM> (e.g., an exhaust diffuser, an exhaust duct, an exhaust stack or tower, an emissions control system such as a selective catalytic reduction (SCR) system, etc.). In the illustrated embodiment, the shaft <NUM> is coupled to a compressor shaft of the compressor <NUM>, which has compressor blades coupled to the compressor shaft in one or more stages (e.g., <NUM> to <NUM> stages in different axial positions). The rotation of the compressor blades within the compressor <NUM> causes compression of the airflow <NUM> from the air intake system <NUM>.

Furthermore, the gas turbine system <NUM> also extracts or bleeds a portion of the compressed airflow (e.g., the heated fluid or a heated fluid flow, as indicated by arrow <NUM>) from the compressor <NUM> through an extraction or bleed conduit <NUM> to an anti-icing system <NUM> (e.g., an inlet bleed heat [IBH] system). In particular, the anti-icing system <NUM> includes multiple nozzles <NUM> (e.g., anti-icing nozzles; inlet bleed heat [IBH] nozzles), a manifold <NUM> (e.g., an inlet bleed heat [IBH] manifold), and a flow-deflector assembly <NUM>. The heated fluid from the bleed conduit <NUM> is provided into the manifold <NUM>, which delivers the heated fluid to the multiple nozzles <NUM>, which spray the heated fluid into the airflow <NUM> to form the heated airflow <NUM>. As discussed in more detail below, the flow-deflector assembly <NUM> includes multiple plates (e.g., flow shields, diverters, baffles) that are configured to distribute (e.g., spread, disperse) the airflow <NUM> to facilitate mixing the airflow <NUM> with the heated fluid from the nozzles <NUM> upstream of a filter <NUM> of the air intake system <NUM>. Thus, the flow-deflector assembly <NUM> operates to block a buildup of ice on the filter <NUM> and/or to generally maintain the heated airflow <NUM> at a temperature that is within desirable limits across a face of the filter <NUM> (e.g., across all or most of the face of the filter <NUM>) to enable proper operation of the air intake system <NUM> and to provide satisfactory performance of the gas turbine system <NUM>.

The bleed conduit <NUM> may be one or more bleed conduits that are coupled to the compressor <NUM> at or downstream from each, some, or one of the one or more compressor stages. The compressor <NUM> increases the pressure and temperature of the compressed airflow <NUM> with each subsequent compressor stage, and thus the bleed conduit <NUM> may extract the compressed airflow <NUM> at a particular compressor stage with a suitable pressure and temperature for use in the anti-icing system <NUM>. In certain embodiments, the anti-icing system <NUM> may selectively extract the compressed airflow <NUM> (e.g., as the heated fluid, as indicated by arrow <NUM>) through the bleed conduit <NUM> based on a temperature (e.g., monitored by one or more sensors, S) of the airflow <NUM> entering the air intake system <NUM>, a temperature of the heated airflow <NUM> at the filter <NUM>, and/or a temperature of the heated airflow <NUM> at the compressor <NUM>. For example, with a progressively lower ambient temperature, the anti-icing system <NUM> may extract the compressed airflow through a greater number of bleed conduits <NUM> and/or through bleed conduits <NUM> at progressively later compressor stages of the compressor <NUM>.

In operation, the air intake system <NUM> receives the airflow <NUM> through an air hood <NUM> coupled to the air intake conduit <NUM>. In some embodiments, the airflow <NUM> may pass through or across one or more additional air intake components, such as multiple silencer baffles <NUM>, one or more coalescers <NUM>, the nozzles <NUM>, the manifold <NUM>, the flow-deflector assembly <NUM>, and the filter <NUM>. Together, the nozzles <NUM>, the manifold <NUM>, and the flow-deflector assembly <NUM> may be considered an anti-icing assembly <NUM> (e.g., inlet bleed heat [IBH] assembly).

As noted above, the anti-icing system <NUM> also includes multiple sensors S that are configured to monitor operational conditions, such as the temperature, humidity, or various conditions conducive to ice formation. For example, the anti-icing system <NUM> may include one or more sensors <NUM> positioned at or outside of the air hood <NUM> to thereby monitor ambient conditions of the air (e.g., ambient temperature, humidity, etc.) The anti-icing system <NUM> may include one or more sensors <NUM> positioned at or upstream of the manifold <NUM>, such as between the manifold <NUM> and the air hood <NUM>. The anti-icing system <NUM> also may include one or more sensors <NUM> positioned at or downstream from the manifold <NUM>, such as at the filter <NUM> or between the manifold <NUM> and the filter <NUM>. Furthermore, the anti-icing system <NUM> may include one or more sensors <NUM> positioned downstream of the filter <NUM>, such as at or upstream of the intake of the compressor <NUM>. The anti-icing system <NUM> also may include one or more sensors <NUM> disposed along each of the bleed conduits <NUM>.

The anti-icing system <NUM> also includes a controller <NUM> communicatively coupled to the sensors <NUM>, <NUM>, <NUM>, <NUM>, and <NUM>, a valve <NUM> disposed along each bleed conduit <NUM>, and various components of the gas turbine system <NUM> (e.g., valves that control a supply of the fuel from the fuel supply <NUM> to the fuel nozzles <NUM>). The controller <NUM> has a processor <NUM>, a memory <NUM>, and computer-readable instructions <NUM> stored on the memory <NUM> and executable by the processor <NUM>. The controller <NUM> obtains sensor readings from the sensors S, and the controller <NUM> may use the computer-readable instructions <NUM> to regulate the operation of the anti-icing system <NUM> based on these sensor readings, upper and lower thresholds for temperature (e.g., desirable limits or targets), computer models, and/or user input. For example, if the temperature at one or more of the sensors falls below a lower temperature threshold (e.g., <NUM> degrees Celsius), then the controller <NUM> may send a control signal to an actuator (e.g., an electric actuator) of the valve <NUM> to partially or entirely open the valve <NUM> to enable a flow of the heated fluid to pass through the bleed conduit <NUM> to the manifold <NUM>. Although <FIG> illustrates the compressed airflow from the compressor <NUM> as the heated fluid supplied to the manifold <NUM>, certain embodiments of the anti-icing system <NUM> may be additionally or alternatively coupled to one or more other sources of heated fluid (e.g., other sources of heated airflow, exhaust gas).

In this way, the controller <NUM> may monitor the anti-icing system <NUM> and control the flowrate and/or the temperature of the heated fluid into the manifold <NUM> and through the nozzles <NUM> into the air intake conduit <NUM>, thereby adjusting the temperature in the air intake conduit <NUM> to inhibit and/or remove ice formation on the filter <NUM> or elsewhere in the air intake system <NUM> and/or in the compressor <NUM>. As discussed in more detail below, the flow-deflector assembly <NUM> distributes the airflow <NUM> to facilitate mixing between the airflow <NUM> and the heated fluid ejected by the nozzles <NUM> to thereby adjust the temperature of the heated airflow <NUM> and/or to make the temperature of the heated airflow <NUM> more uniform within a region of the air intake conduit <NUM> downstream of the anti-icing assembly <NUM> (e.g., between the anti-icing assembly <NUM> and the filter <NUM>, and particularly across a face of the filter <NUM>).

<FIG> is a schematic of an embodiment of the anti-icing system <NUM> coupled to the air intake system <NUM>. To facilitate discussion, the anti-icing system <NUM> and the air intake system <NUM> may be described with reference to a longitudinal axis or direction <NUM>, a lateral axis or direction <NUM>, a vertical axis or direction <NUM>, and/or a circumferential axis or direction <NUM>.

As shown, the anti-icing system <NUM> includes the anti-icing assembly <NUM> having the nozzles <NUM>, the manifold <NUM>, and the flow-deflector assembly <NUM>. The airflow <NUM> enters the air intake system <NUM> through the air hood <NUM>, which may include multiple angled baffles to block entry of rain or snow. The airflow <NUM> may also pass through multiple silencer baffles <NUM> and/or coalescers <NUM> upstream of the anti-icing assembly <NUM>. The silencer baffles <NUM> have one or more acoustic attenuation features (e.g., acoustic attenuation surface features, internal material) to help reduce acoustic noise caused by the airflow <NUM> passing through the air intake system <NUM>. The coalescers <NUM> are configured to remove water from the airflow <NUM>. The coalescers <NUM> may include mechanical coalescers, electrostatic coalescers, or a combination thereof.

After the airflow <NUM> mixes with the heated fluid to form the heated airflow <NUM>, the heated airflow <NUM> may then pass through the filter <NUM>. The filter <NUM> may include any number and type of filters. The filter <NUM> may be configured to filter particulate and moisture; however, the filter <NUM> may be susceptible to ice formation at certain low temperatures and/or heat damage at certain high temperatures. Although the above components are illustrated in a sequence (e.g., upstream to downstream) in the air intake conduit <NUM>, various embodiments may rearrange each of the foregoing components in any suitable order, except that the anti-icing assembly <NUM> remains upstream from the filter <NUM>.

As shown, the flow-deflector assembly <NUM> includes multiple plates <NUM> that are configured to distribute the airflow <NUM> across a cross-sectional area of the air intake conduit <NUM> to facilitate mixing with the heated fluid output by the nozzles <NUM>. The mixing of the airflow <NUM> and the heated fluid forms the heated airflow <NUM> and provides a more uniform, desirable temperature of the heated airflow <NUM> at a face <NUM> (e.g., longitudinally-facing surface; upstream surface) of the filter <NUM> to thereby block the buildup of ice at the filter <NUM> and/or in other regions of the air intake system <NUM>.

The nozzles <NUM> are arranged along the lateral axis <NUM> and the vertical axis <NUM> (e.g., spaced apart in a grid-like pattern). In the illustrated embodiment, each nozzle <NUM> is coupled to the manifold <NUM> on an upstream side of the manifold <NUM>, such that the manifold <NUM> is positioned between the nozzle <NUM> and the filter <NUM> along the longitudinal axis <NUM>. However, it should be appreciated that each nozzle <NUM> may be coupled to the manifold <NUM> on a downstream side of the manifold <NUM>, such that the nozzle <NUM> is positioned between the manifold <NUM> and the filter <NUM> along the longitudinal axis <NUM>. In any case, regardless of the relative positioning of the nozzles <NUM> and the manifold <NUM>, the plates <NUM> of the flow-deflector assembly <NUM> are positioned on an upstream side of the nozzles <NUM>, such that the nozzles <NUM> are positioned between the plates <NUM> and the filter <NUM> along the longitudinal axis <NUM>. The plates <NUM> are generally stacked along the vertical axis <NUM> and are spaced apart from one another along the vertical axis <NUM>, and each of the plates <NUM> generally extends along the lateral axis <NUM>. The plates <NUM> operate to direct and/or to guide the airflow <NUM> through gaps <NUM> (e.g., vertically-extending gaps) between the plates <NUM>. It should be appreciated that the plates <NUM> may be supported via one or more brackets <NUM>, which may extend between and couple the plates <NUM> to the manifold <NUM> or to any other suitable structure within the air intake system <NUM> to position the plates <NUM> adjacent to and/or upstream of the nozzles <NUM>.

Each nozzle <NUM> includes one or more outlets <NUM>. The outlets <NUM> may have any suitable form. For example, the outlets <NUM> may include one or more continuous rings that extend circumferentially about the nozzle <NUM> (as shown), or the outlets <NUM> may be discrete openings spaced circumferentially about the nozzle <NUM>. The outlets <NUM> may also be positioned at any suitable location between a first, upstream end of the nozzle <NUM> and a second, downstream end of the nozzle <NUM> (e.g., any suitable location along the longitudinal axis <NUM>). For example, the outlets <NUM> may be positioned proximate to the first, upstream end (e.g., closer to the first, upstream end) to position the outlets <NUM> closer to the plates <NUM> and to provide more space (e.g., distance along the longitudinal axis <NUM>; as compared to being positioned proximate to the second, downstream end) for mixing of the airflow <NUM> and the heated fluid upstream of the filter <NUM>. It should be appreciated that the placement of the nozzles <NUM> on the upstream side of the manifold <NUM> also provides more space (e.g., distance along the longitudinal axis <NUM>; as compared to each nozzle <NUM> being coupled to the manifold on the downstream side of the manifold <NUM>) for mixing the airflow <NUM> and the heated fluid upstream of the filter <NUM>. Thus, the components of the anti-icing assembly <NUM> may be arranged to provide an efficient anti-icing process within a given size of the air intake conduit <NUM> (e.g., that has limited space within the air intake conduit <NUM>; retrofitted) and/or may enable use of a smaller size air intake conduit <NUM> (e.g., as compared to air intake conduits that are devoid of the anti-icing assembly <NUM>).

Regardless of their form and/or position, the outlets <NUM> may inject (e.g., spray) the heated fluid radially-outwardly from the nozzle <NUM> and/or cross-wise to the airflow <NUM>, as represented by arrow <NUM>. The plates <NUM> of the flow-deflector assembly <NUM> direct the airflow <NUM> into the heated fluid, thereby facilitating mixing of the airflow <NUM> and the injected flows of the heated fluid. In particular, the plates <NUM> direct the airflow <NUM> in a crosswise direction relative to the longitudinal axis <NUM>, thereby providing a low velocity recirculation region downstream of the plates <NUM> and adjacent the outlets <NUM> for improved penetration of the injected flows of the heated fluid into the airflow <NUM>. Thus, the plates <NUM> may improve the anti-icing capability of the anti-icing system <NUM>, block formation of cold spots that could otherwise experience ice formation, block formation of hot spots that could otherwise damage the filter <NUM>, enable use of a smaller number of nozzles <NUM> with a greater spacing between adjacent nozzles <NUM>, and/or enable use of a smaller size air intake conduit <NUM>.

In the illustrated embodiment, the heated fluid includes the compressed airflow extracted from the compressor <NUM>, as discussed above with reference to <FIG>. The compressed air from the compressor <NUM> may be approximately <NUM> to <NUM> degrees Celsius, having approximate pressures of <NUM> to <NUM> Kilopascals. However, the anti-icing system <NUM> may directly or indirectly use any one or more heated fluids to elevate the temperature of the airflow <NUM>. For example, as illustrated, the heated fluid may be any suitable heated fluid that can be directly injected into the airflow <NUM> through the nozzles <NUM> to elevate the temperature of the airflow <NUM>, including, but not limited to, a heated air or exhaust gas.

<FIG> is a perspective view of an embodiment of the anti-icing assembly <NUM> of the anti-icing system <NUM> within a portion of the air intake conduit <NUM> of the air intake system <NUM>. As shown, the anti-icing assembly <NUM> includes the nozzles <NUM>, the manifold <NUM>, and the flow-deflector assembly <NUM> with the plates <NUM>. The nozzles <NUM> are arranged in a grid-like pattern (e.g., two-dimensional grid), and the nozzles <NUM> are mounted on and/or are fluidly coupled to various conduits of the manifold <NUM>. The plates <NUM> may also be mounted on (e.g., via the brackets <NUM> of <FIG>; the brackets <NUM> are omitted in other drawings for image clarity) the manifold <NUM>. As shown, the plates <NUM> are generally spaced apart from one another along the vertical axis <NUM>, and each of the plates <NUM> generally extends along the lateral axis <NUM>. The plates <NUM> operate to direct and/or to guide the airflow <NUM> through the gaps <NUM> (e.g., vertically-extending gaps) between the plates <NUM>. The airflow <NUM> may contact and may be diverted by the plates <NUM> to facilitate mixing between the airflow <NUM> and the heated fluid sprayed radially outwardly from the nozzles <NUM>. The airflow <NUM> and the heated fluid may mix to form the heated airflow <NUM>.

<FIG> is a side view of an embodiment of the anti-icing assembly <NUM>, and <FIG> is a side view of a portion of the embodiment of the anti-icing assembly <NUM> of <FIG> taken within line <NUM>-<NUM> (with the manifold <NUM> excluded for image clarity). As shown, the anti-icing assembly <NUM> includes the nozzles <NUM>, the manifold <NUM>, and the flow-deflector assembly <NUM> with the plates <NUM>. In the illustrated embodiment, each nozzle <NUM> is positioned on an upstream side of the manifold <NUM>, such that the nozzles <NUM> are positioned between the plates <NUM> and the manifold <NUM> along the longitudinal axis <NUM>. The plates <NUM> are provided on an upstream side of the nozzles <NUM> to facilitate mixing between the airflow <NUM> and the heated fluid that is sprayed radially-outwardly from the nozzles <NUM> via the outlets <NUM> (e.g., as shown by the arrows <NUM>).

In the illustrated embodiment, at least some of the plates <NUM> have a v-shape cross-sectional shape with an apex <NUM> positioned upstream of ends <NUM>. In some embodiments, each of the ends <NUM> is positioned adjacent to and/or is substantially aligned with (e.g., along the vertical axis <NUM>) a radially-outer wall of the nozzle <NUM> (e.g., with the outlets <NUM> of the nozzle <NUM>) to facilitate mixing between the airflow <NUM> and the heated fluid.

As shown, the plates <NUM> may have different cross-sectional shapes compared to one another. For example, outer-most plates <NUM>, <NUM> positioned adjacent to a wall of the air intake conduit <NUM> may not have the v-shape cross-sectional shape, but instead may be a linear plate that is tapered or angled (e.g., an outer-most end is upstream from an inner-most end) to direct the airflow <NUM> away from the wall of the air intake conduit <NUM> and toward the nozzles <NUM>. In some embodiments, intermediate plates <NUM>, <NUM> may have an off-center v-shape cross-sectional shape (e.g., asymmetrical about a center line through the apex <NUM>) in which a first section <NUM> (e.g., outer section) is shorter than a second section <NUM> (e.g., inner section) to direct a greater portion of the airflow <NUM> that contacts each of the intermediate plates <NUM>, <NUM> toward a center region <NUM> (e.g., along a center line or axis) within the air intake conduit <NUM> and to direct a smaller portion of the airflow <NUM> that contacts each of the intermediate plates <NUM>, <NUM> toward the walls of the air intake conduit <NUM> (e.g., toward an outer region within the air intake conduit <NUM>; below or above all of the nozzles <NUM>). In some embodiments, a respective length (e.g., from the apex <NUM> to the end <NUM>) of the first section <NUM> may be between about <NUM> to <NUM>, <NUM> to <NUM>, or <NUM> to <NUM> percent of the respective length of the second section <NUM>. In some embodiments, the respective length of the first section <NUM> may be about <NUM> percent of the respective length of the second section <NUM>. The terms "about" or "approximately," when used herein in relation to a measurement of length or angle, are intended to encompass the stated value ±<NUM> percent or ±<NUM> degrees. In some embodiments, central plates <NUM>, <NUM> may have a center v-shape cross-sectional shape (e.g., symmetrical about a center line through the apex <NUM>) with a first section <NUM> and a second section <NUM> being approximately equal in length to direct the airflow <NUM> that contacts each of the central plates <NUM>, <NUM> to each side of the central plate <NUM>, <NUM> in approximately equal amounts.

The sections that form the v-shape cross sections, when joined to one another, define an angle. For example, the first section <NUM> and the second section <NUM> of the off-center v-shape cross-sectional shape of the intermediate plates <NUM>, <NUM> may be joined to one another to define an angle <NUM>, and the first section <NUM> and the second section <NUM> of the center v-shape cross-sectional shape of the central plates <NUM>, <NUM> may be joined to one another to define an angle <NUM>. The angles <NUM>, <NUM> may be the same or different from one another. In some embodiments, the angle <NUM> may be greater than the angle <NUM>. In some embodiments, the angle <NUM> and/or the angle <NUM> may be between about <NUM> to <NUM> degrees, <NUM> to <NUM> degrees, or <NUM> to <NUM> degrees. In some embodiments, the angle <NUM> and/or the angle <NUM> may be approximately <NUM> degrees. It should also be appreciated that the dimensions of the first sections <NUM>, the dimensions of the second sections <NUM>, and/or the angle <NUM> may vary across different intermediate plates <NUM>, <NUM>. For example, one intermediate plate <NUM>, <NUM> may have its first section <NUM> be between <NUM> to <NUM> percent of the second section <NUM>, while another intermediate plate <NUM>, <NUM> may have its first section <NUM> be between <NUM> to <NUM> percent of the second section <NUM>. Similarly, the dimensions of the first sections <NUM>, the dimensions of the second sections <NUM>, and/or the angle <NUM> may vary across different central plates <NUM>, <NUM>.

In the illustrated embodiment, the flow-deflector assembly <NUM> includes two outer-most plates <NUM>, <NUM>, two intermediate plates <NUM>, <NUM>, and three central plates <NUM>, <NUM>. However, it should be appreciated that various other arrangements and combinations are envisioned. For example, the flow-deflector assembly <NUM> may include the two outer-most plates <NUM>, <NUM> without the v-shape cross-sectional shape, four intermediate plates <NUM>, <NUM> with the off-center v-shape cross-sectional shape, and one central plate <NUM> with the center v-shape cross-sectional shape. Indeed, the flow-deflector assembly <NUM> may include any number of outer-most plates <NUM>, <NUM> without the v-shape cross-sectional shape, any number of intermediate plates <NUM>, <NUM> with the off-center v-shape cross-sectional shape, and any number of intermediate plates <NUM>, <NUM> with the center v-shape cross-sectional shape.

Furthermore, each plate <NUM> with the v-shape cross-sectional shape may have a respective width along the longitudinal axis <NUM> and a respective height along the vertical axis <NUM>. The respective widths and/or the respective heights may be the same or different from one another. As shown, the respective height of each plate <NUM> with the v-shape cross-sectional shape (e.g., each plate <NUM> other than the outer-most plates <NUM>, <NUM>) may cause each plate <NUM> to extend vertically across two rows of nozzles <NUM>. However, it should be appreciated that various arrangements of the plates <NUM> are envisioned. For example, any number of plates <NUM> (e.g., <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, or more plates <NUM>) may be used in the flow-deflector assembly <NUM>. Furthermore, each plate <NUM> may extend vertically across more than two rows of nozzles <NUM>. In some embodiments, one or more plates <NUM> may extend vertically across a first number of nozzles <NUM>, and one or more plates <NUM> may extend vertically across a second number of nozzles <NUM>. It should be appreciated that one or more of the plates <NUM> may have any other suitable cross-sectional shape, such as a u-shape with a curvature, or the like. In some embodiments, one or more of the plates <NUM> may include through-holes or openings to enable at least some of the airflow <NUM> to flow through the plates <NUM> (e.g., in addition to flowing around the plates <NUM> through the gaps <NUM> between the plates <NUM>).

<FIG> is a side view of a portion of an embodiment of an anti-icing assembly <NUM> that may be used in an anti-icing system <NUM> in the air intake conduit <NUM> of the air intake system <NUM> of <FIG>. As discussed above, each nozzle <NUM> may be coupled to the manifold <NUM> on an upstream side of the manifold <NUM>, such that the manifold <NUM> is positioned between the plates <NUM> and the nozzle <NUM> along the longitudinal axis <NUM>. In such cases, the airflow <NUM> is distributed by plates <NUM> of the flow-deflector assembly <NUM> toward the nozzles <NUM>, and the airflow <NUM> mixes with the heated fluid that is ejected by through the outlets <NUM>, as shown by the arrow <NUM>, to form the heated airflow <NUM> that flows toward the filter.

Advantageously, the plates of the flow-deflector assembly disclosed herein direct the airflow and the heated fluid into recirculation zones for improved mixing between the anti-icing assembly <NUM> and the filter <NUM> within the air intake system <NUM>. The improved mixing may block the buildup of ice on the filter <NUM>, block damage due to extremely high temperatures, and the like by providing the heated fluid within desirable temperature limits in a substantially uniform manner across the face <NUM> of the filter <NUM>. The plates <NUM> may be positioned upstream from and adjacent to the nozzles <NUM>, which may be positioned upstream from the manifold <NUM>. However, other configurations are envisioned (e.g., as shown in <FIG>).

The technical effects of the anti-icing techniques disclosed herein include providing more effective mixing of the airflow and the heated fluid within the air intake system <NUM>. Under certain conditions (e.g., cold ambient conditions), the mixing may result in more effective removal, reduction, and/or blocking of ice buildup on the filter <NUM> of the air intake system <NUM> of the gas turbine system <NUM> as compared to traditional systems. The plates <NUM> of the flow-deflector assembly <NUM> of the anti-icing assembly <NUM> may include various mechanical features (e.g., arrangement and/or shape of the plates) to facilitate mixing of the airflow with the heated fluid to provide the more effective removal, reduction, and/or blocking of ice buildup on the filter <NUM> of the air intake system <NUM> of the gas turbine system <NUM>. Under certain conditions (e.g., hot ambient conditions and/or IBH maximum flow), the mixing may result in more effective reduction and/or blocking of hot spots on the filter <NUM> of the air intake system <NUM> of the gas turbine system <NUM> as compared to traditional systems. The anti-icing assembly <NUM> may be cost-effective in that the components may be configured to fit within and/or interface with existing anti-icing systems and/or existing air intake systems (e.g., retrofit).

Claim 1:
An anti-icing system (<NUM>) for a gas turbine system (<NUM>), the anti-icing system (<NUM>) comprising:
a plurality of nozzles (<NUM>), wherein each nozzle (<NUM>) of the plurality of nozzles (<NUM>) comprises one or more outlets (<NUM>) that are configured to inject a heated fluid into an airflow (<NUM>) within an air intake conduit (<NUM>); and
a plurality of plates (<NUM>) disposed upstream of the one or more outlets (<NUM>), wherein each plate (<NUM>) of the plurality of plates (<NUM>) extends laterally across the air intake conduit (<NUM>) and is vertically spaced apart from one or more adjacent plates (<NUM>) to define one or more vertically-extending gaps (<NUM>), and the plurality of plates (<NUM>) is configured to direct the airflow (<NUM>) through the one or more vertically-extending gaps (<NUM>) to spread the airflow (<NUM>) upstream of the one or more outlets (<NUM>) to facilitate mixing of the heated fluid and the airflow (<NUM>), characterized in that
a respective height of at least one plate (<NUM>) of the plurality of plates (<NUM>) causes the at least one plate (<NUM>) of the plurality of plates (<NUM>) to extend vertically across two vertically-stacked rows of the plurality of nozzles (<NUM>).