Systems and methods for cooling endwalls in rotary machines

Abstract

To provide a serpentine core for use in cooling portions of a hot gas path in a rotary machine.SOLUTION: A core for use in cooling a component used in a rotary machine is provided. The core includes a passage including a divider separating a first inlet portion and a second inlet portion to define a split pass inlet, which is fluidly coupled to at least one first pass, at least one second pass and at least one turn. The at least one first pass channels a flow of cooling fluid in a first direction from the split pass inlet. The at least one second pass channels the flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes a direction of the flow of the cooling fluid from the first direction to the second direction. The at least one first pass, the at least one second pass and the at least one turn are arranged such that the passage defines a serpentine passage.SELECTED DRAWING: Figure 6

Description

[Technical Field]

[0001] The field of the disclosure relates generally to cooling systems, and more particularly to impingement cooling of rotating machine components. [Background technology]

[0002] In at least some known rotary machines, energy extracted from the gas flow in a turbine is used to power a mechanical load. During operation of the rotary machine, various hot gas path components may be exposed to the hot gas flow. Over time, continued exposure to high temperatures may cause wear of the hot gas path components. For example, in some known turbines, air is compressed in a compressor and mixed with fuel in a combustor to produce hot gases. Generally, hotter gases increase the performance, efficiency, and power output of the rotary machine. To facilitate reducing the effects of high temperatures, at least some known hot gas path components are cooled. However, hotter gases may also increase thermal stresses and / or thermal degradation of the rotary machine components.

[0003] Some known hot gas path components are formed with end walls that include internal cooling systems, and a cooling fluid, such as bleed air extracted from a compressor or steam, is forced into a core defined within the end wall. At least some known cores are formed with inlet openings that direct the cooling fluid into the core and impinge the cooling fluid against the core's inner surface, thereby increasing cooling of the end wall. However, at least some known cores include pin banks that direct the cooling fluid directly from the inlet opening to at least one outlet opening, rather than directing the cooling fluid in a circuit through the end wall. Therefore, these cores are not cooled as efficiently as cores that include serpentine or circuitous paths. Furthermore, at least some known cores have serpentine or circuitous paths that direct the cooling fluid from a single inlet through the end wall. However, adjusting the pressure drop within the paths can be difficult with known cores. Summary of the Invention

[0004] In one aspect, a core for use in cooling components used in rotary machines is provided. The core includes a passageway including a first inlet section, a second inlet section, a partition, at least one first pass, at least one second pass, and at least one turn. The partition separates the first inlet section from the second inlet section such that the first inlet section, the second inlet section, and the partition define a split-pass inlet. The at least one first pass directs the flow of cooling fluid from the split-pass inlet in a first direction. The at least one second pass directs the flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes the direction of the flow of cooling fluid from the first direction to a second direction. The at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passageway defines a serpentine path.

[0005] In another aspect, a gas turbine system is provided. The gas turbine system includes a turbine section including an inner endwall, an outer endwall, a plurality of airfoils, and a core. The turbine section is coupled in flow communication with a combustion system. The inner endwall is aligned along a longitudinal axis of the gas turbine system. Surrounding The outer end wall is aligned with the longitudinal axis of the gas turbine system and the inner end wall SurroundingEach of the plurality of airfoils extends between an outer end wall and an inner end wall. A core is positioned within at least one of the outer end wall and the inner end wall to cool the at least one of the outer end wall and the inner end wall. The core includes a passage including a first inlet portion, a second inlet portion, a partition, at least one first pass, at least one second pass, and at least one turn. The partition separates the first inlet portion from the second inlet portion such that the first inlet portion, the second inlet portion, and the partition define a split-pass inlet. The at least one first pass directs the flow of cooling fluid from the split-pass inlet in a first direction. The at least one second pass directs the flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes the direction of the flow of cooling fluid from the first direction to a second direction. The at least one first pass, the at least one second pass, and the at least one turn are arranged such that the path defines a serpentine path.

[0006] In another aspect, a method for cooling a rotary machine component is provided. The method includes inserting a core into a plenum within the component. The core includes a passage including an inlet portion, at least one first pass, at least one second pass, and at least one turn. The inlet portion includes a first inlet portion, a second inlet portion, and a partition. The partition separates the first inlet portion from the second inlet portion such that the inlet portion is a split-pass inlet. The method also includes directing a flow of cooling fluid to the first inlet portion and the second inlet portion. The method further includes directing the flow of cooling fluid from the first inlet portion and the second inlet portion to at least one first pass. The flow of cooling fluid from the first inlet portion merges with the flow of cooling fluid from the second inlet portion, and the at least one first pass directs the flow of cooling fluid in a first direction. The method also includes directing the flow of cooling fluid from the at least one first pass to at least one turn. The at least one turn changes the direction of the cooling fluid flow from a first direction to a second direction opposite the first direction. The method further includes directing the cooling fluid flow from the at least one turn to at least one second path. The at least one first path, the at least one second path, and the at least one turn are arranged such that the path defines a serpentine path.

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

[0008] [Figure 1] 1 is a schematic diagram of an exemplary rotating machine. [Figure 2] 2 is an enlarged schematic view of an exemplary turbine stage of the rotary machine shown in FIG. 1. [Figure 3] FIG. 3 is a perspective view of an exemplary stationary airfoil, outer endwall, and inner endwall that may be used with the turbine shown in FIG. 2. [Figure 4]3 is a perspective top view of the stationary airfoil, outer endwall, and inner endwall shown in FIG. 2, and an exemplary core extending through the transparent outer and inner endwalls. [Figure 5] FIG. 5 is a radial top cross-sectional view of the outer end wall shown in FIG. 4. [Figure 6] FIG. 6 is a radial top view of the exemplary core shown in FIGS. 3-5. [Figure 7] 7 is a flow diagram of an exemplary method for cooling an end wall, such as the end wall shown in FIGS.

[0009] Unless otherwise specified, the drawings provided herein are intended to illustrate features of embodiments of the present disclosure. These features are believed to be applicable in a wide variety of systems that include one or more embodiments of the present disclosure. Thus, the drawings are not intended to include all conventional features known to those skilled in the art that are required for practicing the embodiments disclosed herein. DETAILED DESCRIPTION OF THE INVENTION

[0010] In the following specification and claims, reference will be made to a number of terms that shall be defined to have the following meanings.

[0011] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise.

[0012] Unless otherwise specified, terms such as "generally," "substantially," and "approximately" used herein indicate that the modified term may apply only to an approximate degree, as recognized by one of ordinary skill in the art, rather than to an absolute or complete degree. Thus, values ​​modified by terms such as "approximately," "about," and "substantially" are not limited to the exact value specified. In at least some instances, terms such as "approximately" may correspond to the precision of the instrument used to measure the value. Range limits may be specified here and throughout the specification and claims. Such ranges are combinable and / or interchangeable, and include all subranges contained herein unless the context or language dictates otherwise. Additionally, unless otherwise specified, terms such as "first," "second," and the like are used herein merely as labels and are not intended to impose any ordering, positioning, or hierarchical requirements on the items to which they refer. Further, a reference to, for example, a "second" item does not require or exclude the presence of, for example, a "first" or lower-numbered item, or a "third" or higher-numbered item.

[0013] As used herein, the terms "axial" and "axially" refer to directions and orientations that extend substantially parallel to the longitudinal axis of a rotary machine. Also, the terms "radial" and "radially" refer to directions and orientations that extend substantially perpendicular to the longitudinal axis of a rotary machine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations that extend in an arc about the longitudinal axis of a rotary machine. Furthermore, as used herein, the term "upstream" refers to the forward or inlet end of a rotary machine, and the term "downstream" refers to the aft or exhaust end of a rotary machine. When describing the flow of fluid through a component, the direction from which the fluid is flowing is described as "upstream" and the direction from which the fluid is flowing is described as "downstream."

[0014] The system described herein relates to a serpentine core for use in a cooling portion of a hot gas path within a rotary machine. Specifically, in an exemplary embodiment, the rotating component includes an outer endwall formed in a nozzle of a turbine section within the rotary machine. The outer endwall includes a core for use in cooling the outer endwall. The core includes a serpentine passage including an inlet portion, a first pass, a second pass, and a turn. The inlet portion includes a partition, a first inlet portion, and a second inlet portion. The partition separates the first inlet portion from the second inlet portion to define a split-pass inlet. The first pass, the second pass, and the turn include multiple outlets that direct cooling fluid from the core to the hot gas path to form a cooling film on the outer endwall. Multiple core ties direct cooling fluid from an upstream portion of the core to a downstream portion of the core, allowing the downstream portion to be replenished with low-temperature cooling fluid.

[0015] In the exemplary embodiment, the cooling fluid is directed through the first passes, second passes, and turns to facilitate cooling the outer endwall from within the core. The serpentine configuration of the first passes, second passes, and turns allows the cooling fluid to cool a larger area of ​​the outer endwall, thus increasing overall heat transfer between the cooling fluid and the outer endwall. In addition, the serpentine configuration allows the cooling fluid to circulate at a lower pressure substantially equal to the pressure of the combustion gases at the nozzle throat. Furthermore, the width of each of the first passes, second passes, and turns is selected to facilitate modifying or adjusting the pressure drop of the cooling fluid through the first passes, second passes, and turns, increasing overall heat transfer between the cooling fluid and the outer endwall. The outlet also directs the cooling fluid into the hot gas path, facilitating the formation of a cooling film across the stator endwall. In addition, the core tie replenishes the cooling fluid to downstream portions of the core and provides inspection access, rigidity during core formation, and leachability for ceramic core removal after the casing process.

[0016] 1 is a schematic diagram of an exemplary rotary machine 100, i.e., a turbomachine, or more specifically, a turbine engine. In the exemplary embodiment, rotary machine 100 is a gas turbine engine. Alternatively, rotary machine may be any other turbine engine and / or rotating machine, including, but not limited to, a steam turbine engine, a gas turbofan aircraft engine, other aircraft engines, a wind turbine, a compressor, and a pump. In the exemplary embodiment, gas turbine engine 100 includes an intake section 102, a compressor section 104 coupled downstream from intake section 102, a combustor section 106 coupled downstream from compressor section 104, a turbine section 108 coupled downstream from combustor section 106, and an exhaust section 110 coupled downstream from turbine section 108. Turbine section 108 is coupled to compressor section 104 via a rotor shaft 112.

[0017] It should be noted that, as used herein, the term “couple” is not limited to a direct mechanical, thermal, electrical, and / or flow communication connection between components, but can also include an indirect mechanical, thermal, electrical, and / or flow communication connection between multiple components. In the exemplary embodiment, combustor section 106 includes multiple combustors 114. Combustor section 106 is coupled to compressor section 104 such that each combustor 114 is in flow communication with compressor section 104. Rotor shaft 112 is further coupled to a load 116, such as, but not limited to, an electrical generator and / or a mechanical drive application. In the exemplary embodiment, compressor section 104 and turbine section 108 each include at least one rotor assembly 118 coupled to rotor shaft 112.

[0018] During operation, the intake section 102 channels air 120 toward the compressor section 104. The compressor section 104 compresses the intake air 120 to a higher pressure before discharging the compressed air 122 toward the combustor section 106. The compressed air 122 is channeled to the combustor section 106, where it is mixed with fuel (not shown) and combusted to generate hot combustion gases 124. The combustion gases 124 are channeled downstream toward the turbine section 108, where they impinge on turbine blades (not shown), converting thermal energy into mechanical rotational energy that is used to drive the rotor assembly 118 about a longitudinal axis 126. Often, the combustor section 106 and the turbine section 108 are referred to as the hot gas section of the turbine engine 100. The exhaust gases 128 are then discharged through the exhaust section 110 to the ambient atmosphere or to a steam turbine (not shown) if the rotary machine 100 is a gas turbine that is part of a combined cycle power plant.

[0019] 2 is an enlarged schematic view of an exemplary turbine stage 200 of turbine engine 100 (shown in FIG. 1 ). Stage 200 includes a plurality of radially extending stationary airfoils 202 spaced circumferentially about longitudinal axis 126 and a plurality of radially extending rotating airfoils 204 spaced circumferentially about longitudinal axis 126 downstream from stationary airfoils 202. The radial direction is indicated by arrow 218. Each rotating airfoil 204 is coupled to rotor shaft 112 (shown in FIG. 1 ) via a disk 230 and extends radially outward toward a casing 208.

[0020] In the exemplary embodiment, each stationary airfoil 202 extends radially inward from a first end 216 that is coupled to an outer endwall 207 of a casing 208 of the turbine section 108 along a radial direction 218 to a second end 214 that is coupled to an inner endwall 209 (outer endwall 207 and inner endwall 209 are shown in FIG. 3 ). Additionally, each stationary airfoil 202 extends axially downstream from a leading edge 222 to an opposed trailing edge 224. During operation, outer endwall 207 and inner endwall 209 define a radial boundary of a hot gas flow path 232, whereby the flow of hot combustion gases 124 is directed therethrough, exposing the surfaces of outer endwall 207 and inner endwall 209 to high temperatures and potential thermal stresses and / or thermal degradation. To mitigate such thermal effects, an internal cavity or plenum 236 is defined within outer endwall 207 and inner endwall 209 to facilitate internal impingement cooling of the interior surfaces of outer endwall 207 and inner endwall 209 .

[0021] Plenum 236 is in flow communication with coolant supply channels 233 via plenum inlets 234 defined in outer endwall 207 and inner endwall 209. In the exemplary embodiment, coolant supply channels 233 direct a cooling fluid 240, such as a flow of compressed bleed air, from compressor section 104 (shown in FIG. 1 ) toward plenum inlets 234. Alternatively, cooling fluid 240 may be any suitable fluid other than air. The term “fluid,” as used herein, includes any flowing medium or material, including, but not limited to, air or steam. In the exemplary embodiment, stage 200 is a first stage in turbine section 108, and stationary airfoil 202, outer endwall 207, and inner endwall 209 define a first-stage turbine nozzle immediately downstream of combustor section 106 (shown in FIG. 1 ). In an alternative embodiment, stage 200 is any other stage in turbine section 108. In the exemplary embodiment, plenum 236 extends axially aft into outer endwall 207 and inner endwall 209 .

[0022] FIG. 3 is a perspective view of the stationary airfoil 202, outer endwall 207, and inner endwall 209, showing an exemplary core 300 extending through the transparent outer endwall 207 and inner endwall 209. FIG. 4 is a perspective top view of the stationary airfoil 202, outer endwall 207, and inner endwall 209. FIG. 5 is a radial top cross-sectional view of the exemplary outer endwall 207. FIG. 6 is a radial top view of the exemplary core 300. As shown in FIGS. 3-5 , the core 300 is defined within a plenum 236 in the outer endwall 207 and inner endwall 209 for cooling the outer endwall 207 and inner endwall 209. More specifically, the core 300 is disposed within the outer endwall 207 and inner endwall 209 to facilitate cooling of the outer endwall 207 and inner endwall 209 by a cooling fluid 240.

[0023] 3-5, each stationary airfoil 202 includes a suction sidewall 302 and a pressure sidewall 304 (shown in FIG. 5). Adjacent stationary airfoils 202, outer endwalls 207, and inner endwalls 209 define a throat 306 (shown in FIG. 5) where the velocity of the combustion gases 124 is maximized. Outer endwall 207 includes an upstream portion 308 upstream of stationary airfoil 202 and a downstream portion 310 downstream of stationary airfoil 202. Outer endwall 207 also includes a trailing edge 312 adjacent rotating airfoil 204. In the illustrated embodiment, core 300 is defined within outer endwall 207 downstream of suction sidewall 302. However, core 300 may be positioned within outer endwall 207 such that an upstream portion 314 (shown in FIG. 5 ) of core 300 is upstream of throat 306 and a downstream portion 316 of core 300 is downstream of throat 306. Additionally, core 300 may be positioned within outer endwall 207 such that core 300 facilitates cooling of outer endwall 207 and trailing edge 312.

[0024] As shown in FIG. 6 , the core 300 includes at least one passageway 600. In the exemplary embodiment of FIG. 6 , the passageway 600 is a serpentine passageway that directs the cooling fluid 240 adjacent the outer end wall 207 and the inner end wall 209 to facilitate cooling of the outer end wall 207 and the inner end wall 209. As shown in FIGS. 3 and 4 , a similar serpentine passageway 600 can be used to direct the cooling fluid 240 adjacent the inner end wall 209 to facilitate cooling of the inner end wall 209. As used herein, a “serpentine passageway” is a conduit having at least one turn such that the passageway winds or twists. That is, a serpentine passageway does not have only a substantially linear path from the inlet to the outlet. Rather, the path from the inlet to the outlet makes at least one turn such that the serpentine passageway does not have a defined linear line-of-sight path from the inlet to the outlet. In the exemplary embodiment, serpentine passage 600 includes at least one inlet 602 and 604, a first inlet portion 606 and a second inlet portion 608 forming a split-path inlet region 610, a first pass 612, a second pass 614, at least one turn 616 disposed between first pass 612 and second pass 614, and at least one outlet 618. First pass 612, second pass 614, and turn 616 are oriented such that passage 600 is a serpentine passage. In the illustrated embodiment, serpentine passage 600 includes multiple inlets 602 and 604.

[0025] The inlets 602 and 604 receive the cooling fluid 240 from the coolant supply channel 233 ( FIG. 2 ) and direct the cooling fluid 240 to the first inlet portion 606 and the second inlet portion 608. Specifically, at least one first inlet 602 directs the cooling fluid 240 to the first inlet portion 606, and at least one second inlet 604 directs the cooling fluid 240 to the second inlet portion 608. FIG. 6 shows a single inlet 602 and 604 extending into each inlet portion 606 and 608. However, each inlet portion 606 and 608 may include multiple inlets 602 and 604. Additionally, the serpentine passage 600 may include three or more inlet portions 606 and 608. For example, the first inlet 602 may include 2 to 20 first inlets 602 that direct the cooling fluid 240 to the first inlet portion 606, and the second inlet 604 may include 2 to 20 second inlets 604 that direct the cooling fluid 240 to the second inlet portion 608. More specifically, the first inlet 602 may include 8 to 10 first inlets 602 that direct the cooling fluid 240 to the first inlet portion 606, and the second inlet 604 may include 8 to 10 second inlets 604 that direct the cooling fluid 240 to the second inlet portion 608.

[0026] A divider 620 separates first inlet portion 606 from second inlet portion 608, forming split-path inlet region 610. Divider 620 reduces width 622 of split-path inlet region 610 such that the velocity of cooling fluid 240 through split-path inlet region 610 increases. More specifically, the velocity of cooling fluid 240 through split-path inlet region 610 without divider 620 decreases because width 622 of split-path inlet region 610 increases downstream of inlets 602 and 604. Divider 620 reduces width 622 such that the velocity of cooling fluid 240 remains constant or increases as cooling fluid 240 is directed through split-path inlet region 610.

[0027] Additionally, first inlet portion 606 defines a first width 624, and second inlet portion 608 defines a second width 626. First width 624 may be the same as or different from second width 626, and first width 624 and second width 626 may be selectively sized to allow a particular volume of cooling fluid 240 to be directed through passage 600. More specifically, first width 624 and second width 626 may be sized for a particular volumetric flow rate of cooling fluid 240 such that the heat transfer coefficient of cooling fluid 240 is tailored to the particular heat transfer requirements of outer end wall 207 and / or inner end wall 209.

[0028] First inlet portion 606 and second inlet portion 608 merge into a first pass 612, with each inlet portion directing cooling fluid 240 into first pass 612. First pass 612 extends through outer endwall 207 substantially parallel to trailing edge 312 and second pass 614. First pass 612, together with first width 624 and second width 626, defines a third width 628 that can be selectively sized to allow a specific volumetric flow rate of cooling fluid 240 to flow therethrough such that the heat transfer coefficient of cooling fluid 240 is tailored to the specific heat transfer requirements of outer endwall 207 and / or inner endwall 209. First pass 612 receives cooling fluid 240 from first inlet portion 606 and second inlet portion 608 and directs cooling fluid 240 into turn 616.

[0029] The turn 616 receives the cooling fluid 240 from the first pass 612 and directs the cooling fluid 240 to the second pass 614. The first pass 612, the second pass 614, and the turn 616 are oriented such that the first pass 612 directs the cooling fluid 240 in a first direction 630 and the second pass 614 directs the cooling fluid 240 in a second direction 632 opposite the first direction 630. The turn 616 changes the direction of the flow of the cooling fluid 240 from the first direction 630 to the second direction 632. In the exemplary embodiment, the turn 616 is a 180° turn such that the first direction 630 is directly opposite the second direction 632. In alternative embodiments, first pass 612, second pass 614, and turn 616 may be oriented such that first pass 612 and second pass 614 have any orientation that enables core 300 to operate as described herein. Turn 616 receives cooling fluid 240 from first pass 612, changes the direction of flow of cooling fluid 240, and directs cooling fluid 240 into second pass 614.

[0030] Second pass 614 extends through outer end wall 207 substantially parallel to trailing edge 312 and first pass 612. Second pass 614, together with first width 624, second width 626, and third width 628, define a fourth width 634 that can be selectively sized to allow for a specific volumetric flow rate of cooling fluid 240 such that the heat transfer coefficient of cooling fluid 240 is tailored to the specific heat transfer requirements of outer end wall 207 and / or inner end wall 209. Second pass 614 receives cooling fluid 240 from turn 616 and directs cooling fluid 240 to outlet 618.

[0031] In the exemplary embodiment, core 300 includes a single first pass 612, a single second pass 614, and a single turn 616. In alternative embodiments, core 300 may include any number of passes and / or turns that enable core 300 to operate as described herein. For example, in an alternative embodiment, core 300 may include three passes and two turns. In yet another alternative embodiment, core 300 may include four passes and three turns.

[0032] Core 300 includes at least one outlet 618 downstream from throat 306. Although core 300 may include only a single outlet 618, in the exemplary embodiment, core 300 includes multiple outlets 618 that direct cooling fluid from core 300 into hot gas path 232. For example, core 300 may include at least one first outlet 636 that extends from first pass 612 through outer endwall 207 into hot gas path 232. In the exemplary embodiment, core 300 includes multiple first outlets 636, each of which extends from first pass 612 through outer endwall 207 into hot gas path 232. Cooling fluid 240 released from first outlets 636 into hot gas path 232 may form a cooling film (not shown) on outer endwall 207 that protects outer endwall 207.

[0033] Core 300 may also include at least one second outlet 638 extending from second pass 614 through outer endwall 207 and into hot gas path 232. In the exemplary embodiment, core 300 includes multiple second outlets 638, each extending from second pass 614 through outer endwall 207 and into hot gas path 232. Cooling fluid 240 discharged from second outlets 638 into hot gas path 232 may form a cooling film (not shown) on outer endwall 207 that facilitates protection of outer endwall 207.

[0034] Core 300 may further include at least one third outlet 640 (shown in FIG. 4 ) extending from second pass 614 through trailing edge 312 of inner endwall 209 into hot gas path 232. In the exemplary embodiment, core 300 includes multiple third outlets 640, each extending from second pass 614 through trailing edge 312 of outer endwall 207 into hot gas path 232. Cooling fluid 240 discharged from third outlets 640 into hot gas path 232 may form a cooling film (not shown) on trailing edge 312 of outer endwall 207 that protects trailing edge 312 of outer endwall 207.

[0035] Core 300 may also include at least one fourth outlet 642 extending from turn 616 through outer endwall 207 and into hot gas path 232. In the exemplary embodiment, core 300 includes multiple fourth outlets 642, each extending from turn 616 through trailing edge 312 of outer endwall 207 and into hot gas path 232. Cooling fluid 240 discharged from fourth outlets 642 into hot gas path 232 may form a cooling film (not shown) on outer endwall 207 that facilitates protection of outer endwall 207. Core 300 may include outlets 618 at any location that enables core 300 to operate as described herein.

[0036] The size, shape, and relative positions of the first, second, third, and fourth outlets 636, 638, 640, and 642 may be sized and arranged to facilitate tuning to a particular / desired pressure drop, volumetric flow rate, and / or heat transfer coefficient of the cooling fluid 240. For example, the first outlet 636 may have a first size, and the second outlet 638 may be sized to have a second size that is smaller than the first size of the first outlet 636. Thus, the first outlet 636 forms a cooling film (not shown) on the outer end wall 207, and the second outlet 638 supplements the cooling film with additional cooling fluid 240. Additionally, having more outlets 636, 638, 640, and 642 facilitates reducing the volumetric flow rate of the cooling fluid 240 through the passage 600, which facilitates reducing the pressure drop of the cooling fluid 240 through the passage 600. Accordingly, the size, shape, and location of the first, second, third, and fourth outlets 636, 638, 640, and 642 may be sized and arranged to facilitate adjustment of the pressure drop, volumetric flow rate, and / or heat transfer coefficient of the cooling fluid 240.

[0037] In the exemplary embodiment, first pass 612 and second pass 614 each include a plurality of turbulators or ridges 644 that create turbulence within first pass 612 and second pass 614. Specifically, turbulators 644 create turbulence within cooling fluid 240, facilitating an increase in the heat transfer coefficient of cooling fluid 240 within first pass 612 and second pass 614. Increasing the heat transfer coefficient increases the overall heat transfer between cooling fluid 240 and outer end wall 207. In the exemplary embodiment, turbulators 644 have a height (not shown) that is approximately 10% of the height of third width 628 and fourth width 634. However, turbulators 644 may have any other height that enables core 300 to operate as described herein.

[0038] In the exemplary embodiment, core 300 includes a plurality of hollow core ties 646 extending from first inlet portion 606 to second inlet portion 608 or from first pass 612 to second pass 614. Specifically, core 300 includes at least one first core tie 648 extending from first inlet portion 606 to second inlet portion 608 and at least one second core tie 650 extending from first pass 612 to second pass 614. More specifically, in the exemplary embodiment, core 300 includes a single first core tie 648 and a plurality of second core ties 650. The first and second core ties 648 and 650, which define fluid passages therein, replenish cooling fluid 240 in a downstream portion of passage 600. As cooling fluid 240 is directed through passage 600, the temperature of cooling fluid 240 increases, thereby facilitating a decrease in the heat transfer coefficient of cooling fluid 240 and a decrease in overall heat transfer between cooling fluid 240 and outer end wall 207. Core tie 646 is a “shortcut” that directs cooling fluid 240 from an upstream portion of passage 600 to a downstream portion of passage 600 without heat transfer between cooling fluid 240 and outer end wall 207. Thus, cooling fluid 240 directed through core tie 646 has a lower temperature than cooling fluid 240 directed through first pass 612, second pass 614, and turn 616. Thus, core tie 646 replenishes the downstream portion of passage 600 with cooling fluid 240 having a lower temperature, thereby facilitating an increase in the heat transfer coefficient of cooling fluid 240 and an increase in overall heat transfer between cooling fluid 240 and outer end wall 207. The core tie 646 may also be used as a test port to test the core 300 .

[0039] During operation, inlets 602 and 604 receive cooling fluid 240 from coolant supply channel 233 and direct the cooling fluid 240 to first inlet portion 606 and second inlet portion 608. First inlet portion 606 directs a portion of the cooling fluid 240 through first core tie 648 to replenish second inlet portion 608. First inlet portion 606 and second inlet portion 608 merge into first pass 612, each directing cooling fluid 240 to first pass 612. First pass 612 directs a portion of the cooling fluid 240 through second core tie 650 to replenish second pass 614 and directs another portion of the cooling fluid 240 to turn 616. First pass 612 also directs a portion of the cooling fluid through first outlet 636 to hot gas path 232 to form a cooling film on outer endwall 207. Turn 616 directs a portion of cooling fluid 240 through fourth outlet 642 to hot gas path 232 to form a cooling film on outer endwall 207 and directs the remaining cooling fluid 240 to second pass 614. Second pass 614 directs cooling fluid 240 through second and third outlets 638 and 640 to replenish the cooling film and form a cooling film on trailing edge 312. Cooling fluid 240 exchanges heat with outer endwall 207 as it is directed through passage 600. Thus, cooling fluid 240 facilitates cooling outer endwall 207 from within core 300 and forms a protective cooling film that protects outer endwall 207.

[0040] The serpentine configuration of the passage 600 allows the cooling fluid 240 to cool a larger area of ​​the outer endwall 207, thus increasing the overall heat transfer between the cooling fluid 240 and the outer endwall 207. Additionally, the serpentine orientation of the passage 600 allows the cooling fluid 240 to have a lower pressure that is approximately equal to the pressure of the combustion gases 124 at the throat 306. Furthermore, the widths 624, 626, 628, and 634 are sized to adjust the pressure drop of the cooling fluid 240 through the passage 600 and facilitate increasing the overall heat transfer between the cooling fluid 240 and the outer endwall 207. Also, the outlet 618 directs the cooling fluid 240 into the hot gas path 232 and protects the outer endwall 207 by forming a cooling film. Additionally, the core tie 646 replenishes the cooling fluid 240 in the downstream portion of the passage 600. Therefore, the arrangement of the core 300 increases the overall heat transfer between the cooling fluid 240 and the outer endwall 207.

[0041] While the description of Figures 3-6 describes the core 300 and its features in relation to the outer end wall 207, it should be understood that the core 300 may be used with similar features in the inner end wall 209 to achieve similar results and benefits.

[0042] FIG. 7 is a flow diagram of an exemplary method 700 for cooling a rotary machine component. In an exemplary embodiment, the method 700 includes inserting 702 a core into a plenum within the component. The core includes a passage including an inlet portion, at least one first pass, at least one second pass, and at least one turn between each of the first and second passes. The inlet portion includes a partition separating the first inlet portion from the second inlet portion such that the inlet portions are split-pass inlets. The method 700 also includes directing 704 a flow of cooling fluid into the first inlet portion and the second inlet portion. The method 700 further includes directing 706 the flow of cooling fluid from the first inlet portion and the second inlet portion into at least one first pass. The flow of cooling fluid from the first inlet portion merges with the flow of cooling fluid from the second inlet portion, and the at least one first pass directs the flow of cooling fluid in a first direction. The method 700 also includes directing 708 the flow of cooling fluid from the at least one first pass into at least one turn. The at least one turn changes the direction of the flow of cooling fluid from the first direction to a second direction opposite the first direction. The method 700 further includes directing 710 the flow of cooling fluid from the at least one turn into at least one second pass. The at least one first pass, the at least one second pass, and the at least one turn are arranged such that the path is a serpentine path.

[0043] The above-described system relates to a serpentine core for use in a cooling portion of a hot gas path within a rotary machine. Specifically, in an exemplary embodiment, the rotating component includes an outer endwall formed in a nozzle of a turbine section within the rotary machine. The outer endwall includes a core for use in cooling the outer endwall. The core includes a serpentine passage including an inlet portion, a first pass, a second pass, and a turn between the first and second passes. The inlet portion includes a partition separating the first inlet portion from the second inlet portion such that a split-pass inlet is defined. The first pass, the second pass, and the turn include multiple outlets, each of which directs cooling fluid from the core to the hot gas path to form a cooling film on the outer endwall. Multiple hollow core ties direct cooling fluid from an upstream portion of the core to a downstream portion of the core, allowing the downstream portion to be replenished with low-temperature cooling fluid.

[0044] In the exemplary embodiment, the cooling fluid is directed through the first passes, second passes, and turns to facilitate convective cooling of the outer endwall from within the core. The serpentine configuration of the first passes, second passes, and turns allows the cooling fluid to convectively cool a larger area of ​​the outer endwall, thus increasing overall heat transfer between the cooling fluid and the outer endwall. Additionally, the serpentine configuration allows the cooling fluid to circulate at a lower pressure substantially equal to the pressure of the combustion gases at the nozzle throat. Furthermore, the width of each of the first passes, second passes, and turns is selected to facilitate modifying or adjusting the pressure drop of the cooling fluid through the first passes, second passes, and turns, thereby increasing overall heat transfer between the cooling fluid and the outer endwall. The outlet also directs the cooling fluid into the hot gas path, facilitating the formation of a cooling film across the stator endwall. Additionally, the core ties replenish the cooling fluid in downstream portions of the core. Thus, the core achieves both endwall convective cooling and endwall film cooling.

[0045] Additionally, exemplary technical effects of the systems and methods described herein include at least one of: (a) removing heat from the rotating machine components; (b) increasing the heat transfer coefficient of the cooling fluid; (c) increasing the overall heat transfer between the cooling fluid and the rotating machine components; and (d) improving the efficiency of the rotating machine.

[0046] Exemplary embodiments of systems and methods for cooling a portion of a hot gas path of a rotary machine have been described in detail above. The methods and systems are not limited to the specific embodiments described herein; rather, system components and / or method steps may be utilized independently and separately from other components and / or steps described herein. For example, the methods may also be used in combination with other turbine components and are not limited to practice solely with the hot gas path portion of a rotary machine described herein. Rather, the exemplary embodiments may be implemented and utilized in connection with many other rotary machine applications.

[0047] Although particular features of various embodiments of the present disclosure may be shown in some drawings and not in others, this is for convenience only, and in accordance with the principles of embodiments of the present disclosure, any feature of a drawing may be referenced and / or claimed in combination with any feature of any other drawing.

[0048] This specification uses examples to disclose embodiments of the present disclosure, including the best mode, and to enable any person skilled in the art to practice the embodiments of the present disclosure, including making and using any device or system and performing any incorporated methods. The patentable scope of the embodiments described herein 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 do not differ substantially from the literal language of the claims. [Explanation of symbols]

[0049] 100 Rotating Machinery / Gas Turbine Engine / Gas Turbine System 102 Intake section 104 Compressor Section 106 Combustor Section / Combustion System 108 Turbine Section 110 Exhaust Section 112 rotor shaft 114 Combustor 116 Load 118 Rotor Assembly 120 intake air 122 Compressed Air 124 Hot Combustion Gases 126 Longitudinal Axis 128 Exhaust Gas 200 turbine stages 202 Stationary airfoil 204 Rotating airfoil section 207 Outer end wall / component 208 Casing 209 Inner end wall 214 Second End 216 First End 218 Radial / Arrow 222 leading edge 224 Trailing edge 230 discs 232 Hot Gas Path / Hot Gas Path 233 Coolant supply channel 234 Plenum Entrance 236 Plenum 240 Cooling fluid 300 cores 302 Negative pressure side wall 304 pressure side wall 306 Throat 308 Upstream section 310 downstream part 312 Trailing edge 314 Upstream section 316 Downstream section 600 aisles / serpentine aisles 602 First Entrance 604 Second Entrance 606 First entrance 608 Second entrance 610 Split path entrance area 612 First Pass 614 Second Pass 616 turns 618 Exit 620 Divider 622 width 624 First Width 626 Second Width 628 Third Width 630 First Direction 632 Second Direction 634 Fourth Width 636 Exit 1 638 Second Exit 640 Third Exit 642 Exit 4 644 Turbulator / Ridge 646 Core Thai 648 First Core Tie 650 Second Core Tie 700 methods 702 steps 704 steps 706 steps 708 steps 710 steps

Claims

1. 1. A core (300) for use in cooling a component (207, 209) used in a rotary machine (100), the component (207, 209) being at least one of an inner end wall (209) and an outer end wall (207) of a turbine section (108) of a gas turbine system (100), the core (300) comprising: A passageway (600), a first inlet portion (606); a second inlet portion (608); a partition (620) separating the first inlet portion (606) from the second inlet portion (608), the first inlet portion (606), the second inlet portion (608), and the partition (620) defining a split path inlet (610); at least one first path (612) for directing a flow of cooling fluid from the split path inlet (610) in a first direction (630); at least one second path (614) for directing the flow of the cooling fluid in a second direction (632) substantially opposite the first direction (630); at least one turn (616) for changing the direction of the cooling fluid flow from the first direction (630) to the second direction (632), wherein the at least one first pass (612), the at least one second pass (614), and the at least one turn (616) are arranged such that the path (600) defines a serpentine path (600); A passage (600) comprising It is equipped with The core (300), wherein the passage (600) further comprises a plurality of outlets (618) extending through the components (207, 209), the plurality of outlets (618) comprising at least one first outlet (636) extending from the at least one first path (612) through the components (207, 209), and a portion of the cooling fluid flow is directed through the at least one first outlet (636) to form a protective film on the components (207, 209).

2. 2. The core (300) of claim 1, wherein the passage (600) comprises at least one first inlet (602) for directing the flow of the cooling fluid to the first inlet portion (606) and at least one second inlet (604) for directing the flow of the cooling fluid to the second inlet portion (608).

3. 2. The core (300) of claim 1, wherein the at least one first pass (612) and the at least one second pass (614) each comprise a plurality of turbulators (644) for generating turbulence within the flow of the cooling fluid.

4. 2. The core (300) of claim 1, wherein the passage (600) further comprises a plurality of core ties (646) for directing a portion of the flow of the cooling fluid from an upstream portion of the passage (600) to a downstream portion of the passage (600).

5. 2. The core (300) of claim 1, wherein the passage (600) comprises at least one first core tie (648) for directing a portion of the flow of the cooling fluid between the first inlet portion (606) and the second inlet portion (608).

6. 5. The core (300) of claim 4, wherein the plurality of core ties (646) comprises at least one second core tie (650) for directing a portion of the flow of the cooling fluid from the at least one first path (612) to the at least one second path (614).

7. A gas turbine system (100) comprising: a turbine section (108) coupled in flow communication with a combustion system (106), said turbine section (108) comprising: an inner end wall (209) surrounding a longitudinal axis (126) of the gas turbine system (100); an outer end wall (207) surrounding the longitudinal axis (126) of the gas turbine system (100) and the inner end wall (209); a plurality of airfoils (202) extending between said outer end wall (207) and said inner end wall (209); a core (300) positioned in at least one of the outer end wall (207) and the inner end wall (209) for cooling the at least one of the outer end wall (207) and the inner end wall (209), the core (300) being a core according to any one of claims 1 to 6; A turbine section (108) comprising: A gas turbine system (100) comprising:

8. 8. The gas turbine system of claim 7, wherein adjacent airfoils of the plurality of airfoils define a throat therebetween, and wherein the passage further comprises an upstream portion and a downstream portion, the upstream portion being positioned upstream of the throat and the downstream portion being positioned downstream of the throat.

9. 8. The gas turbine system of claim 7, wherein the plurality of outlets comprises at least one second outlet extending from the at least one second path through at least one of the outer end wall and the inner end wall, and wherein a portion of the flow of the cooling fluid is directed through the at least one second outlet to form a protective film on at least one of the outer end wall and the inner end wall.

10. 8. The gas turbine system of claim 7, wherein at least one of the outer end wall and the inner end wall comprises a trailing edge, the plurality of outlets comprises at least one third outlet extending from the at least one second pass through the trailing edge, and a portion of the flow of the cooling fluid is directed through the at least one third outlet to form a protective film on the trailing edge.

11. 8. The gas turbine system of claim 7, wherein the plurality of outlets comprises at least one fourth outlet extending from the at least one turn through at least one of the outer end wall and the inner end wall, and wherein a portion of the flow of the cooling fluid is directed through the at least one fourth outlet to form a protective film on at least one of the outer end wall and the inner end wall.

12. A method (700) of cooling a component (207) of a rotary machine (100), wherein the component (207, 209) is at least one of an inner endwall (209) and an outer endwall (207) of a turbine section (108) of a gas turbine system (100), the method comprising: a step (702) of inserting a core (300) into a plenum in the component (207), the core (300) including a passage (600) including an inlet portion, at least one first pass (612), at least one first outlet (636) extending from the at least one first pass (612) through the component (207, 209), at least one second pass (614), and at least one turn (616), the inlet portion including a first inlet portion (606), a second inlet portion (608), and a partition (620), the partition (620) separating the first inlet portion (606) from the second inlet portion (608) such that the inlet portion is a split-path inlet (610); directing (704) a flow of cooling fluid into the first inlet portion (606) and the second inlet portion (608); directing (706) the flow of cooling fluid from the first inlet portion (606) and the second inlet portion (608) to the at least one first path (612), wherein the flow of cooling fluid from the first inlet portion (606) merges with the flow of cooling fluid from the second inlet portion (608), and the at least one first path (612) directs the flow of cooling fluid in a first direction (630); directing a first portion of the flow of cooling fluid from the at least one first path (612) through the at least one first outlet (636) to form a protective coating on the component (207, 209); directing (708) a second portion of the cooling fluid flow from the at least one first pass (612) to the at least one turn (616), the at least one turn (616) changing the direction of the cooling fluid flow from the first direction (630) to a second direction (632) opposite the first direction (630); directing (710) a second portion of the flow of cooling fluid from the at least one turn (616) to the at least one second pass (614), wherein the at least one first pass (612), the at least one second pass (614), and the at least one turn (616) are arranged such that the path (600) defines a serpentine path (600); A method (700) comprising:

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