阅读说明：本技术 用于冷却旋转机械中的端壁的系统和方法 (System and method for cooling endwalls in rotary machines ) 是由 J·基特森 D·R·布尔诺斯 于 2021-04-14 设计创作，主要内容包括：本发明题为“用于冷却旋转机械中的端壁的系统和方法”。本发明提供了一种用于冷却在旋转机械(100)中使用的部件(207)的芯(300)。芯(300)包括通道(600),该通道包括隔离壁(620),该隔离壁将第一入口部分(606)与第二入口部分(608)隔开以限定分流式管程入口(610),该分流式管程入口流体耦接到至少一个第一管程(612)、至少一个第二管程(614)和至少一个转弯(616)。至少一个第一管程(612)在第一方向(630)上从分流式管程入口(610)输送冷却流体流。至少一个第二管程(614)在与第一方向(630)相反的第二方向(632)上输送冷却流体流。至少一个转弯(616)将冷却流体的流动方向从第一方向(630)改变为第二方向(632)。至少一个第一管程(612)、至少一个第二管程(614)和至少一个转弯(616)被布置成使得通道(600)限定蛇形通道(600)。(The invention provides a system and a method for cooling an endwall in a rotary machine. A core (300) for cooling a component (207) used in a rotary machine (100) is provided. The core (300) includes a channel (600) including a dividing wall (620) separating a first inlet portion (606) from a second inlet portion (608) to define a split pass inlet (610) fluidly coupled to at least one first pass (612), at least one second pass (614), and at least one turn (616). At least one first pass (612) delivers a flow of cooling fluid from the split pass inlet (610) in a first direction (630). At least one second pass (614) conveys a flow of cooling fluid in a second direction (632) opposite the first direction (630). At least one turn (616) changes a flow direction of the cooling fluid from a first direction (630) to a second direction (632). 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 channel (600) defines a serpentine channel (600).)

1. A core (300) for cooling a component (207) used in a rotary machine (100), the core (300) comprising:

a channel (600) comprising:

a first inlet portion (606);

a second inlet portion (608);

a dividing wall (620) separating the first inlet portion (606) from the second inlet portion (608) such that the first inlet portion (606), the second inlet portion (608), and the dividing wall (620) define a split tube-side inlet (610);

at least one first pass (612) for conveying a flow of cooling fluid from the split pass inlet (610) in a first direction (630);

at least one second pass (614) for conveying the cooling fluid flow in a second direction (632) substantially opposite the first direction (630); and

at least one turn (616) for changing the flow direction of the cooling fluid 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 channel (600) defines a serpentine channel (600).

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

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

4. The core (300) of claim 1, wherein the channel (600) further comprises a plurality of core banding strips (646) for conveying a portion of the flow of cooling fluid from an upstream portion of the channel (600) to a downstream portion of the channel (600).

5. The core (300) of claim 4, wherein the plurality of core twist ties (646) comprises at least one first core twist tie (648) for transporting a portion of the flow of cooling fluid from the first inlet portion (606) to the second inlet portion (608).

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

7. A gas turbine system (100), comprising:

a turbine portion (108) coupled in fluid communication with a combustion system (106), wherein the turbine portion (108) comprises:

an inner endwall (209) circumscribing a longitudinal axis (126) of the gas turbine system (100);

an outer endwall (207) circumscribing the inner endwall (209) and a longitudinal axis (126) of the gas turbine system (100);

a plurality of tabs (202) extending between the outer end wall (207) and the inner end wall (209); and

a core (300) positioned within at least one of the outer endwall (207) and the inner endwall (209) for cooling at least one of the outer endwall (207) and the inner endwall (209), the core (300) comprising:

a channel (600) comprising:

a first inlet portion (606);

a second inlet portion (608);

a dividing wall (620) separating the first inlet portion (606) from the second inlet portion (608) such that the first inlet portion (606), the second inlet portion (608), and the dividing wall (620) define a split tube-side inlet (610);

at least one first pass (612) for conveying a flow of cooling fluid from the split pass inlet (610) in a first direction (630);

at least one second pass (614) for conveying a flow of cooling fluid in a second direction (632) substantially opposite the first direction (630); and

at least one turn (616) for changing the flow direction of the cooling fluid 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 channel (600) defines a serpentine channel (600).

8. The gas turbine system (100) of claim 7, the passage (600) including a first inlet (602) for delivering the cooling fluid flow into the first inlet portion (606) and a second inlet (604) for delivering the cooling fluid flow into the second inlet portion (608).

9. The gas turbine system (100) of claim 7, wherein adjacent vanes (202) of the plurality of vanes (202) define a throat (306) therebetween, and wherein the passage (600) further includes an upstream portion and a downstream portion, and wherein the upstream portion is positioned upstream of the throat (306) and the downstream portion is positioned downstream of the throat (306).

10. The gas turbine system (100) of claim 7, wherein the passage (600) further includes a plurality of outlets (618) extending through the outer endwall (207).

11. The gas turbine system (100) of claim 10, wherein the plurality of outlets (618) includes at least one first outlet (636) extending from the at least one first pass (612) through the outer endwall (207), and wherein a portion of the cooling fluid stream is delivered through the at least one first outlet (636) to form a protective film on the outer endwall (207).

12. The gas turbine system (100) of claim 10, wherein the plurality of outlets (618) includes at least one second outlet (638) extending from the at least one second pass (614) through the outer endwall (207), and wherein a portion of the flow of cooling fluid is delivered through the at least one second outlet (638) to form a protective film on the outer endwall (207).

13. The gas turbine system (100) of claim 10, wherein the outer endwall (207) includes a trailing edge (224) and the plurality of outlets (618) includes at least one third outlet (640) extending from the at least one second tube side (614) through the trailing edge (224), and wherein a portion of the cooling fluid flow is delivered through the at least one third outlet (640) to form a protective film on the trailing edge (224).

14. The gas turbine system (100) of claim 10, wherein the plurality of outlets (618) includes at least one fourth outlet (642) extending from the at least one turn (616) through the outer endwall (207), and wherein a portion of the cooling fluid flow is delivered through the at least one fourth outlet (642) to form a protective film on the outer endwall (207).

15. A method (700) of cooling a component (207) of a rotating machine (100), the method (700) comprising:

inserting (702) a wick (300) into a plenum within the member (207), the wick (300) comprising a channel (600) comprising an inlet portion comprising a first inlet portion (606), a second inlet portion (608), and a dividing wall (620), at least one first pass (612), at least one second pass (614), at least one turn (616), wherein the dividing wall (620) separates the first inlet portion (606) from the second inlet portion (608) such that the inlet portion is a split pass inlet (610);

delivering (704) a flow of cooling fluid into the first inlet portion (606) and the second inlet portion (608);

conveying (706) the cooling fluid from the first inlet portion (606) and the second inlet portion (608) into the at least one first pass (612), wherein the flow of cooling fluid from the first inlet portion (606) is combined with the flow of cooling fluid from the second inlet portion (608), and wherein the at least one first pass (612) conveys the flow of cooling fluid in a first direction (630);

conveying (708) the flow of cooling fluid from the at least one first pass (612) into the at least one turn (616), wherein the at least one turn (616) changes a flow direction of the cooling fluid from the first direction (630) to a second direction (632) opposite the first direction (630); and

conveying (710) the cooling fluid flow from the at least one turn (616) into 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 channel (600) defines a serpentine channel (600).

Background

The field of the present disclosure relates generally to cooling systems, and more particularly to impingement cooling for rotating machine components.

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

Some known hot gas path components are formed from endwalls that include an internal cooling system, wherein a cooling fluid, such as discharge air extracted from a compressor or steam, is forced through a core defined within the endwall. At least some known cores are formed with inlet openings that deliver cooling fluid into the core and direct the cooling fluid against the inner surface of the core, thereby enhancing cooling of the end walls. However, at least some known cores include a set of pins that deliver cooling fluid from the inlet opening directly to the at least one outlet opening, rather than delivering cooling fluid in a circuit through the end wall. Thus, the core is not as efficiently cooled as a core comprising a serpentine or circuitous channel. In addition, at least some known cores have serpentine or circuitous channels that convey cooling fluid from a single inlet through the end walls. However, in known wicks, it can be difficult to regulate the pressure drop within the channels.

Disclosure of Invention

In one aspect, a core for cooling a component used in a rotary machine is provided. The core includes a channel including a first inlet portion, a second inlet portion, a dividing wall, at least one first pass, at least one second pass, and at least one turn. A dividing wall separates the first inlet portion from the second inlet portion such that the first inlet portion, the second inlet portion, and the dividing wall define a split tube-side inlet. At least one first pass delivers a flow of cooling fluid in a first direction from the split pass inlet. At least one second tube side conveys a flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes a flow direction of the cooling fluid from a 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 channel defines a serpentine channel.

In another aspect, a gas turbine system is provided. The gas turbine system includes a turbine section having an inner endwall, an outer endwall, a plurality of vanes, and a core. The turbine section is coupled in fluid communication with the combustion system. The inner endwall circumscribes a longitudinal axis of the gas turbine system. The outer endwall circumscribes a longitudinal axis of the gas turbine system and the inner endwall. A plurality of tabs each extend between the outer end wall and the inner end wall. A core is positioned within at least one of the outer endwall and the inner endwall for cooling the at least one of the outer endwall and the inner endwall. The core includes a channel including a first inlet portion, a second inlet portion, a dividing wall, at least one first pass, at least one second pass, and at least one turn. A dividing wall separates the first inlet portion from the second inlet portion such that the first inlet portion, the second inlet portion, and the dividing wall define a split tube-side inlet. At least one first pass delivers a flow of cooling fluid in a first direction from the split pass inlet. At least one second tube side conveys a flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes a flow direction of the cooling fluid from a 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 channel defines a serpentine channel.

In another aspect, a method of cooling a component of a rotary machine is provided. The method includes inserting a core into a plenum within the member. The core includes a passageway including an inlet portion, at least one first pass, at least one second pass, at least one turn. The inlet portion includes a first inlet portion, a second inlet portion, and a partition wall. The dividing wall separates the first inlet portion from the second inlet portion such that the inlet portion is a split tube-side inlet. The method also includes delivering a flow of cooling fluid into the first inlet portion and the second inlet portion. The method also includes delivering a flow of cooling fluid from the first inlet portion and the second inlet portion into at least one first tube side. The cooling fluid flow from the first inlet portion is combined with the cooling fluid flow from the second inlet portion, and the at least one first tube side conveys the cooling fluid flow in a first direction. The method also includes delivering a flow of cooling fluid from the at least one first pass into the at least one turn. The at least one turn changes a flow direction of the cooling fluid from a first direction to a second direction opposite the first direction. The method also includes conveying 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 channel defines a serpentine channel.

Drawings

These and other features, aspects, and advantages of the present disclosure 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:

FIG. 1 is a schematic illustration of an exemplary rotary machine;

FIG. 2 is an enlarged schematic illustration of an exemplary turbine stage of the rotary machine shown in FIG. 1;

FIG. 3 is a perspective view of exemplary stationary vanes, an outer endwall, and an inner endwall that may be used with the turbine shown in FIG. 2;

FIG. 4 is a perspective top view of the securing flap, outer and inner end walls, and an exemplary core extending through the transparent outer and inner end walls shown in FIG. 2;

FIG. 5 is a radial top cross-sectional view of the outer end wall shown in FIG. 4;

FIG. 6 is a radial top view of the exemplary core shown in FIGS. 3-5; and is

Fig. 7 is a flow chart of an exemplary method of cooling an endwall, such as the endwalls shown in fig. 2-6.

Unless otherwise indicated, the drawings provided herein are intended to illustrate features of embodiments of the present disclosure. These features are believed to be applicable to a variety of systems that include one or more embodiments of the present disclosure. Accordingly, the drawings are not intended to include all of the conventional features known to those of ordinary skill in the art to be required to practice the embodiments disclosed herein.

Detailed Description

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

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

Unless otherwise indicated, approximating language, such as "substantially," "substantially," and "about," as used herein, indicates that the terms so modified may apply to only a similar degree, as one of ordinary skill in the art would recognize, and not to an absolute or perfect degree. Accordingly, a value modified by a term or terms (such as "about", "about" and "substantially") is not to be limited to the precise value specified. In at least some cases, the approximating language may correspond to the precision of an instrument for measuring the value. Here and throughout the specification and claims, range limitations may be identified. Unless context or language indicates otherwise, these ranges may be combined and/or interchanged, and include all the sub-ranges contained therein. In addition, the terms "first," "second," and the like, unless otherwise indicated, are used herein as labels only and are not intended to impose order, positional, or hierarchical requirements on the items to which the terms refer. Further, for example, reference to "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.

As used herein, the terms "axial" and "axially" refer to directions and orientations that extend substantially parallel to a longitudinal axis of a rotating machine. Furthermore, the terms "radial" and "radially" refer to directions and orientations that extend substantially perpendicular to a longitudinal axis of the rotary machine. Further, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations that extend arcuately about a longitudinal axis of a rotating machine. Further, as used herein, the term "upstream" refers to a forward or inlet end of the rotary machine, and the term "downstream" refers to a rearward or discharge end of the rotary machine. When discussing fluid flow through a component, the direction from which the fluid flows is described as "upstream" and the direction over which the fluid flows is described as "downstream".

The systems described herein relate to serpentine cores for cooling portions of a hot gas path in 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 cooling the outer endwall. The core includes a serpentine channel including an inlet portion, a first pass, a second pass, and a turn. The inlet portion includes a partition wall, a first inlet portion and a second inlet portion. A dividing wall separates the first inlet portion from the second inlet portion such that a split tube-side inlet is defined. The first pass, the second pass, and the turn include a plurality of outlets that deliver cooling fluid from the core into the hot gas path to form a cooling film on the outer endwall. The plurality of core wraps convey cooling fluid from the upstream portion of the core to the downstream portion of the core such that the downstream portion can be replenished with lower temperature cooling fluid.

In an exemplary embodiment, a cooling fluid is delivered through the first pass, the second pass, and the turn to facilitate cooling of the outer end wall from within the core. The first pass, the second pass, and the serpentine configuration of the turns enable the cooling fluid to cool a larger area of the outer endwall, thereby enhancing overall heat transfer between the cooling fluid and the outer endwall. In addition, the serpentine configuration enables the cooling fluid to circulate at a lower pressure that is substantially equal to the pressure of the combustion gases at the nozzle throat. Further, the width of each of the first pass, the second pass, and the turn is selected to facilitate modifying or tuning the pressure drop of the cooling fluid through the first pass, the second pass, and the turn, and to enhance the overall heat transfer between the cooling fluid and the outer endwall. Further, the outlet delivers a cooling fluid into the hot gas path to facilitate forming a cooling film on the stator endwall. In addition, the core wrap replenishes the downstream portion of the core with cooling fluid, as well as providing inspection access, rigidity during core formation, and leachability for ceramic core removal after the casing process.

FIG. 1 is a schematic illustration of an exemplary rotary machine 100 (i.e., a turbomachine), and more specifically, a turbine engine. In the exemplary embodiment, rotary machine 100 is a gas turbine engine. Alternatively, the rotary machine may be any other turbine engine and/or rotary machine, including, but not limited to, steam turbine engines, gas turbine fan aircraft engines, other aircraft engines, wind turbines, compressors, and pumps. In the exemplary embodiment, gas turbine engine 100 includes an intake portion 102, a compressor portion 104 coupled downstream from intake portion 102, a combustor portion 106 coupled downstream from compressor portion 104, a turbine portion 108 coupled downstream from combustor portion 106, and an exhaust portion 110 coupled downstream from turbine portion 108. Turbine portion 108 is coupled to compressor portion 104 via a rotor shaft 112.

It should be noted that, as used herein, the term "coupled" is not limited to direct mechanical, thermal, electrical, and/or fluid communicative connection between components, but may also include indirect mechanical, thermal, electrical, and/or fluid communicative connection between components. In the exemplary embodiment, combustor portion 106 includes a plurality of combustors 114. Combustor section 106 is coupled to compressor section 104 such that each combustor 114 is in fluid communication with compressor section 104. Rotor shaft 112 is also coupled to a load 116, such as, but not limited to, an electrical generator and/or a mechanical drive application. In the exemplary embodiment, each of compressor portion 104 and turbine portion 108 includes at least one rotor assembly 118 coupled to rotor shaft 112.

During operation, the intake portion 102 delivers air 120 toward the compressor portion 104. Compressor section 104 compresses inlet air 120 to a higher pressure and then discharges compressed air 122 toward combustor section 106. Compressed air 122 is delivered to combustor section 106 where it is mixed with fuel (not shown) and combusted to produce high temperature combustion gases 124. Combustion gases 124 are channeled downstream towards turbine section 108 and impinge upon turbine blades (not shown), converting thermal energy into mechanical rotational energy that is utilized to drive rotor assembly 118 to rotate about a longitudinal axis 126. In general, combustor section 106 and turbine section 108 are referred to as the hot gas section of turbine engine 100. If the rotary machine 100 is a gas turbine that is part of a combined cycle power plant, the exhaust gas 128 is then discharged through the exhaust section 110 to the ambient atmosphere or to a steam turbine (not shown).

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

In the exemplary embodiment, each stationary vane 202 extends radially inward in a radial direction 218 from a first end 216 coupled to outer endwall 207 of casing 208 of turbine portion 108 to a second end 214 coupled to inner endwall 209 (outer endwall 208 and inner endwall 209 are shown in fig. 3). In addition, each stationary vane 202 extends axially downstream from a leading edge 222 to an opposite trailing edge 224. During operation, the outer and inner end walls 207, 209 define the radial boundaries of the hot gas flow path 232 such that a flow of high temperature combustion gases 124 is conveyed therethrough, thereby exposing the surfaces of the outer and inner end walls 207, 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 the outer and inner end walls 207, 209 to facilitate internal impingement cooling of the interior surfaces of the outer and inner end walls 207, 209.

The plenum 236 is in fluid communication with the coolant supply channel 233 via a plenum inlet 234 defined on the outer and inner end walls 207, 209. In the exemplary embodiment, coolant supply channel 233 conveys a cooling fluid 240, such as a flow of pressurized discharge air from compressor section 104 (shown in fig. 1), toward plenum inlet 234. Alternatively, the cooling fluid 240 may be any suitable fluid other than air. As used herein, the term "fluid" includes any flowing medium or material, including but not limited to air or steam. In the exemplary embodiment, stage 200 is a first stage of turbine section 108, and stationary vanes 202, outer endwall 207, and inner endwall 209 define a first stage turbine nozzle immediately downstream from combustor section 106 (shown in FIG. 1). In alternative embodiments, stage 200 is any other stage of turbine section 108. In the exemplary embodiment, plenum chamber 236 extends axially rearward into outer end wall 207 and inner end wall 209.

Fig. 3 is a perspective view of securing flap 202, outer end wall 207, and inner end wall 209, and illustrates an exemplary core 300 extending through transparent outer end wall 207 and inner end wall 209. Fig. 4 is a perspective top view of securing flap 202, outer end wall 207, and inner end wall 209. Fig. 5 is a radial top cross-sectional view of an exemplary outer end wall 207. Fig. 6 is a radial top view of an exemplary core 300. As shown in fig. 3-5, the core 300 is defined in a plenum 236 in the outer end wall 207 and the inner end wall 209 for cooling the outer end wall 207 and the inner end wall 209. More specifically, the core 300 is disposed within the outer and inner endwalls 207, 209 to facilitate cooling of the outer and inner endwalls 207, 209 with the cooling fluid 240.

As shown in fig. 3-5, stationary vanes 202 each include a suction sidewall 302 and a pressure sidewall 304 (shown in fig. 5). Adjacent stationary vanes 202, outer end wall 207, and inner end wall 209 define a throat 306 (shown in fig. 5) where the velocity of combustion gases 124 is maximized. Outer end wall 207 includes an upstream portion 308 located upstream of stationary vane 202 and a downstream portion 310 located downstream of stationary vane 202. Outer endwall 207 also includes a trailing edge 312 adjacent rotor airfoil 204. In the illustrated embodiment, the wick 300 is defined within the outer end wall 207 downstream of the suction sidewall 302. However, the core 300 may be positioned within the outer end wall 207 such that an upstream portion 314 (shown in FIG. 5) of the core 300 is upstream of the throat 306 and a downstream portion 316 of the core 300 is downstream of the throat 306. Further, the core 300 may be positioned within the outer endwall 207 such that the core 300 facilitates cooling of the outer endwall 207 and the trailing edge 312.

As shown in fig. 6, the core 300 includes at least one channel 600. In the exemplary embodiment of fig. 6, the channel 600 is a serpentine channel that conveys the cooling fluid 240 adjacent to the outer and inner end walls 207, 209 to facilitate cooling of the outer and inner end walls 207, 209. As shown in fig. 3 and 4, a similar serpentine channel 600 may be used to convey the cooling fluid 240 adjacent the inner end wall 209 to facilitate cooling of the inner end wall 209. As used herein, a "serpentine channel" is a conduit having at least one turn such that the channel is coiled or twisted. That is, the serpentine channel does not have only a substantially straight path from the inlet to the outlet. Instead, the path from the inlet to the outlet forms at least one turn such that the serpentine channel does not have a straight line-of-sight path defined from the inlet to the outlet. In an exemplary embodiment, the serpentine channel 600 includes at least one inlet 602 and 604, a first inlet portion 606, and a second inlet portion 608 forming a split tube pass inlet region 610; a first pass 612; a second pass 614; at least one turn 616 disposed between the first pass 612 and the second pass 614; and at least one outlet 618. The first pass 612, the second pass 614, and the turn 616 are oriented such that the channel 600 is a serpentine channel. In the illustrated embodiment, the serpentine channel 600 includes a plurality of inlets 602 and 604.

The inlets 602 and 604 receive the cooling fluid 240 from the coolant supply channel 233 (fig. 2) and deliver the cooling fluid 240 to a first inlet portion 606 and a second inlet portion 608. Specifically, at least one first inlet 602 delivers cooling fluid 240 to a first inlet portion 606 and at least one second inlet 604 delivers cooling fluid 240 to a 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 channel 600 can include more than two inlet portions 606 and 608. For example, the first inlet 602 may include from two to twenty first inlets 602 that deliver the cooling fluid 240 to the first inlet portion 606, and the second inlet 604 may include from two to twenty second inlets 604 that deliver the cooling fluid 240 to the second inlet portion 608. More specifically, first inlet 602 may include eight to ten first inlets 602 that deliver cooling fluid 240 to first inlet portion 606, and second inlet 604 may include eight to ten second inlets 604 that deliver cooling fluid 240 to second inlet portion 608.

A dividing wall 620 separates the first inlet portion 606 from the second inlet portion 608 to form a split tube pass inlet region 610. The dividing wall 620 reduces the width 622 of the split pass inlet region 610 such that the velocity of the cooling fluid 240 passing through the split pass inlet region 610 is increased. More specifically, as the width 622 of the split pass inlet region 610 increases downstream from the inlets 602 and 604, the velocity of the cooling fluid 240 through the split pass inlet region 610 without the dividing wall 620 will decrease. The dividing wall 620 decreases in width 622 such that the velocity of the cooling fluid 240 remains constant or increases as the cooling fluid 240 is conveyed through the split tube pass inlet region 610.

Additionally, the first inlet portion 606 defines a first width 624 and the second inlet portion 608 defines a second width 626. The first width 624 may be the same as or different than the second width 626, and the first width 624 and the second width 626 may be selectively sized to enable a particular volume of cooling fluid 240 to be conveyed through the channel 600. More specifically, the first width 624 and the second width 626 may be sized to accommodate a particular volumetric flow rate of the cooling fluid 240 such that the heat transfer coefficient of the cooling fluid 240 is tuned to a particular heat transfer requirement of the outer endwall 207 and/or the inner endwall 209.

The first inlet portion 606 and the second inlet portion 608 merge into a first pass 612, and each inlet portion delivers the cooling fluid 240 into the first pass 612. First pass 612 extends through outer endwall 207 substantially parallel to trailing edge 312 and second pass 614. The first pass 612 defines a third width 628 that, along with the first and second widths 624, 626, can be selectively sized to enable a particular volumetric flow rate of the cooling fluid 240 therethrough such that the heat transfer coefficient of the cooling fluid 240 is tuned to the particular heat transfer requirements of the outer and/or inner end walls 207, 209. The first pass 612 receives the cooling fluid 240 from the first inlet portion 606 and the second inlet portion 608 and delivers the cooling fluid 240 to a turn 616.

The turn 616 receives the cooling fluid 240 from the first pass 612 and delivers 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 conveys the cooling fluid 240 in a first direction 630 and the second pass 614 conveys the cooling fluid 240 in a second direction 632 opposite the first direction 630. The turn 616 changes the flow direction of the cooling fluid 240 from the first direction 630 to the second direction 632. In the exemplary embodiment, turn 616 is a 180 ° turn such that first direction 630 is diametrically opposed to 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. The turn 616 receives the cooling fluid 240 from the first pass 612, changes the flow direction of the cooling fluid 240, and delivers the cooling fluid 240 to the second pass 614.

Second pass 614 extends through outer endwall 207 substantially parallel to trailing edge 312 and first pass 612. The second tube side 614 defines a fourth width 634 that, along with the dimensions of the first width 624, the second width 626, and the third width 628, may be selectively set to achieve a particular volumetric flow rate of the cooling fluid 240 such that the heat transfer coefficient of the cooling fluid 240 is tuned to the particular heat transfer requirements of the outer end wall 207 and/or the inner end wall 209. The second pass 614 receives the cooling fluid 240 from the turn 616 and delivers the cooling fluid 240 to an outlet 618.

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, the core 300 may include three passes and two turns. In another alternative embodiment, the core 300 may include four passes and three turns.

The core 300 includes at least one outlet 618 downstream of the throat 306. While the core 300 may include only a single outlet 618, in exemplary embodiments, the core 300 includes a plurality of outlets 618 that convey the cooling fluid from the core 300 into the hot gas flow path 232. For example, the core 300 may include at least one first outlet 636 that extends from the first pass 612, through the outer endwall 207, and into the hot gas flow path 232. In the exemplary embodiment, core 300 includes a plurality of first outlets 636, each of which extends from first pass 612, through outer endwall 207, and into hot gas flow path 232. The cooling fluid 240 discharged from the first outlet 636 into the hot gas flow path 232 may form a cooling film (not shown) on the outer endwall 207 that protects the outer endwall 207.

The core 300 may also include at least one second outlet 638 extending from the second pass 614 through the outer endwall 207 and into the hot gas flow path 232. In the exemplary embodiment, core 300 includes a plurality of second outlets 638, each of which extends from second pass 614 through outer endwall 207 and into hot gas flow path 232. The cooling fluid 240 discharged from the second outlet 638 into the hot gas flow path 232 may form a cooling film (not shown) on the outer endwall 207 that facilitates protecting the outer endwall 207.

The core 300 may also include at least one third outlet 640 (shown in fig. 4) extending from the second tube side 614 through the trailing edge 312 of the inner endwall 209 and into the hot gas flow path 232. In the exemplary embodiment, core 300 includes a plurality of third outlets 640, each of which extends from second tube side 614 through trailing edge 312 of outer endwall 207 and into hot gas flow path 232. The cooling fluid 240 discharged from the third outlet 640 into the hot gas flow path 232 may form a cooling film (not shown) on the trailing edge 312 of the outer endwall 207 that protects the trailing edge 312 of the outer endwall 207.

The core 300 may also include at least one fourth outlet 642 extending from the turn 616 through the outer end wall 207 and into the hot gas flow path 232. In the exemplary embodiment, core 300 includes a plurality of fourth outlets 642, each of which extends from turn 616 through trailing edge 312 of outer endwall 207 and into hot gas flow path 232. The cooling fluid 240 discharged from the fourth outlet 642 into the hot gas flow path 232 may form a cooling film (not shown) on the outer endwall 207 that facilitates protecting the outer endwall 207. The cartridge 300 may include the outlet 218 at any location that enables the cartridge 300 to operate as described herein.

The size, shape, and relative position of the first, second, third, and fourth outlets 636, 638, 640, 642 may be sized and arranged to facilitate tuning 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 endwall 207, and the second outlet 638 supplements the cooling film with additional cooling fluid 240. In addition, more outlets 636, 638, 640, and 642 facilitate reducing a volumetric flow rate of the cooling fluid 240 through the channel 600 and facilitate reducing a pressure drop of the cooling fluid 240 through the channel 600. Accordingly, the size, shape, and location of the first, second, third, and fourth outlets 636, 638, 640, 642 may be sized and arranged to facilitate tuning the pressure drop, volumetric flow rate, and/or heat transfer coefficient of the cooling fluid 240.

In the exemplary embodiment, first tube pass 612 and second tube pass 614 each include a plurality of turbulators or ridges 644 that generate turbulent flow within first tube pass 612 and second tube pass 614. Specifically, turbulators 644 generate turbulence within cooling fluid 240 to facilitate increasing a heat transfer coefficient of cooling fluid 240 within first pass 612 and second pass 614. Increasing the heat transfer coefficient enhances the overall heat transfer between the cooling fluid 240 and the outer endwall 207. In the exemplary embodiment, turbulator 644 has a height (not shown) that is about 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.

In an exemplary embodiment, the core 300 includes a plurality of hollow core twist ties 646 extending from the first inlet portion 606 to the second inlet portion 608 or from the first pass 612 to the second pass 614. In particular, the core 300 includes at least one first core twist tie 648 extending from the first inlet portion 606 to the second inlet portion 608 and at least one second core twist tie 650 extending from the first pass 612 to the second pass 614. More specifically, in the exemplary embodiment, the core 300 includes a single first core wrap 648 and a plurality of second core wraps 650. The first core wrap tape 648 and the second core wrap tape 650, which define fluid channels therein, replenish the downstream portion of the channels 600 with cooling fluid 240. As the cooling fluid 240 is conveyed through the channel 600, the temperature of the cooling fluid 240 increases, which facilitates reducing a heat transfer coefficient of the cooling fluid 240 and reducing an overall heat transfer between the cooling fluid 240 and the outer endwall 207. Core wrap 646 is a "chopped segment" that transports cooling fluid 240 from an upstream portion of channel 600 to a downstream portion of channel 600 without heat transfer between cooling fluid 240 and outer end wall 207. Thus, the temperature of the cooling fluid 240 conveyed through the core wrap 646 is lower than the temperature of the cooling fluid 240 conveyed through the first pass 612, the second pass 614, and the turn 616. Thus, core wrap 646 supplements the downstream portion of channel 600 with cooling fluid 240 having a lower temperature, which facilitates increasing the heat transfer coefficient of cooling fluid 240 and enhancing the overall heat transfer between cooling fluid 240 and outer end wall 207. Core twist tie 646 may also be used as an inspection aperture to inspect core 300.

During operation, the inlets 602 and 604 receive the cooling fluid 240 from the coolant supply channel 233 and deliver the cooling fluid 240 to the first inlet portion 606 and the second inlet portion 608. The first inlet portion 606 conveys a portion of the cooling fluid 240 through the first wicking tie 648 to supplement the second inlet portion 608. The first inlet portion 606 and the second inlet portion 608 merge into a first tube pass 612 and each deliver the cooling fluid 240 into the first tube pass 612. The first pass 612 conveys a portion of the cooling fluid 240 through a second core wrap 650 to supplement the second pass 614 and conveys another portion of the cooling fluid 240 to the turn 616. The first pass 612 also conveys a portion of the cooling fluid through a first outlet 636 into the hot gas path 232 to form a cooling film on the outer endwall 207. The turn 616 conveys a portion of the cooling fluid 240 through a fourth outlet 642 into the hot gas path 232 to form a cooling film on the outer endwall 207 and conveys the remaining cooling fluid 240 to the second pass 614. The second pass 614 conveys the cooling fluid 240 through the second outlet 638 and the third outlet 640 to replenish the cooling film and form a cooling film on the trailing edge 312. As the cooling fluid 240 is conveyed through the channel 600, it exchanges heat with the outer endwall 207. Thus, the cooling fluid 240 facilitates cooling the outer endwall 207 from within the core 300 and forms a protective cooling film that protects the outer endwall 207.

The serpentine configuration of the channel 600 enables the cooling fluid 240 to cool a larger area of the outer endwall 207, thereby enhancing overall heat transfer between the cooling fluid 240 and the outer endwall 207. Additionally, the serpentine orientation of the channels 600 enables the cooling fluid 240 to have a lower pressure that is approximately equal to the pressure of the combustion gas 124 at the throat 306. Further, widths 624, 626, 628, and 634 are sized to tune the pressure drop of cooling fluid 240 through channel 600 and facilitate enhancing the overall heat transfer between cooling fluid 240 and outer endwall 207. Further, the outlet 618 delivers the cooling fluid 240 into the hot gas path 232 to protect the outer endwall 207 by forming a cooling film. In addition, core wrap 646 supplements the downstream portion of channel 600 with cooling fluid 240. Thus, the arrangement of the core 300 enhances the overall heat transfer between the cooling fluid 240 and the outer endwall 207.

Although fig. 3-6 describe the core 300 and its features in connection with 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.

FIG. 7 is a flow diagram of an exemplary method 700 of cooling components of a rotating machine. In an exemplary embodiment, the method 700 includes inserting 702 a core into a plenum within a member. The core includes a channel including an inlet portion, at least one first pass, at least one second pass, at least one turn between the respective first and second passes. The inlet section includes a dividing wall separating the first inlet section from the second inlet section such that the inlet section is a split tube-side inlet. The method 700 further includes delivering 704 a flow of cooling fluid into the first inlet portion and the second inlet portion. The method 700 further includes delivering 706 a flow of cooling fluid from the first inlet portion and the second inlet portion into at least one first tube pass. The cooling fluid flow from the first inlet portion is combined with the cooling fluid flow from the second inlet portion, and the at least one first tube side conveys the cooling fluid flow in a first direction. The method 700 further includes conveying 708 the flow of cooling fluid from the at least one first pass into the at least one turn. The at least one turn changes a flow direction of the cooling fluid from a first direction to a second direction opposite the first direction. The method 700 further includes conveying 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 channel is a serpentine channel.

The above-described systems relate to serpentine cores for cooling portions of a hot gas path in 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 cooling the outer endwall. The core includes a serpentine channel including an inlet portion, a first pass, a second pass, and a turn between the first pass and the second pass. The inlet section includes a dividing wall separating the first inlet section from the second inlet section such that a split tube-side inlet is defined. The first pass, the second pass, and the turn include a plurality of outlets, each of which conveys a cooling fluid from the core into the hot gas path to form a cooling film on the outer endwall. A plurality of hollow core ties convey cooling fluid from an upstream portion of the core to a downstream portion of the core such that the downstream portion can be replenished with lower temperature cooling fluid.

In an exemplary embodiment, a cooling fluid is delivered through the first pass, the second pass, and the turn to facilitate convective cooling of the outer end wall from within the core. The first pass, the second pass, and the serpentine configuration of the turns enable the cooling fluid to convectively cool a larger area of the outer endwall, thereby enhancing overall heat transfer between the cooling fluid and the outer endwall. In addition, the serpentine configuration enables the cooling fluid to circulate at a lower pressure that is substantially equal to the pressure of the combustion gases at the nozzle throat. Further, the width of each of the first pass, the second pass, and the turn is selected to facilitate modifying or tuning the pressure drop of the cooling fluid through the first pass, the second pass, and the turn, and to enhance the overall heat transfer between the cooling fluid and the outer endwall. Further, the outlet delivers a cooling fluid into the hot gas path to facilitate forming a cooling film on the stator endwall. In addition, the core wrap supplements the downstream portion of the core with cooling fluid. Thus, the core achieves both convective cooling of the endwall and film cooling of the endwall.

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

Exemplary embodiments of systems and methods for cooling portions of a hot gas path of a rotary machine are described above in detail. The systems and methods are not limited to the specific embodiments described herein, but rather, components of systems and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein. For example, the method may also be used in combination with other turbine components and is not limited to practice with only portions of the hot gas path of a rotary machine as described herein. Rather, the exemplary embodiment can be implemented and utilized in connection with many other rotary machine applications.

Although specific features of various embodiments of the disclosure may be shown in some drawings and not in others, this is for convenience only. 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.

This written description uses examples to disclose embodiments of the disclosure, including the best mode, and also to enable any person skilled in the art to practice embodiments of the disclosure, including making and using any devices or systems 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 with insubstantial differences from the literal languages of the claims.