Gas turbine component with exhaust circuit for removing debris from cooling air supply source

Abstract

To provide a gas turbine component with an ejection circuit for removing debris from a cooling air supply.SOLUTION: A gas turbine component includes an ejection circuit 130 for removing debris 142 from cooling air 120 flowing through a gas turbine component. The gas turbine component includes: an impingement insert 100, which is disposed within a cavity 102 in the component and includes an end wall 144 and distribution holes 114 for directing cooling air against a wall of the cavity; a bypass aperture 132, which is defined in the end wall and fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel 138, which fluidly couples the end section of the cavity to a wheelspace cavity 140 or a hot gas path 64. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.SELECTED DRAWING: Figure 4

Description

Technical Field

[0001] The present disclosure generally relates to gas turbine systems, and more particularly to an exhaust circuit for removing debris from a source of cooling air flowing through components of a gas turbine system (e.g., a first stage nozzle).

Background Art

[0002] A gas turbine system is an example of a turbomachine widely used in fields such as power generation. Conventional gas turbine systems generally include a compressor section, a combustor section, and a turbine section. During operation of a gas turbine system, various components within the system, such as nozzle vanes, turbine blades, and shroud segments, are exposed to a high-temperature gas flow, which can cause the components to fail. A hotter gas flow generally results in an improvement in the performance, efficiency, and output of the gas turbine system. Therefore, it is beneficial to cool the components exposed to the high-temperature gas flow, operate the gas turbine system at a higher temperature, and extend the life of the components of the gas turbine system.

[0003] Cooling (e.g., impingement cooling, convective cooling, etc.) is often provided by directing a pressurized flow of a cooling fluid (e.g., air) through internal passages formed in components of the gas turbine system. In many cases, the cooling fluid is provided by bleeding off a portion of the pressurized air discharged by the compressor section of the gas turbine system. In many cases, a thin-walled container, generally referred to as an insert (e.g., an impingement insert), is attached to cavities within components of the gas turbine system (e.g., the vanes of a nozzle), which is configured to distribute the 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 in the cooling air entering the insert can accumulate in the small distribution holes in the insert's walls, potentially clogging these holes. Such clogging can reduce the insert's cooling efficiency and may lead to oxidation or other damage to parts of the insert. [Overview of the project]

[0005] One aspect of the present disclosure is a gas turbine component comprising an impingement insert disposed within a cavity of the gas turbine component, the impingement insert having an end wall and a plurality of distribution holes for directing cooling air to the wall of the cavity; a bypass opening defined in the end wall of the impingement insert, which fluidly couples the interior of the impingement insert with the end section of the cavity; and a discharge channel defined in the rear section of the gas turbine component, which fluidly couples the end section of the cavity with the wheel space cavity, the wheel space cavity comprising a debris discharge circuit including a discharge channel located radially inward of the gas turbine component. The pressure difference between the inside of the gas turbine components and the wheel space cavity guides debris in the cooling air into the wheel space cavity through bypass openings and discharge channels. This focuses on gas turbine components.

[0006] Another aspect of the present disclosure relates to a gas turbine component having a discharge circuit for removing debris from cooling air flowing through a component of a gas turbine system, comprising: an impingement insert disposed within a cavity of the gas turbine component, the impingement insert having an end wall and a plurality of distribution holes for directing cooling air to the wall of the cavity; and a debris discharge circuit comprising a bypass opening defined in the end wall of the impingement insert, which fluidly couples the interior of the impingement insert with the end section of the cavity; and a discharge channel defined in the rear section of the gas turbine component, which fluidly couples the impingement insert with a hot gas path outside the gas turbine component via the bypass opening, wherein the pressure difference between the interior of the impingement insert and the exterior of the gas turbine component directs the debris in the cooling air through the bypass opening and the discharge channel to the hot gas path outside the gas turbine component.

[0007] Exemplary embodiments of this disclosure solve problems described herein and / or other problems not discussed herein.

[0008] These and other features of the Disclosure will be more readily apparent from the following detailed description of various aspects of the Disclosure, in conjunction with the accompanying drawings illustrating various embodiments of the Disclosure. [Brief explanation of the drawing]

[0009] [Figure 1] This is a schematic diagram of a gas turbine system according to an embodiment described herein. [Figure 2] This is a side view of a portion of the turbine section of a gas turbine system including a debris discharge circuit, according to an embodiment described herein. [Figure 3] This is a perspective view of an impingement insert according to an embodiment described herein. [Figure 4]This figure schematically illustrates an enlarged view of the debris discharge circuit and its operation according to the embodiments described herein. [Figure 5] This figure schematically illustrates an enlarged view of a debris discharge circuit and its operation according to an additional embodiment described herein. [Modes for carrying out the invention]

[0010] Please note that the drawings in this disclosure are not necessarily to scale. The drawings are intended to illustrate only typical embodiments of this disclosure and should not be considered to limit the scope of this disclosure. In the drawings, similar reference numerals represent similar elements between drawings.

[0011] Hereinafter, we refer in detail to representative embodiments shown in the accompanying drawings. It should be understood that the following description is not intended to limit embodiments to one preferred embodiment. Rather, this disclosure is intended to cover alternatives, modifications, and equivalents that may fall within the spirit and scope of the described embodiments as defined by the accompanying claims.

[0012] As a first issue, in order to clearly explain the current disclosure, it is necessary to select specific technical terms when referring to and describing relevant mechanical components within the scope of this disclosure. Wherever possible, common industrial technical terms will be used and utilized in the same sense as their accepted meanings. Unless otherwise stated, such technical terms should be given a broad interpretation consistent with the context of this application and the appended claims. Those skilled in the art will understand that in many cases, certain components may be referred to using several different or overlapping terms. What may be described herein as a single part may include and be referred to in another context as consisting of multiple components. Or, what may be described herein as consisting of multiple components may be referred elsewhere as a single part.

[0013] In addition, several descriptive terms may be used in accordance with the rules of this specification, and it will be useful to define these terms at the beginning of this section. These terms and their definitions are as follows, unless otherwise specified: As used herein, “downstream” and “upstream” are terms indicating the direction of fluid flow, such as the working fluid through a turbine engine, or, for example, the flow of air through a combustor, or the coolant through one of the turbine's component systems. The term “downstream” corresponds to the direction of fluid flow, and the term “upstream” refers to the opposite direction of flow. The terms “forward” and “rear” refer to directions, unless otherwise specified, with “forward” referring to the front of the engine or compressor end, and “rear” referring to the rear of the engine or turbine end. In addition, the terms “leading” and “following” can be used and / or understood in the same manner as the terms “forward” and “rear,” respectively.

[0014] Often, it is required to describe parts located in different radial, axial, and / or circumferential directions. The "A" axis represents the axial orientation. As used herein, the terms "axial" and / or "axially" refer to the relative position / direction of an object along axis A substantially parallel to the axis of rotation of a gas turbine system (particularly the rotor section). Furthermore, as used herein, the terms "radial" and / or "radially" refer to the relative position / direction of an object along direction "R" (see Figures 1 and 2), which is substantially perpendicular to axis A and intersects axis A at only one location. Finally, the term "circumferential" refers to movement or position around axis A (e.g., direction "C").

[0015] In various embodiments, components described as "fluidically coupled" or "fluidly communicating" with one another can be joined along one or more interfaces. In some embodiments, these interfaces can include joints between separate components, and in other cases, these interfaces can include interconnections that are firmly and / or integrally formed. That is, in some cases, the "coupled" components can be formed simultaneously to define a single continuous member. However, in other embodiments, these coupled components can be formed as separate members and then joined by known processes (e.g., fastening, ultrasonic welding, bonding).

[0016] When an element or layer is referred to as “on top of,” “engaged with,” “connected to,” or “joined with” another element, it may be directly on top of, engaged with, connected to, or joined to the other element, or there may be an intervening element. Conversely, when an element is referred to as “directly on top of,” “directly engaged with,” “directly connected to,” or “directly joined with” another element, there may be no intervening element or layer. Other words used to describe relationships between elements should be interpreted similarly (e.g., “between” versus “directly between,” “adjacent to” versus “directly adjacent to.”). As used herein, the term “and / or” includes any combination of one or more of the related enumerated items.

[0017] Figure 1 illustrates schematic diagrams of gas turbine systems 10 according to various embodiments. As shown, the gas turbine system 10 includes a compressor section 12 for compressing an incoming airflow 14 and delivering a pressurized flow of compressed air 16 to a combustor section 18. The combustor section 18 mixes the flow of compressed air 16 with a pressurized feed of fuel 20 and ignites the mixture to produce a flow of combustion gases 22. Although only a single combustor section 18 is shown, the gas turbine system 10 may include any number of combustor sections 18. The flow of combustion gases 22 is then delivered to a turbine section 24. The flow of combustion gases 22 drives the turbine section 24 to generate mechanical work. The mechanical work generated in the turbine section 24 may be used to drive the compressor section 12 via a shaft 26 and further to drive an external load 28 such as a generator.

[0018] Figure 2 illustrates a side view of a portion of the turbine section 24 of a gas turbine system (e.g., the gas turbine system 10 in Figure 1), which includes at least one turbine stage 30. The turbine stage 30 includes a set of turbine blades 32 (one blade 32 is shown) and a set of corresponding nozzles 36 (one nozzle 36 is shown) positioned within the casing 38 of the turbine section 24. For example, as shown in Figure 2, the stage 30 of the turbine blades 32 may consist of a first stage 30 of the turbine blades 32 and a nozzle 36 within the turbine section 24. During operation, the set of first stage nozzles 36 34 is configured to direct the flow of combustion gas 22 onto the turbine blades 32 of the first turbine stage 30. Each nozzle 36 in the first set 34 of 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) in order to separate the high-pressure compressed air in the region 62 generated by the compressor section 12 (Figure 1) from the low-pressure, high-temperature combustion gas 22 flowing along the high-temperature gas path 64 to the turbine blades 32 of the first stage 30 in the turbine section 24.

[0019] A turbine blade 32 in a particular stage (e.g., the first stage 30) may include a plurality of turbine blades 32 coupled to the rotor 26, positioned circumferentially around it, and driven by combustion gases 22 generated by the combustor section 18 (Figure 1) of the gas turbine system. A set of nozzles 36 34 within the first stage 30 includes a plurality of stationary nozzles 36 coupled to the casing 38 of the turbine section 24 and positioned circumferentially around it. In the embodiment shown in Figure 2, each nozzle 36 may include a vane 40 positioned between an outer platform 42 and an inner platform 44. Similar to the nozzles 36, each turbine blade 32 in the turbine section 24 may include an airfoil 46 extending radially from the rotor 26. Each airfoil 46 may include a tip portion 48 and a platform 50 positioned opposite the tip portion 48.

[0020] The turbine blades 32 and nozzles 36 can be positioned adjacent to each other axially within the casing 38. Figure 2 shows, for example, a set of nozzles 36 positioned axially upstream adjacent to 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 positioned axially throughout the casing 38.

[0021] The turbine section 24 of the gas turbine system 10 can include a plurality of stages 52 of shroud 54 (one stage shown in FIG. 2) axially positioned throughout the casing 38. In FIG. 2, for example, the stage 52 of the shroud 54 is shown radially positioned adjacent to the turbine blade 32 of the turbine stage 30 and substantially surrounding or encompassing the turbine blade. The stage 52 of the shroud 54 may also be axially and / or downstream positioned adjacent to the set 34 of nozzles 36. Further, the stage 52 of the shroud 54 can be positioned between two adjacent sets 34 of nozzles 36 located on both sides of the turbine blade 32 of the turbine stage 30. The stage 52 of the shroud 54 can be coupled around the casing 38 of the turbine section 24 using a set of extensions 56 that each include an opening 58 configured to receive a corresponding section of the shroud 54.

[0022] Referring to FIGS. 2-4, an impingement insert 100 can be positioned within a cavity 102 formed in a vane 40 of at least one nozzle 36 of at least one set 34 of nozzles 36 within the turbine section 24. As shown in detail in FIG. 3, the impingement insert 100 can include a body 104 that has a leading edge wall 106, a trailing edge wall 108, and first and second side walls 110, 112 extending between the leading edge wall 106 and the trailing edge wall 108 of the body 104. A plurality of distribution holes 114 may be formed through one or more of the leading edge wall 106, the trailing edge wall 108, the first side wall 110, and / or the second side wall 112 and may extend from an inner surface 116 of the impingement insert 100 to an outer surface 118 of the impingement insert 100. A pressurized flow of cooling air 120, which can be provided by extracting a portion of the compressed air 16 discharged by the compressor section 12 of the gas turbine system 10 (FIG. 1), can be directed through an opening 122 into the interior 150 of the impingement insert 100.

[0023] Next, the debris discharge circuit 130 according to the present disclosure will be described with reference to Figures 2 to 4. At least one nozzle 36 in a set 34 of nozzles 36 (e.g., nozzles 36 of the first stage 30 of the turbine section 24) may include the debris discharge circuit 130. As shown, the debris discharge circuit 130 may include at least one bypass opening 132 extending through the bottom (e.g., end) wall 134 of the impingement insert 100 to fluidly couple the interior 150 of the impingement insert 100 with the bottom (e.g., end) section 136 of the cavity 102 located beneath the impingement insert 100. The debris discharge circuit 130 may further include a discharge channel 138 (Figures 2 and 4) extending through the inner platform 44 of the nozzle 36 and fluidly couple the bottom section 136 of the cavity 102 located beneath the impingement insert 100 with the wheel space cavity 140 of the turbine section 24.

[0024] During operation of the gas turbine system 10 (Figure 1), small particles (e.g., rust fragments from the compressor section casing, sand, etc.) contained in the cooling air 120 entering the impingement insert 100 can accumulate in the small distribution holes 114 in the walls 106, 108, 110, and / or 112 of the impingement insert 100, potentially blocking the distribution holes. Such blockage can reduce the cooling efficiency of the impingement insert 100 and may result in oxidation or other damage to part of the impingement insert 100. Advantageously, such debris is removed from the impingement insert 100 by the debris removal circuit 130 according to this embodiment.

[0025] Figure 4 illustrates the debris discharge circuit 130 and an enlarged view of its operation. In the embodiment shown in Figure 4, the debris discharge circuit 130 may be provided in the first set 34 of nozzles 36 of the nozzles 36 within the first turbine stage 30. The impingement insert 100 of this embodiment provides impingement cooling to the rear end portion 131 of the cavity 102 via a plurality of distribution holes 114 formed in the trailing edge wall 108 of the impingement insert 100. In this regard, the flow of cooling air 120 entering the impingement insert 100 flows downward into the interior 150 of the impingement insert 100 and then flows towards a plurality of distribution holes 114 formed in the trailing edge wall 108 of the body 104 of the impingement insert 100.

[0026] The debris discharge circuit 130 can include at least one bypass opening 132 (three bypass openings 132 are shown in the illustrated embodiment) extending through the bottom wall 134 of the impingement insert 100. Each bypass opening 132 is configured to fluidly couple the interior 150 of the impingement insert 100 with the bottom section 136 of the cavity 102 disposed below the impingement insert 100. According to an embodiment, each bypass opening 132 can have a diameter larger than the size (e.g., width, diameter, etc.) of any debris 142 that may be expected to enter the impingement insert 100 during operation of the gas turbine system. For example, in a non-limiting example, the bypass opening 132 may have a diameter of from about 0.10 inches to about 0.15 inches (from about 2.54 mm to about 3.91 mm). Although three bypass openings 132 are shown in Figures 2 - 4, fewer or more bypass openings 132 can be used. Further, all of the bypass openings 132 may have the same diameter, or the bypass openings 132 may have two or more different diameters.

[0027] As shown in Figure 4, the flow of cooling air 120 can transport (e.g., carry) the debris 142 into the interior 150 of the impingement insert 100. The momentum of the debris 142 (e.g., due to the velocity of the flow of cooling air 120) is high enough that the debris 142 is not redirected to the distribution hole 114 formed in the trailing edge wall 108 of the body 104 of the impingement insert 100, but instead moves towards the bottom wall 134 of the impingement insert 100. The debris 142 can be briefly recirculated at the bottom of the impingement insert 100 before passing through the bypass opening 132 in the bottom wall 134 of the impingement insert 100 and entering the bottom section 136 of the cavity 102.

[0028] As shown in Figure 4, the cooling air 120 flows into the interior 150 of the impingement insert 100, into a distribution hole 114 formed in the trailing edge wall 108 of the body 104 of the impingement insert 100, and flows through it. In this respect, the debris 142 may be deflected toward the trailing edge wall 108 by the flow of the cooling air 120 as the debris 142 moves toward the bottom wall 134 of the impingement insert 100. According to the embodiment, the bypass opening 132 is positioned toward the trailing edge wall 108 of the body 104 of the impingement insert 100 (for example, as close as possible) in the bottom wall 134, thereby increasing the probability that the debris 142 will be captured by the bypass opening 132 and pass through the bypass opening into the bottom section 136 of the cavity 102.

[0029] The debris discharge circuit 130 may further include a discharge channel 138 extending through the inner platform 44 of the nozzle 36. The discharge channel 138 fluidly couples the bottom section 136 of the cavity 102 located beneath the impingement insert 100 with the wheel space cavity 140 of the turbine section 24. The discharge channel 138 may have a diameter greater than or equal to the diameter of the bypass opening 132.

[0030] According to various embodiments, the discharge channel 138 can be positioned behind the bypass opening 132 (for example, 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 can extend at an angle through the platform 44 of the nozzle 36 toward the trailing edge 144 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 with a first-stage nozzle 36, the discharge channel 138 can be positioned behind the inner chord hinge seal 60 to allow debris 142 to flow into the wheel space cavity 140 of the turbine section 24. In an alternative embodiment illustrated by dashed lines in Figure 4, the discharge channel 138' can be formed in the trailing edge wall 144 of the nozzle 36, allowing debris 142 to be discharged directly into the hot gas path 64 instead of the wheel space cavity 140.

[0031] A pressure difference exists across the discharge channel 138 that draws the debris 142 from the bottom section 136 of the cavity 102 into the wheel space cavity 140 of the turbine section 24. For example, according to the embodiments described herein, the pressure in the bottom section 136 of the cavity 102 due to the flow of cooling air 120 entering the impingement insert 100 is greater than the pressure in the wheel space cavity 140. This pressure difference generates an airflow through the discharge channel 138 that propels the debris 142 from the bottom section 136 of the cavity 102 into the wheel space cavity 140. From the wheel space cavity 140, the debris 142 can flow into the hot gas path 64 of the turbine section 24 and eventually exit the gas turbine system.

[0032] According to some embodiments, the pressure ratio across the discharge channel 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, placement, and / or diameter of the bypass openings 132, the placement, angle, and / or diameter of the discharge channel 138, and / or other factors (e.g., the flow rate of the cooling air 120, the pressure in the wheel space cavity 140, etc.).

[0033] Figure 5 shows an enlarged view of the debris removal circuit 230 and its operation according to an additional embodiment. As described above with respect to the embodiment illustrated in Figure 4, the debris 142 enters the bottom section 136 of the cavity 102 through a bypass opening 132 in the bottom wall 134 of the impingement insert 100, and 2) enters the wheel space cavity 140 through the discharge channel 138 from the bottom section 136 of the cavity 102. However, as shown in Figure 5, the debris removal circuit 230 may include a discharge channel 238, which is configured as a tubular structure extending from the bottom of the impingement insert 100 and directly fluid-couples the impingement insert 100 and the wheel space cavity 140 for removing the debris 142 (via the bypass opening 232).

[0034] The debris discharge circuit 230 may include at least one bypass opening 232 extending through the bottom wall 134 of the impingement insert 100. If multiple bypass openings 232 are used, all of the bypass openings 232 may be fluid-coupled to the same discharge channel 238. According to such embodiments, the bypass openings 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 impingement insert 100 during the operation of the gas turbine system. For example, in a non-limiting example, the bypass openings 232 may have a diameter of about 0.10 inches to about 0.15 inches (about 2.54 mm to about 3.91 mm). Figure 5 illustrates one bypass opening 232, but many more bypass openings 232 can be used. Furthermore, all bypass openings 232 may have the same diameter, or the bypass openings 232 may have two or more different diameters. The discharge channel 238 may have a diameter greater than or equal to the diameter of the bypass openings 232.

[0035] As shown in Figure 5, the flow of cooling air 120 can transport the debris 142 into the interior 150 of the impingement insert 100. Here again, the momentum of the debris 142 is high enough that it is not redirected to the distribution holes 114 formed in the wall of the impingement insert 100, but instead moves towards the bottom wall 134 of the impingement insert 100. The debris 142 can be briefly recirculated at the bottom of the impingement insert 100 before passing through the bypass opening 232 in the bottom wall 134 of the impingement insert 100 and entering the discharge channel 238.

[0036] A pressure difference exists across the discharge channel 238, configured to draw the debris 142 through the discharge channel 238 into the wheel space cavity 140 of the turbine section 24. For example, according to one embodiment, the pressure inside the impingement insert 100 due to the flow of cooling air 120 entering the impingement insert 100 is greater than the pressure inside the wheel space cavity 140. This pressure difference generates an airflow through the discharge channel 238 that propels the debris 142 into the bypass opening 232 and then into the wheel space cavity 140 through the discharge channel 238. From the wheel space cavity 140, the debris 142 can flow into the hot gas path 64 of the turbine section 24 and eventually exit the gas turbine system. In an alternative embodiment illustrated by dashed lines in Figure 5, the discharge channel 238' can be formed in the trailing edge wall 144 of the nozzle 36, allowing the debris 142 to be discharged directly into the hot gas path 64 instead of the wheel space cavity 140.

[0037] According to various embodiments, the discharge channel 238 may extend at an angle through the platform 44 of the nozzle 36 toward the trailing edge 144 of the nozzle 36 to facilitate the discharge of debris 142. In other embodiments, the discharge channel 238 may extend vertically through the platform 44 of the nozzle 36. When used with a first-stage nozzle 36, the discharge channel 238 may be positioned behind the inner chord hinge seal 60 to allow debris 142 to flow into the wheel space cavity 140 of the turbine section 24.

[0038] Various components of this disclosure can be formed using additive manufacturing processes. Advantageously, additive manufacturing allows for the design and manufacture of more customizable and complex features.

[0039] As used herein, additive manufacturing may include any process that manufactures an object through the continuous layering of material rather than the removal of material, as in conventional processes. Additive manufacturing can form complex geometric shapes without the use of any kind of tools, molds, or equipment, and with little or no waste material. Instead of machining components from solid billets of plastic or metal, much of which would be cut and discarded, the material used in additive manufacturing is only the material required to form the part. Additive manufacturing processes may 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 setting, DMLM or SLM has been found to be advantageous.

[0040] The technical terms used herein are for the sole purpose of describing specific embodiments and are not intended to limit the disclosure. Where used herein, the singular forms “a,” “an,” and “the” are intended to include the plural unless otherwise explicitly indicated by the context. Where used herein, the terms “comprise” and / or “comprising” express the existence of the described features, integers, steps, actions, elements, and / or components, but do not exclude the existence or addition of one or more other features, integers, steps, actions, elements, components, and / or sets thereof.

[0041] This specification discloses the present invention, including its best mode, and uses examples to enable any person skilled in the art to practice the invention, including the fabrication and use of any apparatus or system and the execution of any incorporated method. The patentable scope of the present invention is defined by the claims and may include other embodiments that a person skilled in the art may conceive. Such other embodiments are intended to be within the claims if they have structural elements that do not differ from the language of the claims, or if they include equivalent structural elements that do not substantially differ from the language of the claims. [Explanation of symbols]

[0042] 10 Gas Turbine Systems 12 Compressor Section 14 Airflow 16 Compressed air 18. Combustor Section 20 fuel 22 Combustion gases 24 Turbine Section 26 Shaft, Rotor 28 External load 30 First Turbine Stage 32 Turbine Blades 34 First Set 36. First stage nozzle, stationary nozzle 38 Casing 40 vanes 42 Outer platform 44 Inner Platform 46 Airfoil 48 Tip part 50 platforms 52 steps 54 Shroud 56 Extension 58 Opening 60 Inner wing chord hinge seal 62 areas 64 High-temperature gas pathway 100 impingement inserts 102 Cavity 104 Main Unit 106 Front edge wall 108 Trailing edge wall 110 First side wall 112 Second side wall 114 Distribution hole 116 Inner self 118 Exterior 120 Cooling air 122 Opening 130 Debris Ejection Circuit 131 Rear end 132 Bypass opening 134 Bottom wall, end wall 136 Bottom section, end section 138 Emission Channels 138' Emission Channel 140 Wheelspace Cavity 142 Debris 144 Trailing edge, trailing edge wall 150 internal 230 Debris Ejection Circuit 232 Bypass opening 238 Emission Channels 238' Emission Channel A-axis, arrow

Claims

1. A gas turbine component of a gas turbine system (10), A gas turbine component extending in the radial direction, comprising a discharge circuit (130) for removing debris (142) from cooling air (120) flowing through the gas turbine component, An impingement insert (100) disposed within a cavity (102) of the gas turbine component, the impingement insert (100) includes an end wall (134) and a plurality of distribution holes (114) for guiding cooling air (120) to the wall of the cavity (102), Bypass openings (132, 232) defined in the end wall (134) of the impingement insert (100), which fluidly connect the interior (150) of the impingement insert (100) to the cavity (102), and Discharge channels (138, 238) defined in the inner platform (44) of the gas turbine component, which fluidly connect the cavity (102) and the wheel space cavity (140), wherein the wheel space cavity (140) is located radially inward of the gas turbine component. Debris (142) discharge circuit (130) including Equipped with, The end wall (134) is located at the radially inward end of the impingement insert (100). The pressure difference between the interior (150) of the gas turbine component and the wheel space cavity (140) guides the debris (142) in the cooling air (120) into the wheel space cavity (140) through the bypass openings (132, 232) and the discharge channels (138, 238). The gas turbine component includes the nozzle (36) of the gas turbine system (10), The plurality of distribution holes (114) for guiding cooling air (120) against the wall of the cavity (102) are formed in the rear edge (108) wall of the impingement insert (100), The bypass openings (132, 232) defined in the end wall (134) of the impingement insert (100) are positioned adjacent to the trailing edge (108) wall. Gas turbine components.

2. The gas turbine component according to claim 1, wherein the discharge channels (138, 238) are located behind the bypass openings (132, 232) and adjacent to the trailing edge of the gas turbine component.

3. The gas turbine component according to claim 1, wherein the nozzle (36) includes the nozzle (36) of the first stage (30) of the turbine of the gas turbine system (10).

4. The gas turbine component according to claim 1, wherein the discharge channels (138, 238) pass through the inner platform (44) of the nozzle (36) and enter the wheel space cavity (140), and the discharge channels (138, 238) are inclined toward the downstream end of the nozzle (36).

5. The gas turbine component according to claim 4, wherein the discharge channels (138, 238) have outlets to the wheel space cavity (140) downstream of the inner chord hinge seal (60) of the nozzle (36).

6. The gas turbine component according to claim 4, wherein the discharge channels (138, 238) are partially defined by a tubular structure extending from the end wall (134) of the impingement insert (100) to the inner platform (44) of the nozzle (36).

7. The gas turbine component according to claim 1, further comprising a plurality of bypass openings (132, 232) in the end wall (134) of the impingement insert (100).

8. The gas turbine component according to claim 1, wherein the bypass openings (132, 232) have a diameter of approximately 2.54 mm to approximately 3.91 mm.

9. The gas turbine component according to claim 1, wherein the discharge channels (138, 238) have a diameter greater than or equal to the diameter of the bypass openings (132, 232).

10. The gas turbine component according to claim 1, wherein the pressure ratio between the interior (150) and the wheel space cavity (140) of the gas turbine component is about 1.1 to about 1.

8.

11. A gas turbine component extending radially, having a discharge circuit (130) for removing debris (142) from cooling air (120) flowing through the components of a gas turbine system (10), An impingement insert (100) disposed within a cavity (102) of the gas turbine component, the impingement insert (100) includes an end wall (134) and a plurality of distribution holes (114) for guiding cooling air (120) to the wall of the cavity (102), Bypass openings (132, 232) defined in the end wall (134) of the impingement insert (100), which fluidly connect the interior (150) of the impingement insert (100) to the cavity (102), and Discharge channels (138, 238) defined in the inner platform (44) of the gas turbine component, wherein the discharge channels (138, 238) fluidly couple the impingement insert (100) and the high-temperature gas path (64) outside the gas turbine component via the bypass openings (132, 232). Debris (142) discharge circuit (130) including Equipped with, The end wall (134) is located at the radially inward end of the impingement insert (100). The pressure difference between the interior (150) of the impingement insert (100) and the exterior of the gas turbine component guides the debris (142) in the cooling air (120) through the bypass openings (132, 232) and the discharge channels (138, 238) to the high-temperature gas path (64) outside the gas turbine component. The gas turbine component includes the nozzle (36) of the gas turbine system (10), The plurality of distribution holes (114) for guiding cooling air (120) against the wall of the cavity (102) are formed in the rear edge (108) wall of the impingement insert (100), The bypass openings (132, 232) defined in the end wall (134) of the impingement insert (100) are positioned adjacent to the trailing edge (108) wall. Gas turbine components.

12. The gas turbine component according to claim 11, wherein the discharge channels (138, 238) are located behind the bypass openings (132, 232) and adjacent to the trailing edge of the gas turbine component.

13. The gas turbine component according to claim 11, wherein the nozzle (36) is provided on the first stage (30) of the turbine of the gas turbine system (10).

14. The gas turbine component according to claim 11, wherein the discharge channels (138, 238) are partially defined by a tubular structure extending from the end wall (134) of the impingement insert (100) to the trailing edge (108) of the nozzle (36).

Images