Gas turbine component with a drain circuit for removing debris from a cooling air supply

Abstract

The invention is entitled "Gas turbine component with drain circuit for removing debris from cooling air supply." A gas turbine (10) component includes a drain circuit (130) for removing debris (142) from cooling air (120) flowing through the gas turbine (10) component. The gas turbine (10) component includes: an impingement insert (100) and a debris drain circuit (130). The impingement insert (100) disposed within a cavity (102) in the component includes an end wall (144) and distribution holes (114) for directing cooling air (120) against the walls (134, 144) of the cavity (102). The debris drain circuit (130) includes: a bypass orifice (132, 232) defined in the end wall, the bypass orifice fluidly coupling an interior of the impingement insert (100) and an end section of the cavity (102); and a drain passage (138, 238) fluidly coupling the end section of the cavity (102) to an inter-turbine cavity (140) or hot gas path (64). A pressure differential between the interior of the impingement insert (100) and the inter-turbine cavity (140) or hot gas path (64) directs debris (142) in the cooling air (120) through the bypass orifice (132, 232) and the drain passage (138, 238).

Description

Background Technology

[0001] This disclosure relates generally to gas turbine systems, and more particularly to a discharge circuit for removing debris from a supply of cooling air flowing through components of a gas turbine system (e.g., a first-stage nozzle).

[0002] Gas turbine systems are an example of turbines widely used in fields such as power generation. A typical gas turbine system usually consists of a compressor section, a combustor section, and a turbine section. During operation, various components of a gas turbine system, such as nozzle blades, turbine blades, and shroud sections, are subjected to high-temperature gas flow, which can lead to component failure. Since higher-temperature gas flow generally results in increased performance, efficiency, and power output of the gas turbine system, it is advantageous to cool the components subjected to the high-temperature gas flow to allow the gas turbine system to operate at elevated temperatures and to extend the lifespan of the gas turbine system components.

[0003] Cooling (e.g., impingement cooling, convection cooling, etc.) is typically provided by directing a flow of pressurized cooling fluid (e.g., air) through internal passages formed in components of a gas turbine system. In many cases, cooling fluid is provided by venting a portion of the pressurized air discharged from the compressor section of the gas turbine system. Typically, cavities within components of the gas turbine system (e.g., nozzle blades) are fitted with thin-walled containers (often referred to as inserts (e.g., impingement inserts)) configured to distribute cooling air against the walls of the cavity to provide impingement cooling. Such inserts typically include a plurality of small distribution holes dispersed around the walls of the insert.

[0004] During operation of a gas turbine system, small particles contained in the cooling air entering the insert may accumulate in the small distribution holes in the insert's walls and potentially become blocked. Such blockage reduces the insert's cooling efficiency and can lead to oxidation or damage to parts of the insert. Summary of the Invention

[0005] One aspect of this disclosure relates to a gas turbine component having a discharge circuit for removing debris from cooling air flowing through the gas turbine component, the gas turbine component comprising: an impact insert disposed within a cavity in the gas turbine component, the impact insert including an end wall and a plurality of distribution holes for guiding cooling air against the wall of the cavity; and a debris discharge circuit including: a bypass orifice defined in the end wall of the impact insert, the bypass orifice fluidly coupled to the interior of the impact insert and an end section of the cavity; and a discharge passage defined in a rear section of the gas turbine component, the discharge passage fluidly coupled to the end section of the cavity and an inter-wheel cavity located radially inward of the gas turbine component; wherein a pressure difference between the interior of the gas turbine component and the inter-wheel cavity guides debris in the cooling air through the bypass orifice and the discharge passage to the inter-wheel cavity.

[0006] Another aspect of this disclosure relates to a gas turbine component having a discharge circuit for removing debris from cooling air flowing through components of a gas turbine system. The gas turbine component includes: an impact insert disposed within a cavity in the gas turbine component, the impact insert including an end wall and a plurality of distribution holes for guiding cooling air against the wall of the cavity; and a debris discharge circuit including: a bypass orifice defined in the end wall of the impact insert, the bypass orifice fluidly coupling the interior of the impact insert and an end section of the cavity; and a discharge passage defined in a rear section of the gas turbine component, the discharge passage fluidly coupling the impact insert and a hot gas path located outside the gas turbine component via the bypass orifice; wherein a pressure difference between the interior of the impact insert and the exterior of the gas turbine component guides debris in the cooling air through the bypass orifice and the discharge passage to the hot gas path located outside the gas turbine component.

[0007] The exemplary aspects of this disclosure address the problems described herein and / or other problems not discussed herein. Attached Figure Description

[0008] These and other features of the present disclosure will be more readily understood from the following detailed description of various aspects of the present disclosure in conjunction with the accompanying drawings depicting various embodiments thereof, wherein:

[0009] Figure 1 A schematic diagram of a gas turbine system according to the embodiment described herein is shown;

[0010] Figure 2 A side view of a turbine section of a gas turbine system according to an embodiment described herein, including a portion of a debris discharge circuit, is shown.

[0011] Figure 3 A perspective view of an impact insert according to an embodiment described herein is shown;

[0012] Figure 4 An enlarged view schematically illustrating a debris discharge circuit and its operation according to the embodiment described herein; and

[0013] Figure 5 An enlarged view of the debris discharge circuit and its operation according to the additional embodiment described herein is shown schematically.

[0014] It should be noted that the accompanying drawings of this disclosure are not necessarily drawn to scale. The drawings are intended to depict only typical aspects of this disclosure and should therefore not be considered as limiting the scope of this disclosure. In the drawings, similar numbers denote similar elements between figures. Detailed Implementation

[0015] Reference will now be made in detail to the representative embodiments illustrated in the accompanying drawings. It should be understood that the following description is not intended to limit the embodiments to a single preferred embodiment. Rather, this disclosure is intended to cover alternatives, modifications, and equivalents that may be included within the substance and scope of the embodiments defined by the appended claims.

[0016] First, in order to clearly describe the present disclosure, it will be necessary to select certain terms when referring to and describing relevant machine parts within the scope of this disclosure. Where possible, common industry terms will be used and adopted in a manner consistent with the accepted meaning of the terms. Unless otherwise stated, such terms should be given a broad interpretation consistent with the context of this application and the scope of the appended claims. Those skilled in the art will understand that several different or overlapping terms may generally be used to refer to a particular part. An object that can be described herein as a single part may include multiple parts and is referred to in another context as being composed of multiple parts. Alternatively, an object that can be described herein as comprising multiple parts may elsewhere be referred to as a single part.

[0017] In addition, several descriptive terms may be used periodically throughout this document, and it should prove helpful to define these terms at the beginning of this section. Unless otherwise stated, these terms and their definitions are as follows. As used herein, “downstream” and “upstream” are terms indicating the direction of fluid flow, such as through the working fluid of a turbine engine, or, for example, through the airflow of a combustor or through the coolant of one of the turbine's component systems. The term “downstream” corresponds to the direction of fluid flow, and the term “upstream” refers to the direction opposite to the flow. Without any other particularity, the terms “front” and “rear” refer to directions, where “front” refers to the front end of the engine or compressor end, and “rear” refers to the rear end of the engine or turbine end. Additionally, the terms “ahead” and “rear” may be used and / or understood to be descriptively similar to the terms “front” and “rear.”

[0018] Typically, it is necessary to describe parts in different radial, axial, and / or circumferential positions. The "A" axis indicates axial orientation. As used herein, the terms "axial" and / or "axially" refer to the relative position / direction of an object along axis A, which is substantially parallel to the axis of rotation of the gas turbine system (particularly the rotor section). As further used herein, the terms "radial" and / or "radially" refer to the position of an object along direction "R" (see [reference]). Figure 1 and Figure 2 The relative position / direction of axis A, which is substantially perpendicular to axis A and intersects axis A at only one location. Finally, the term "circumferential" refers to movement or position about axis A (e.g., direction "C").

[0019] In various embodiments, components described as “fluidly coupled” or “fluidly connected” to each other may be joined along one or more interfaces. In some embodiments, these interfaces may include joints between different components, and in others, these interfaces may include firmly and / or integrally formed interconnections. That is, in some cases, components that are “coupled” to each other may be formed simultaneously to define a single continuous member. However, in other embodiments, these coupled components may be formed as separate members and subsequently joined by known processes (e.g., fastening, ultrasonic welding, bonding).

[0020] When an element or layer is referred to as “located on another element,” “joined to another element,” “connected to another element,” or “coupled to another element,” it may be directly located on, joined to, connected to, or coupled to another element, or an intermediary element may be present. In contrast, when an element is referred to as “directly located on another element,” “directly joined to another element,” “directly connected to another element,” or “directly coupled to another element,” an intermediary element or layer may not be present. Other terms used to describe the relationship between elements should be interpreted in a similar manner (e.g., “between” vs. “directly between,” “adjacent” vs. “directly adjacent,” etc.). As used herein, the term “and / or” includes any and all combinations of one or more of the associated listed items.

[0021] Figure 1 A schematic diagram of a gas turbine system 10 according to various embodiments is shown. As shown, the gas turbine system 10 includes a compressor section 12 for compressing an incoming airflow 14 and for delivering a pressurized compressed airflow 16 to a combustor section 18. The combustor section 18 mixes the compressed airflow 16 with a pressurized fuel supply 20 and ignites the mixture to form a combustion gas flow 22. Although only a single combustor section 18 is shown, the gas turbine system 10 may include any number of combustor sections 18. The combustion gas flow 22 is then delivered to a turbine section 24. The combustion gas flow 22 drives the turbine section 24 to generate mechanical work. The mechanical work generated in the turbine section 24 drives the compressor section 12 via a shaft 26 and can be used to drive an external load 28 (such as a generator).

[0022] Figure 2 A gas turbine system (e.g., is shown) is illustrated. Figure 1 A side view of a portion of the turbine section 24 of a gas turbine system 10, including at least one turbine stage 30. The turbine stage 30 includes a set of turbine blades 32 (one blade 32 shown) positioned within a housing 38 of the turbine section 24 and a corresponding set of nozzles 36 (one nozzle 36 shown). For example, as... Figure 2 As shown, stage 30 of turbine blade 32 can be the first stage 30 of turbine blade 32 and nozzle 36 in turbine section 24. In operation, a set of 34 first-stage nozzles 36 is configured to direct combustion gas flow 22 onto the turbine blade 32 of the first turbine stage 30. Each nozzle 36 in the first set of 34 nozzles 36 may include an inner chord hinge seal 60 configured to form a seal between the nozzle 36 and an inner support ring (not shown) to seal the region 62 formed by compressor section 12 ( Figure 1 The high-pressure compressed air generated is separated from the low-pressure hot combustion gas 22 in the turbine blades 32 of the first stage 30 that flows into the turbine section 24 along the hot gas path 64.

[0023] The turbine blades 32 of a particular stage (e.g., the first stage 30) may include a plurality of turbine blades 32 coupled to and circumferentially positioned around the rotor 26, and defined by the combustor section 18 of the gas turbine system. Figure 1 The combustion gases 22 produced by the turbine section 24 drive the turbine. A group of nozzles 36 in the first stage 30 includes multiple fixed nozzles 36 coupled to and circumferentially positioned around the housing 38 of the turbine section 24. Figure 2 In the illustrated embodiment, each nozzle 36 may include a blade 40 positioned between the outer platform 42 and the inner platform 44. Similar to the nozzle 36, each turbine blade 32 of the turbine section 24 may include a vane 46 extending radially from the rotor 26. Each vane 46 may include a tail portion 48 and a platform 50 positioned opposite the tail portion 48.

[0024] The turbine blades 32 and nozzles 36 can be axially positioned adjacent to each other within the housing 38. Figure 2 In this example, a set of 34 nozzles 36 is shown positioned axially adjacent to and upstream of a set of turbine blades 32 in a turbine stage 30. The turbine section 24 may include multiple stages 30 of turbine blades 32 and nozzles 36, which are axially positioned throughout the housing 38.

[0025] The turbine section 24 of the gas turbine system 10 may include multiple stages 52 of a shroud 54 axially positioned throughout the housing 38. Figure 2 (A level is shown in the text). Figure 2 In this example, stage 52 of shroud 54 is shown radially positioned adjacent to and substantially surrounding or around the turbine blades 32 of turbine stage 30. Stage 52 of shroud 54 may also be axially positioned adjacent to and / or downstream of a set of nozzles 36. Furthermore, stage 52 of shroud 54 may be positioned between two adjacent sets of nozzles 36 on opposite sides of the turbine blades 32 of turbine stage 30. Stage 52 of shroud 54 may be coupled to the housing 38 of turbine section 24 using a set of extensions 56, each extension including an opening 58 configured to receive a corresponding section of shroud 54.

[0026] refer to Figures 2 to 4 The impact insert 100 can be positioned within a cavity 102 formed in the blade 40 of at least one of a set of nozzles 36 in the turbine section 24. For example... Figure 3As shown in detail, the impact insert 100 may include a body 104 having a leading edge wall 106, a trailing edge wall 108, and a first sidewall 110 and a second sidewall 112 extending between the leading edge wall 106 and the trailing edge wall 108 of the body 104. A plurality of dispensing holes 114 may be formed through one or more of the leading edge wall 106, the trailing edge wall 108, the first sidewall 110, and / or the second sidewall 112, and may extend from the inner surface 116 of the impact insert 100 to the outer surface 118 of the impact insert 100. This can be achieved by venting the gas turbine system 10 (… Figure 1 A portion of the compressed air 16 discharged from the compressor section 12 of the compressor section 12 is used to provide pressurized cooling air 120, which can be guided through the opening 122 to the interior 150 of the impact insert 100.

[0027] Now refer to Figures 2 to 4 Describing a debris discharge circuit 130 according to this disclosure. At least one nozzle 36 of a set of 34 nozzles 36 (e.g., nozzle 36 of the first stage 30 of turbine section 24) may include the debris discharge circuit 130. As shown, the debris discharge circuit 130 may include at least one bypass orifice 132 extending through a bottom (e.g., end) wall 134 of the discharge insert 100 for fluid coupling of the interior 150 of the discharge insert 100 and the bottom (e.g., end) section 136 of the cavity 102 located below the discharge insert 100. The debris discharge circuit 130 may also include a discharge passage 138 ( Figure 2 and Figure 4 The discharge passage extends through the inner platform 44 of the nozzle 36 and the fluid coupling chamber 102 is located in the bottom section 136 below the impact insert 100 and the inter-wheel chamber 140 of the turbine section 24.

[0028] In the gas turbine system 12 ( Figure 1 During operation, small particles (e.g., rust flakes, sand, etc. from the housing of the compressor section) contained in the cooling air 120 entering the impact insert 100 can accumulate in the small distribution holes 114 in the walls 106, 108, 110 and / or 112 of the impact insert 100 and can become blocked. Such blockage can reduce the cooling efficiency of the impact insert 100 and can lead to oxidation or other damage to portions of the impact insert 100. Advantageously, such debris is removed from the impact insert 100 by a debris discharge circuit 130 according to an embodiment of the invention.

[0029] Figure 4 An enlarged view of the debris discharge circuit 130 and its operation is shown. Figure 4In the illustrated embodiment, the debris discharge circuit 130 may be disposed in nozzle 36 of the first set of 34 nozzles 36 in the first turbine stage 30. In this embodiment, the impact insert 100 provides impact cooling to the rear end 131 of the cavity 102 via a plurality of distribution holes 114 formed in the trailing edge wall 108 of the impact insert 100. To this extent, the cooling air 120 flowing into the injection insert 100 will flow downward into the interior 150 of the impact insert 100 and toward the plurality of distribution holes 114 formed in the trailing edge wall 108 of the body 104 of the impact insert 100.

[0030] The debris discharge circuit 130 may include at least one bypass orifice 132 extending through the bottom wall 134 of the impact insert 100 (three bypass orifices 132 are shown in the illustrated embodiment). Each bypass orifice 132 is configured to fluidly couple the interior 150 of the impact insert 100 and the bottom section 136 of the cavity 102 located below the impact insert 100. According to embodiments, each bypass orifice 132 may have a diameter larger than the size (e.g., width, diameter, etc.) of any debris 142 that may be expected to enter the impact insert 100 during operation of the gas turbine system. For example, in a non-limiting example, the bypass orifice 132 may have a diameter of about 0.10 inches to about 0.15 inches (about 2.54 mm to about 3.91 mm). Although in Figures 2 to 4 Three bypass orifices 132 are shown, but fewer or more bypass orifices 132 may be used. Furthermore, all bypass orifices 132 may have the same diameter, or two or more different diameters may be used.

[0031] like Figure 4 As shown, the cooling airflow 120 can transport (e.g., convey) debris 142 into the interior 150 of the impact insert 100. (E.g., due to the velocity of the cooling airflow 120) the momentum of the debris 142 is high enough that it will not be redirected to the distribution hole 114 formed in the trailing edge wall 108 of the body 104 of the impact insert 100, but will instead travel towards the bottom wall 134 of the impact insert 100. The debris 142 may be briefly recirculated at the bottom of the impact insert 100 and then enter the bottom section 136 of the cavity 102 through the bypass port 132 in the bottom wall 134 of the impact insert 100.

[0032] like Figure 4As shown, cooling air 120 flows into the interior 150 of the impact insert 100 and into and through distribution holes 114 formed in the rear edge wall 108 of the body 104 of the impact insert 100. To this extent, as debris 142 travels toward the bottom wall 134 of the impact insert 100, the debris 142 can be deflected toward the rear edge wall 108 by the flow of cooling air 120. According to an embodiment, a bypass orifice 132 may be positioned in the bottom wall 134 toward (e.g., as close as possible to) the rear edge wall 108 of the body 104 of the impact insert 100 to increase the likelihood that debris 142 will be captured by the bypass orifice 132 and enter the bottom section 136 of the cavity 102 through it.

[0033] The debris discharge circuit 130 may also include a discharge passage 138 extending through the inner platform 44 of the nozzle 36. The discharge passage 138 fluid coupling chamber 102 is disposed in the bottom section 136 below the impact insert 100 and the inter-wheel cavity 140 of the turbine section 24. The diameter of the discharge passage 138 may be greater than or equal to the diameter of the bypass orifice 132.

[0034] According to various embodiments, the discharge channel 138 may be positioned at the rear of the bypass orifice 132 (e.g., downstream in the direction indicated by arrow A) to facilitate the discharge of debris 142 from the bottom section 136 of the cavity 102. Furthermore, the discharge channel 138 may extend at an angle toward the trailing edge 144 of the nozzle 36 through the platform 44 of the nozzle 36 to facilitate the discharge of debris 142. In other embodiments, the discharge channel 138 may extend vertically through the platform 44 of the nozzle 36. When used for the first-stage nozzle 36, the discharge channel 138 may be positioned at the rear of the inner chord hinge seal 60 to allow debris 142 to flow into the inter-wheel cavity 140 of the turbine section 24. In an alternative embodiment, Figure 4 As shown by the dashed line, the discharge channel 138' may be formed in the trailing edge wall 144 of the nozzle 36 to discharge the debris 142 directly into the hot gas path 64 instead of into the inter-wheel cavity 140.

[0035] A pressure differential exists across ejection channel 138, which draws debris 142 from the bottom section 136 of cavity 102 and into the inter-wheel cavity 140 of turbine section 24. For example, according to the embodiment described herein, the pressure in the bottom section 136 of cavity 102 caused by the flow of cooling air 120 into impact insert 100 is greater than the pressure in inter-wheel cavity 140. This pressure differential creates an airflow through discharge channel 138 that ejects debris 142 from the bottom section 136 of cavity 102 and pushes it into inter-wheel cavity 140. Debris 142 can flow from inter-wheel cavity 140 into the hot gas path 64 of turbine section 24 and eventually exit from the gas turbine system.

[0036] According to some embodiments, the pressure ratio across the discharge passage 138 may be in the range of about 1.1 to about 1.8. However, the pressure ratio may vary based on, for example, the number, layout and / or diameter of the bypass orifices 132; the layout, angle and / or diameter of the discharge passage 138; and / or other factors (e.g., the flow rate of the cooling air 120, the pressure within the inter-wheel cavity 140, etc.).

[0037] Figure 5 An enlarged view of the debris discharge circuit 230 according to an additional embodiment and its operation is shown. (As previously mentioned...) Figure 4 As described in the illustrated embodiment, debris 142: 1) enters the bottom section 136 of the cavity 102 through the bypass port 132 in the bottom wall 134 of the impact insert 100; and 2) reaches the inter-wheel cavity 140 from the bottom section 136 of the cavity 102 through the discharge channel 138. However, as Figure 5 As shown, the debris discharge circuit 230 may include a discharge channel 238 configured as a tubular structure extending from the bottom of the impact insert 100 to directly fluid couple the impact insert 100 and the inter-wheel cavity 140 (via bypass orifice 232) to remove debris 142.

[0038] The debris discharge circuit 230 may include at least one bypass orifice 232 extending through the bottom wall 134 of the impact insert 100. If multiple bypass orifices 232 are used, all bypass orifices 232 may be fluidly coupled to the same discharge passage 238. According to such embodiments, the bypass orifice 232 may have a diameter larger than the size (e.g., width, diameter, etc.) of any debris 142 that may be expected to enter the impact insert 100 during operation of the gas turbine system. For example, in a non-limiting example, the bypass orifice 232 may have a diameter of about 0.10 inches to about 0.15 inches (about 2.54 mm to about 3.91 mm). Although in Figure 5 A bypass orifice 232 is shown, but a greater number of bypass orifices 232 may be used. Furthermore, all bypass orifices 232 may have the same diameter, or two or more different diameters may be present. The diameter of the discharge channel 238 may be greater than or equal to the diameter of the bypass orifice 232.

[0039] like Figure 5 As shown, the cooling airflow 120 can transport debris 142 into the interior 150 of the impact insert 100. Similarly, the momentum of the debris 142 is high enough that it will not be redirected to the distribution hole 114 formed in the wall of the impact insert 100, but will instead travel towards the bottom wall 134 of the impact insert 100. The debris 142 can be briefly recirculated at the bottom of the impact insert 100, and then pass through the bypass orifice 232 in the bottom wall 134 of the impact insert 100 and enter the discharge channel 238.

[0040] A pressure differential exists across the discharge passage 238, configured to draw debris 142 through the discharge passage 238 and into the inter-wheel cavity 140 of the turbine section 24. For example, according to one embodiment, the pressure within the impact insert 100 due to the flow of cooling air 120 into the impact insert 100 is greater than the pressure within the inter-wheel cavity 140. This pressure differential creates an airflow through the discharge passage 238 that pushes debris 142 into the bypass orifice 232, through the discharge passage 238, and into the inter-wheel cavity 140. Debris 142 can flow from the inter-wheel cavity 140 into the hot gas path 64 of the turbine section 24 and eventually exit from the gas turbine system. In another embodiment, Figure 5 As shown by the dashed line, the discharge channel 238' may be formed in the trailing edge wall 144 of the nozzle 36 to discharge the debris 142 directly into the hot gas path 64 instead of into the inter-wheel cavity 140.

[0041] According to various embodiments, the discharge passage 238 may extend at an angle toward the trailing edge 144 of the nozzle 36 through the platform 44 of the nozzle 36 to facilitate the discharge of debris 142. In other embodiments, the discharge passage 238 may extend vertically through the platform 44 of the nozzle 36. When used for a first-stage nozzle 36, the discharge passage 238 may be positioned at the rear of the inner chord hinge seal 60 to allow debris 142 to flow into the inter-wheel cavity 140 of the turbine section 24.

[0042] The various components disclosed herein can be formed using additive manufacturing processes. Advantageously, additive manufacturing enables the design and production of more customizable and complex feature structures.

[0043] As used herein, additive manufacturing can include any process that produces objects by continuously layering materials rather than removing them (as is the case with conventional processes). Additive manufacturing can form complex geometries without the use of any kind of tooling, molds, or jigs, and with little or no material waste. Instead of machining parts from solid plastic or metal blanks (many of which are cut away and discarded), the only material used in additive manufacturing is the material required to shape the part. Additive manufacturing processes can include, but are not limited to: 3D printing, rapid prototyping (RP), direct digital manufacturing (DDM), binder jetting, selective laser sintering (SLS), selective laser melting (SLM), direct metal laser sintering (DMLS), and direct metal laser melting (DMLM). In the current setup, DMLM or SLM has been found to be advantageous.

[0044] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that, when used in the specification, the terms “comprises” and / or “comprising” specify the presence of stated features, integers, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0045] This written description uses examples to disclose the invention, including the best mode, and also enables any person skilled in the art to practice the invention, including making and using any device or system and performing any combined methods. The patentable scope of the invention is defined by the claims and may include other examples that would occur to a person skilled in the art. Such other examples are contemplated within the scope of the claims if they have structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A gas turbine component having a debris evacuation circuit (130) for removing debris (142) from cooling air (120) flowing through the gas turbine component, the gas turbine component comprising: a strike insert (100) disposed within a cavity (102) in the gas turbine component, the strike insert (100) comprising an end wall (134) and a plurality of distribution holes (114) for directing cooling air (120) against a wall of the cavity (102); and a debris (142) evacuation circuit comprising: a bypass orifice (132, 232) defined in the end wall (134) of the strike insert (100), the bypass orifice (132, 232) fluidly coupling an interior (150) of the strike insert (100) and an end section (136) of the cavity (102); and an evacuation passage (138, 238) defined in a rear section of the gas turbine component, the evacuation passage (138, 238) fluidly coupling the end section (136) of the cavity (102) and an inter-wheel cavity (140) located radially inward of the gas turbine component; wherein the gas turbine component is configured to direct debris (142) in the cooling air (120) through the bypass orifice (132, 232) and the evacuation passage (138, 238) to the inter-wheel cavity (140) due to a pressure differential between the interior (150) of the gas turbine component and the inter-wheel cavity (140), wherein the gas turbine component comprises a nozzle (36) of a gas turbine system (10), characterized in that the plurality of distribution holes (114) for directing cooling air (120) against a wall of the cavity (102) are formed in a trailing edge (144) wall of the strike insert (100), and wherein the bypass orifice (132, 232) defined in the end wall (134) of the strike insert (100) is positioned adjacent to the trailing edge (144) wall. The nozzle (36) 2. The gas turbine component of claim 1, wherein, is a nozzle (36) located in a first stage (30) of a turbine of the gas turbine system (10). The evacuation passage (138, 238) reaches the inter-wheel cavity (140) through a platform (50) of the nozzle (36); and wherein the evacuation passage (138, 238) is angled toward a downstream end of the nozzle (36).

3. The gas turbine component of claim 1, wherein, The evacuation passage (138, 238) has an exit into the inter-wheel cavity (140) downstream of an inner chord hinge seal (60) of the nozzle (36).

4. The gas turbine component of claim 3, wherein, The evacuation passage (138, 238) is partially defined by a tubular structure extending from the end wall (134) of the strike insert (100) to the platform (50) of the nozzle (36).

5. The gas turbine component of claim 3, wherein, ​ 6. The gas turbine component of claim 1, further comprising a plurality of the bypass orifices (132, 232) located in the end wall (134) of the impingement insert (100).

7. The gas turbine component of claim 1, wherein, The bypass orifices (132, 232) have a diameter of 2.54 mm to 3.91 mm.

8. The gas turbine component of claim 1, wherein, The diameter of the exhaust passage (138, 238) is greater than or equal to the diameter of the bypass passage.

9. The gas turbine component of claim 1, wherein, The pressure ratio between the interior (150) of the gas turbine component and the inter-wheel cavity (140) is 1.1 to 1.

8.

10. A gas turbine component having an exhaust circuit for removing debris (142) from cooling air (120) flowing through a component of a gas turbine system (10), the gas turbine component comprising: an impingement insert (100) disposed within a cavity (102) in the gas turbine component, the impingement insert (100) comprising an end wall (134) and a plurality of distribution holes (114) for directing cooling air (120) against a wall of the cavity (102); and a debris (142) exhaust circuit comprising: a bypass orifice (132, 232) defined in the end wall (134) of the impingement insert (100), the bypass orifice (132, 232) fluidly coupling an interior (150) of the impingement insert (100) and an end section (136) of the cavity (102); and an exhaust passage (138, 238) defined in an aft section of the gas turbine component, the exhaust passage (138, 238) fluidly coupling the impingement insert (100) and a hot gas path (64) located at an exterior of the gas turbine component via the bypass orifice (132, 232); wherein the impingement insert (100) is configured to direct debris (142) in the cooling air (120) through the bypass orifice (132, 232) and the exhaust passage (138, 238) to the hot gas path (64) located at the exterior of the gas turbine component due to a pressure differential between the interior (150) of the impingement insert (100) and the exterior of the gas turbine component, wherein the gas turbine component comprises a nozzle (36) of the gas turbine system (10), characterized in that the exhaust passage (138, 238) is partially defined by a tubular structure extending from the end wall (134) of the impingement insert (100) to an aft edge (144) of the nozzle (36).

11. The gas turbine component of claim 10, wherein, The nozzle (36) is a nozzle (36) located in a first stage (30) of a turbine of the gas turbine system (10).

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