Stator vane assembly with mechanical retention

Abstract

The stator vane assembly (200) includes a platform (201) defining an opening (102). The stator vane assembly (200) also includes an airfoil section (206) that includes an airfoil (56) and a boss (216). The airfoil (56) includes a leading edge (60), a trailing edge (62), a suction side wall (66), and a pressure side wall (64). The airfoil (56) extends radially between the base (68) and the tip (70). The boss (216) extends from one of the base (68) or the tip (70) of the airfoil (56). The boss (216) is disposed in the opening (102) of the platform (201). The stator vane assembly (200) also includes a mechanical retention device (210) that couples the platform (201) to the boss (216) of the airfoil section (206).

Description

Technical Field

[0001] The present disclosure generally relates to a stator vane having multiple components joined together via a mechanical retention device. Background Art

[0002] Turbines are used for energy transfer purposes in various industries and applications. For example, a gas turbine engine typically includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid entering the gas turbine engine, and supplies the compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed in the combustion section and burned in the combustion chamber to generate high-pressure and high-temperature combustion gases. The combustion gases flow from the combustion section into the turbine section, where the combustion gases expand to do work. For example, the expansion of the combustion gases in the turbine section can rotate a rotor shaft connected to, for example, a generator to generate electricity. The spent combustion gases then leave the turbine section via the exhaust section.

[0003] During operation of the turbine, various hot gas path components in the system are subjected to high temperature flows, which can lead to failure of the hot gas path components. Since higher temperature flows generally result in increased performance, efficiency, and power output of the turbine, the hot gas path components subjected to high temperature flows must be cooled to allow the gas turbine system to operate at the elevated temperature flows.

[0004] Forced air cooling becomes necessary when the maximum local temperature of a hot gas path component approaches the melting temperature of the hot gas path component. To this end, turbine rotor blades and fixed nozzle airfoils often require complex cooling schemes in which air (usually bleed air from the compressor segment) is forced through internal cooling passages within the airfoil and then exhausted through cooling holes at the airfoil surface to transfer heat from the hot gas path component.

[0005] Many complex cooling schemes use small cooling passages or microchannels to deliver cooling fluid through the airfoil. Such cooling schemes present considerable manufacturing challenges to the core and castings, which can significantly increase the manufacturing cost of hot gas path components using such known near-wall cooling systems. In order to address the manufacturing challenges of complex and / or small cooling passages near the surface of the component, many hot gas path components with such features can be additively manufactured. Additive manufacturing is able to produce components with complex and varying cooling features. However, additive manufacturing of hot gas path components such as rotor blades or stator vanes as a single component can be expensive and time-consuming. In addition, manufacturing errors in a single portion of a hot gas path component may result in the scrapping of the entire component.

[0006] Therefore, it may be advantageous to manufacture the hot gas path component as multiple subcomponents. However, due to the complex geometry of the subcomponents, joining the subcomponents to form the hot gas path component may be difficult. Additionally, the joints formed between the subcomponents may be particularly weak and / or fail when exposed to the hot combustion gases that are generated during operation of the turbine and transmitted through the hot gas path through the turbine segment.

[0007] Therefore, an improved hot gas path component having one or more subcomponents that are joined together and capable of withstanding the hot combustion gases without risk of joint failure is desirable and would be appreciated in the art. Summary of the invention

[0008] Various aspects and advantages of stator vane assemblies and turbines according to the present disclosure will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the technology.

[0009] According to one embodiment, a stator guide vane assembly is provided. The stator guide vane assembly includes a platform defining an opening. The stator guide vane assembly also includes an airfoil section, the airfoil section including an airfoil and a boss. The airfoil includes a leading edge, a trailing edge, a suction sidewall, and a pressure sidewall. The airfoil extends radially between a base and a top end. The boss extends from at least one of the base or the top end of the airfoil. The boss is disposed in the opening of the platform. The stator guide vane assembly also includes a mechanical retaining device that couples the platform to the boss of the airfoil section.

[0010] According to another embodiment, a turbine is provided. The turbine defines an axial direction, a radial direction, and a circumferential direction. The turbine includes a compressor segment, a combustion segment, and a turbine segment. At least one of the compressor segment or the turbine segment includes a stator guide vane assembly. The stator guide vane assembly includes a platform defining an opening. The stator guide vane assembly also includes an airfoil section, which includes an airfoil and a boss. The airfoil includes a leading edge, a trailing edge, a suction sidewall, and a pressure sidewall. The airfoil extends radially between a base and a top end. The boss extends from at least one of the base or the top end of the airfoil. The boss is disposed in the opening of the platform. The stator guide vane assembly also includes a mechanical retaining device that couples the platform to the boss of the airfoil section.

[0011] These and other features, aspects and advantages of the stator guide vane assembly and method of the present invention will become better understood with reference to the following description and appended claims.The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present invention and, together with the description, serve to explain the principles of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] This specification sets forth a complete and enabling disclosure of the stator guide vane assembly and turbine of the present invention, including the best mode of making the system of the present invention and using the system and method of the present invention, to one of ordinary skill in the art, with reference to the accompanying drawings, in which:

[0013] Figure 1 is a schematic diagram of a turbomachine (e.g., a gas turbine engine) according to an embodiment of the present disclosure;

[0014] Figure 2 The embodiment according to the present disclosure is shown as follows Figure 1 A partial cross-sectional side view of a turbine segment of a gas turbine engine is shown;

[0015] Figure 3 shows an exploded view of a stator vane according to an embodiment of the present disclosure;

[0016] Figure 4 shows a perspective view of an airfoil segment according to an exemplary aspect of the present disclosure;

[0017] Figure 5 shows a perspective view of an outer portion of a stator vane assembly including an airfoil segment and an outer platform according to an exemplary embodiment of the present disclosure;

[0018] Figure 6 According to an exemplary embodiment of the present disclosure, Figure 5 A perspective cross-sectional view of the stator guide vane assembly taken along line 6-6 shown in FIG.

[0019] Figure 7 shows a plan view of a stator guide vane assembly according to an exemplary embodiment of the present disclosure;

[0020] Figure 8 According to an exemplary embodiment of the present disclosure, Figure 7 A perspective cross-sectional view of the stator guide vane assembly taken along line 8-8 shown in FIG.

[0021] Fig. 9 shows a perspective view of an interior portion of a stator vane assembly including an airfoil segment and an inner platform according to an exemplary embodiment of the present disclosure;

[0022] Fig.10 According to an exemplary embodiment of the present disclosure, Fig. 9 a perspective cross-sectional view of the stator guide vane assembly taken along line 10-10 shown in FIG. 1 ; and

[0023] Fig.11 A perspective cross-sectional view of a stator vane assembly according to an embodiment of the present disclosure is shown. DETAILED DESCRIPTION

[0024] Reference will now be made in detail to embodiments of the stator guide vane assembly and turbine of the present invention, one or more examples of which are shown in the accompanying drawings. Each example is provided by way of explanation of the present invention technology, rather than limitation of the present invention technology. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the present invention technology without departing from the scope or essence of the present invention technology protected by the claims. For example, a feature shown or described as part of one embodiment can be used with another embodiment to produce yet another embodiment. Therefore, the present disclosure is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0025] The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. In addition, unless otherwise specifically stated, all embodiments described herein should be considered exemplary.

[0026] The detailed description uses numbers and letter names to refer to the features in the drawings. Similar or similar names in the drawings and description have been used to refer to similar or similar parts of the present invention. As used herein, the terms "first", "second", and "third" may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of the various components.

[0027] The term "fluid" may be a gas or a liquid. The term "fluid communication" means that two or more regions defining a flow channel are joined to each other so that a fluid can form a connection between the designated regions.

[0028] As used herein, the terms "upstream" (or "upward") and "downstream" (or "downward") refer to relative directions relative to the flow of a fluid in a fluid passage. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing. The term "radially" refers to a relative direction that is substantially perpendicular to the axial centerline of a particular component; the term "axially" refers to a relative direction that is substantially parallel and / or coaxially aligned with the axial centerline of a particular component; and the term "circumferentially" refers to a relative direction that extends around the axial centerline of a particular component.

[0029] Terms with approximate meanings (such as "about", "approximately", "substantially" and "substantially") are not limited to the exact values ​​specified. In at least some cases, approximate language may correspond to the accuracy of an instrument used to measure a value, or the accuracy of a method or machine used to construct or manufacture a component and / or system. In at least some cases, approximate language may correspond to the accuracy of an instrument used to measure a value, or the accuracy of a method or machine used to construct or manufacture a component and / or system. For example, approximate language may refer to a tolerance of 1%, 2%, 4%, 5%, 10%, 15% or 20% in an individual value, a range of values, and / or an end value of a range of defined values. When used in the context of an angle or direction, such terms are included within ten degrees greater than or less than the angle or direction. For example, "substantially vertical" includes directions within ten degrees of vertical in any direction (e.g., clockwise or counterclockwise).

[0030] Unless otherwise indicated herein, the terms "coupled," "fixed," "attached to," and the like refer to both direct coupling, fixing, or attachment, as well as indirect coupling, fixing, or attachment through one or more intermediate components or features. The terms "directly coupled," "directly fixed," "directly attached to," and the like mean that two components are engaged in contact with one another and there are no intermediate components or features present.

[0031] As used herein, the terms "includes," "comprising," "having," or any other variation thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, article, or apparatus that includes a list of features is not necessarily limited to only those features but may include other features not expressly listed or inherent to such process, method, article, or apparatus. In addition, unless expressly specified otherwise, "and / or" refers to a condition that is satisfied by any of the following: A is true (or exists) and B is false (or does not exist); A is false (or does not exist) and B is true (or exists); and both A and B are true (or exist).

[0032] Here and throughout the specification and claims, unless context or language indicates otherwise, range limitations are combined and interchanged, such ranges are identified and include all sub-ranges contained therein. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other.

[0033] The phrase "adjacent" means closer to one end than the opposite end. For example, when used in conjunction with a first end and a second end; a high pressure side and a low pressure side; a leading edge and a trailing edge; etc., the phrase "adjacent to the first end" or "adjacent to the high pressure side" refers to a position closer to the first end than the second end or a position closer to the high pressure side than the low pressure side, respectively.

[0034] As used herein, "solid" may refer to a component that is free of voids, cavities, holes, or other openings, such that the component is impermeable and does not allow air or other fluids to pass therethrough.

[0035] Now referring to the accompanying drawings, Figure 1 A schematic diagram of one embodiment of a turbomachine is shown, which in the illustrated embodiment is a gas turbine engine 10. Although an industrial or land-based gas turbine engine is shown and described herein, the present disclosure is not limited to industrial and / or land-based gas turbine engines unless otherwise indicated in the claims. For example, the present invention as described herein may be used for any type of turbomachine, including but not limited to a steam turbine, an aircraft gas turbine, or a marine gas turbine.

[0036] like Figure 1 As shown, the gas turbine engine 10 generally includes a compressor section 12. The compressor section 12 includes a compressor 14. The compressor section 12 includes an inlet 16 disposed at the upstream end of the gas turbine engine 10. The gas turbine engine 10 also includes a combustion section 18 having one or more combustors 20 disposed downstream of the compressor section 12. The gas turbine engine 10 also includes a turbine section 22 (i.e., an expansion turbine) located downstream of the combustion section 18. A shaft 24 generally extends axially through the gas turbine engine 10.

[0037] The compressor segment 12 may generally include a plurality of rotor disks 21 and a plurality of rotor blades 23 extending radially outward from each rotor disk 21 and connected to each rotor disk. Each rotor disk 21 may in turn be coupled to or form a portion of a shaft 24 extending through the compressor segment 12. The rotor blades 23 of the compressor segment 12 may include a turbine airfoil defining an airfoil shape (e.g., having a leading edge, a trailing edge, and a sidewall extending between the leading edge and the trailing edge). Additionally, in many embodiments, the compressor segment 12 may include stator vanes 19 disposed between the rotor blades 23. The stator vanes 19 may extend from the compressor casing 11 and be coupled to the compressor casing.

[0038] The turbine segment 22 may generally include a plurality of rotor disks 27 and a plurality of rotor blades 28 extending radially outward from each rotor disk 27 and interconnected to each rotor disk. Each rotor disk 27, in turn, may be coupled to or form a portion of a shaft 24 extending through the turbine segment 22. The turbine segment 22 also includes an outer casing 32 that circumferentially surrounds a portion of the shaft 24 and the rotor blades 28. The turbine segment 22 may include stator vanes or fixed nozzles 26 extending radially inward from the outer casing 32. The rotor blades 28 and the stator vanes 26 may be arranged in an alternating manner along the axial centerline 30 of the gas turbine 10. Both the rotor blades 28 and the stator vanes 26 may include a turbine airfoil defining an airfoil shape (e.g., having a leading edge, a trailing edge, and a sidewall extending between the leading edge and the trailing edge).

[0039] In operation, ambient air 36 or other working fluid is drawn into the inlet 16 of the compressor 14 and is gradually compressed to provide compressed air 38 to the combustion section 18. The compressed air 38 flows into the combustion section 18 and mixes with the fuel to form a combustible mixture. The combustible mixture is burned in the combustion chamber 40 of the combustor 20, thereby generating combustion gases 42 that flow from the combustion chamber 40 into the turbine section 22. Energy (kinetic energy and / or thermal energy) is transferred from the combustion gases 42 to the rotor blades 28, causing the shaft 24 to rotate and produce mechanical work. The spent combustion gases 42 (also referred to as "exhaust gases") leave the turbine section 22 and flow through the exhaust diffuser 34 across a plurality of struts or main airfoils 44 disposed within the exhaust diffuser 34.

[0040] The gas turbine 10 may define a cylindrical coordinate system having an axial direction A extending along the axial centerline 30 , a radial direction R perpendicular to the axial centerline 30 , and a circumferential direction C extending about the axial centerline 30 .

[0041] Figure 2 is a partial cross-sectional side view of a turbine segment 22 of a gas turbine engine 10 according to an embodiment of the present disclosure. The turbine segment 22 may include one or more stages 50, each stage including a set of rotor blades 28 coupled to a rotor disk 27, which is rotatably attached to a shaft 24. Each of the one or more stages 50 also includes a set of stator vanes 26 axially adjacent to the set of rotor blades 28. The stator vanes 26 described herein may be used in a first stage, a second stage, a third stage, a fourth stage, or a plurality of stages, where "first stage" refers to a stage immediately downstream of the combustion segment 18.

[0042] Each stator vane 26 may include at least one airfoil 56 extending in the radial direction R between the inner platform or end wall 52 and the outer platform or end wall 54. The circumferentially adjacent outer platforms 54 of each stator vane 26 may be coupled together to form an outer annular ring extending around the inner annular ring formed by the circumferentially adjacent inner platforms 52 of each stator vane 26. The at least one airfoil 56 may extend between the two annular rings formed by the platforms 52, 54. The turbine segment 22 may also include a shroud section 58, which may be disposed downstream of the outer platform 54 to guide the combustion gases 42 flowing through the stator vane 26 to the rotor blades 28.

[0043] Structures or components disposed along the flow path of the combustion gases 42 may be referred to as hot gas path components. In one example, the hot gas path components may be stator guide vanes 26 and / or rotor blades 28. In some embodiments, to cool the hot gas path components, cooling features such as impingement sleeves, cooling ducts, cooling holes, etc. may be disposed within the hot gas path components, as indicated by dashed line 78. For example, cooling air may be passed from the compressor segment 12 or elsewhere as indicated by arrow 79 and directed through cooling features as indicated by arrow 81. Although in Figure 2 This cooling flow is shown with respect to the stator vanes 2 , but it should be understood that similar cooling flows may be used for the rotor blades 28 .

[0044] Figure 3 An exploded view of a stator guide vane assembly 200 is shown, which may represent the stator guide vanes 19 in the compressor segment 12 and / or the stator guide vanes 26 in the turbine segment 22. However, in an exemplary embodiment, the stator guide vane assembly 200 may be the stator guide vanes 26 in the turbine segment 22. Figure 3 As shown, the stator guide vane assembly 200 includes a platform 201 and an airfoil section 206. For example, the stator guide vane assembly 200 may include an inner platform 202, an outer platform 204, and an airfoil section 206, which are separated from each other along the axial centerline 55 of the stator guide vane assembly 200 to illustrate various features of the stator guide vane assembly 200 that cannot otherwise be seen when the assembly is constructed. When the stator guide vane assembly 200 is installed in the turbine segment 22, the axial centerline 55 may be generally parallel to the radial direction of the gas turbine 10. The airfoil section 206 may include an airfoil 56 that generally defines an aerodynamic shape or profile. For example, the airfoil 56 may include a leading edge 60 that engages the flow of combustion gases and a sidewall that guides the combustion gases to a trailing edge 62 along the airfoil 56. For example, the airfoil 56 may include a pressure sidewall 64 and a suction sidewall 66 that each extend from the leading edge 60 to the trailing edge 62. Additionally, the airfoil 56 may extend radially between a base 68 and a tip 70 .

[0045] In an exemplary embodiment, the inner platform 202, the airfoil 56, and the outer platform 204 may be separate components (e.g., manufactured as separate components) coupled to each other via a mechanical retention device 210. In an exemplary embodiment, the mechanical retention device 210 may include one or more retention pins 212 extending through a boss 216 of the platform 201 and the airfoil segment 206. In some embodiments, the one or more retention pins 212 may include a leading edge pin 213 and a trailing edge pin 214.

[0046] While the exemplary embodiment of the present stator guide vane assembly 200 includes a mechanical retention device 210 in the form of one or more retention pins 212, which advantageously provides ease of assembly, it should be understood that other mechanical retention devices may be used without departing from the scope of the present disclosure. For example, in other embodiments, the mechanical retention device 210 may include one or more shear keys, snap rings, machined tongues and grooves, etc. The present disclosure should not be limited to embodiments having one or more retention pins as the mechanical retention device unless explicitly stated in the claims.

[0047] One or more retaining pins 212 can be solid (e.g., not hollow or including voids), cylindrical pins. With this shape, each of the retaining pins 212 can extend linearly along the centerline 215, and each of the retaining pins 212 can have a circular cross-sectional shape. However, in other embodiments, the retaining pins 212 can have other cross-sectional shapes, and the present disclosure should not be limited to any particular shape unless explicitly stated in the claims. In various embodiments, one or more retaining pins 212 can be formed of a metal (such as a nickel superalloy or other metal or other metal alloy). However, in other embodiments, the retaining pins 212 can be formed of another material (such as ceramic), and the pins of the present disclosure should not be limited to any particular material unless explicitly stated in the claims.

[0048] For example, in a particular embodiment, the inner platform 202, the airfoil 56, and the outer platform 204 may each be additively manufactured (e.g., 3D printed) separately and then joined to each other via a mechanical retaining device 210 and / or via one or more metallurgical joints. In various embodiments, the metallurgical joint may include a welded joint, a brazed joint, a sintered joint, etc. In an exemplary embodiment, the metallurgical joint may be a brazed joint. Forming the stator vane assembly 200 as three separate components advantageously increases the repairability of the stator vane assembly 200. For example, if a portion of the airfoil segment 206 is damaged, the entire stator vane assembly 200 will not need to be replaced. Instead, the mechanical connection can be released (e.g., by removing one or more pins 212) and the metallurgical connection can be released (e.g., via reheating and melting the components) to separate the airfoil segment 206 from the platform 202, 204, and a new airfoil segment 206 can be used or the old airfoil can be repaired.

[0049] Additionally, where additive manufacturing is used to produce some or all of the stator vane assembly 200, the build (i.e., printing) time of the airfoil segment 206 as a separate component from the inner platform 202 and the outer platform 204 is significantly shorter than the build time of an integral nozzle in which the inner platform 202 and the outer platform 204 are printed with the airfoil segment 206. Furthermore, forming the stator vane assembly 200 from three separate components simplifies the build process and allows different manufacturing techniques and / or different materials to be used for various components.

[0050] like Figure 3 As shown, the airfoil section 206 may include a camber axis 57 that may extend from the leading edge 60 to the trailing edge 62 and may be defined halfway between the pressure side wall 64 and the suction side wall 66 of the airfoil 56. The camber axis 57 may be curved and / or contoured to correspond to the curves of the pressure side wall 64 and the suction side wall 66. The transverse direction T may be defined orthogonally relative to the camber axis 57.

[0051] like Figure 3 As shown, the airfoil segment 206 may also include a boss 216 extending from at least one of the base 68 or the tip 70 of the airfoil 56. The boss 216 may extend outward from the airfoil 56 in both the radial direction R and the transverse direction T. For example, the stator vane assembly 200 may include an inner boss 73 extending radially inward from the airfoil 56 at the base 68 and an outer boss 75 extending radially outward from the airfoil 56 at the tip 70. Each boss 73, 75 may extend generally perpendicularly from the pressure side wall 64 and the suction side wall 66 in the transverse direction T.

[0052] Both the inner platform 202 and the outer platform 204 may define an opening 102. Bosses 216 are disposed in the openings 102 of the platforms 202, 204. The openings 102 may be sized and shaped to correspond to the respective bosses 73, 75 so that the respective bosses 73, 75 may be inserted into the openings 102 (and subsequently connected to the respective platforms 202, 204 via the mechanical retention device 208 and / or a brazed connection), thereby coupling the airfoil segment 206 to the inner platform 202 and the outer platform 204. Specifically, the inner boss 73 may be inserted into the opening 102 of the inner platform 202 (and subsequently connected to the inner platform 202), and the outer boss 75 may be inserted into the opening 102 of the outer platform 204 (and subsequently connected to the outer platform 204).

[0053] In many embodiments, in addition to or as an alternative to the mechanical retention device 208, the boss 216 of the airfoil segment 206 can be brazed to the inner platform 52 and the outer platform 54 via a metallurgical bond 211 ( Figure 6 and Fig.10). In an exemplary embodiment, the metallurgical bond 211 may be a brazed joint. In such an embodiment, the brazing material 107 may be disposed between the boss 216 and the boundary of the opening 102 (at both the inner platform 202 and the outer platform 204). The entire stator guide vane assembly 200 may then be placed in a brazing furnace to melt the brazing material 107, and then the brazing material 107 may solidify, thereby joining the inner platform 202 and the outer platform 204 to the corresponding boss 216 of the airfoil segment 206. The brazing material 107 may include copper, nickel, silver, gold, aluminum, or other suitable brazing metals.

[0054] In many embodiments, such as Figure 3 As shown, the inner platform 202 and / or the outer platform 204 include a bottom plate 53. The bottom plate 53 may extend substantially perpendicular to the airfoil 56. The bottom plate 53 of the inner platform 202 may define a radially inward flow boundary for the combustion gases in the turbine segment 22. Similarly, the bottom plate 53 of the outer platform 204 may define a radially outer flow boundary for the combustion gases in the turbine segment 22. In addition, the bottom plates 53 of the inner platform 202 and the outer platform 204 may at least partially define the corresponding openings 102. In an exemplary embodiment, one or both of the inner platform 202 and / or the outer platform 204 may include one or more protrusions 80 extending radially from the bottom plate 53. The one or more protrusions 80 may at least partially define the opening 102. In many embodiments, the boss 216 may be brazedly coupled to the one or more protrusions 80.

[0055] In some embodiments, such as Figure 3 As shown, the one or more protrusions 80 may be a single protrusion 80 that annularly surrounds the opening 102. However, in other embodiments, the one or more protrusions 80 may include a plurality of protrusions 80 that are spaced apart from each other and disposed around the opening 102 in a discontinuous manner.

[0056] In certain embodiments, the bosses 73, 216 extending from the base 68 of the airfoil 56 may extend into the opening 102 of the inner platform 202 such that the inner platform 202 surrounds the bosses 73, 216 of the airfoil 56. Specifically, the floor 53 and / or one or more protrusions 80 of the inner platform 202 may surround the bosses 73, 216 extending from the base 68 of the airfoil 56. Similarly, the bosses 75, 216 extending from the top end 70 of the airfoil 56 may extend into the opening 102 of the outer platform 204 such that the outer platform 204 surrounds the bosses 75, 216 of the airfoil 56. Specifically, the floor 53 and / or one or more protrusions 80 of the outer platform 204 may surround the bosses 75, 216 extending from the top end 70 of the airfoil 56.

[0057] In some embodiments, as shown, the boss 216 may at least partially define the cavity 92 that extends into and is further defined in the airfoil 56. The cavity 92 may be exposed through the opening 102 of the platform 54 so that air (e.g., bleed air from the compressor 14) may enter the cavity 92. In other embodiments (not shown), the boss 216 may be solid (i.e., without a void, cavity, or opening defined therein).

[0058] Reference now Figure 4 , shows a perspective view of an airfoil segment 206 according to an embodiment of the present disclosure. As shown, the airfoil segment 206 may include an airfoil 56 and at least one boss 216. The airfoil 56 may include a leading edge 60 that engages the working fluid and a trailing edge 62 opposite the leading edge 60. In addition, the airfoil 56 may include pressure side walls 64 ( Figure 3 ) and the suction sidewall 66. The airfoil 56 may extend radially between a base 68 and a tip 70. In many embodiments, the boss 216 may extend from at least one of the base 68 or the tip 70 of the airfoil 56. Specifically, in an exemplary embodiment, the boss 216 may extend from both the base 68 and the tip 70. In such an embodiment, the airfoil segment 206 may include an inner boss 73 extending radially inward from the base 68 and an outer boss 75 extending radially outward from the tip 70. The inner boss 73 and the outer boss 75 may have different radial heights and may include different features as discussed below.

[0059] In many embodiments, the boss 216 may include a shoulder 218 and a shank 220. The shoulder 218 may extend (e.g., radially) from the top end 70 of the airfoil 56 and surround the top end of the airfoil. Specifically, the outer boss 75 may include both the shoulder 218 and the shank 220, and the inner boss 73 may include only the shoulder 218 (without the shank). The shank 220 may extend radially (e.g., radially outward) from the shoulder 218. Figure 4 As shown, the shank 220 may include a shank leading edge 222, a shank trailing edge 224, a shank suction side 226, and a shank pressure side 228. The shank leading edge 222 is adjacent to the leading edge 60 of the airfoil 56, while the shank trailing edge 224 is offset from the trailing edge 62 of the airfoil 56. In addition, the shank 220 may include a solid shank tail 230 extending from the shank suction side 226 to the shank pressure side 228 adjacent to the shank trailing edge 224. The shank 220 of the boss 216 may at least partially define a cavity 92 that extends into the shoulder 218 and the airfoil 56 and is further defined therein.

[0060] In various embodiments, the shoulder 218 may include a shoulder leading edge 232, a shoulder trailing edge 234, a shoulder suction side 236, and a shoulder pressure side 238. The shoulder leading edge 232 is adjacent to the leading edge 60 of the airfoil 56 and aligned with the shank leading edge 222, while the shoulder trailing edge 234 is adjacent to the trailing edge 62 of the airfoil and offset from the shank trailing edge 224. Additionally, the shoulder 218 may include a solid shoulder tail 240. The solid shoulder tail 240 may extend downstream of both the shank trailing edge 224 and the trailing edge 62 of the airfoil 56, such that the solid shoulder tail 240 defines a bearing surface 242. When the stator vane assembly 200 is constructed, the bearing surface 242 may contact (and be brazed coupled to) the radially inner surface of the outer platform 204.

[0061] The boss 216 may have a profile that is generally similar to the airfoil 56, but the boss 216 may be larger in size than the airfoil 56. In many embodiments, the boss 216 may define one or more undercut surfaces 244 that are generally planar (e.g., flat). The undercut surfaces 244 may extend along the shank 220 and / or the shoulder 218 of the boss 216. At least one retaining pin 212 may extend through the one or more undercut surfaces 244. The undercut surfaces 244 may advantageously provide a more rigid connection between the platforms 202, 202 and the boss 216.

[0062] like Figure 4 As shown, the one or more retaining pins 212 may include a leading edge pin 213, a trailing edge pin 214, and an inner retaining pin 217. The leading edge pin 213 may extend through the outer boss 75 adjacent the leading edge 60 of the airfoil 56. The leading edge pin 213 may be disposed on an undercut surface 244 adjacent the shank leading edge 222 (e.g., along the shank suction side 226). The trailing edge pin 214 may extend through the solid shank tail 230 of the shank portion 220 adjacent the shank trailing edge 224 through the outer boss 75. The inner retaining pin 217 (or inner leading edge pin) may extend through the inner boss 73 adjacent the leading edge 60 of the airfoil 56. The inner retaining pin 217 may be disposed on the undercut surface 244.

[0063] Reference now Figures 5 to 10 , various views of a stator guide vane assembly 200 according to an exemplary embodiment of the present disclosure are shown. Specifically, Figure 5 A perspective view of an outer portion of the stator vane assembly 200 including the airfoil segment 206 and the outer platform 204 is shown. Figure 6 Shown along Figure 5 6 is a perspective cross-sectional view of the stator vane assembly 200 taken along line 6 - 6 shown in FIG. Figure 7 A plan view of the stator vane assembly 200 is shown. Figure 8 Shown along Figure 7 8 is a perspective cross-sectional view of the stator vane assembly 200 taken along line 8 - 8 shown in FIG. Fig. 9A perspective view of an interior portion of the stator vane assembly 200 including the airfoil segment 206 and the inner platform 202 is shown. Fig.10 Shown along Fig. 9 1 is a perspective cross-sectional view of the stator vane assembly 200 taken along line 10 - 10 shown in FIG.

[0064] exist Figures 5 to 10 In the embodiment, the platforms 202, 204 may each include a base plate 53 and one or more protrusions 80 extending radially from the base plate 53. The one or more protrusions 80 may be substantially perpendicular to the base plate 53. In some embodiments, such as Figures 5 to 8 As shown, the one or more protrusions 80 may include a plurality of protrusions 246 that are spaced apart from one another and disposed around the boss 216 of the airfoil segment 206. Specifically, the outer platform 204 may include a plurality of protrusions 246 that are spaced apart from one another and disposed around the shank 220 of the boss 216 such that each protrusion 246 contacts the shank 220 of the boss 216. Each protrusion 246 of the plurality of protrusions 246 may define a hole through which a corresponding retaining pin 212 extends. In other embodiments, such as Fig. 9 and Fig.10 As shown, one or more protrusions 80 may be a continuous protrusion 248 that surrounds the boss 216. Specifically, the inner platform 202 may include a continuous protrusion 248 that extends radially inward from the bottom plate 53 such that the continuous protrusion 248 contacts the inner boss 75.

[0065] The platforms 202, 204 may each include a pressure side sloping surface 250, a suction side sloping surface 252 opposite the pressure side sloping surface 250, a leading edge surface 254, and a trailing edge surface 256 opposite the leading edge surface 254. The leading edge surface 254 and the trailing edge surface 256 may each extend between the pressure side sloping surface 250 and the suction side sloping surface 252. When positioned within the gas turbine, the suction side sloping surface 252 and the pressure side sloping surface 250 may contact the adjacent stator guide vane assembly 200. The suction side sloping surface 252 and the pressure side sloping surface 250 may be substantially parallel to each other, and the leading edge surface 254 and the trailing edge surface 256 may be substantially parallel to each other.

[0066] In many embodiments, the platforms 202, 204 may each include a leading edge hook rail 258 and a trailing edge hook rail 260 extending (e.g., radially) from the base plate 53. The leading edge hook rail 258 may extend radially from the base plate 53 at or adjacent to the leading edge face 254. The trailing edge hook rail 260 may extend radially from the base plate 53 at or adjacent to the trailing edge face 256. The hook rails 258, 260 may extend generally parallel to the leading edge face 254 and the trailing edge face 256. The hook rails 258, 260 may be disposed on either side (e.g., forward and rearward) of the shank 220 of the boss 216. The hook rails 258, 260 may be attached to an adjacent shroud assembly, a casing or a stationary retaining ring of a turbine or compressor.

[0067] like Figures 5 to 10 As shown, the one or more retaining pins 212 may include a leading edge pin 213, a trailing edge pin 214, and an inner retaining pin 217. The leading edge pin 213 may extend through the outer boss 75 adjacent the leading edge 60 of the airfoil 56. The leading edge pin 213 may be disposed on an undercut surface 244, and the undercut surface 244 may be positioned on the shank suction side 226 of the shank 220. The trailing edge pin 214 may extend through the solid shank tail 230 of the shank 220 adjacent the trailing edge 62 of the airfoil 56 through the outer boss 75. The inner retaining pin 217 (or inner leading edge pin) may extend through the inner boss 73 adjacent the leading edge 60 of the airfoil 56. The inner retaining pin 217 may be disposed on the undercut surface 244.

[0068] like Figure 6 As best shown, the leading edge pin 213 may extend through a first protrusion 262 of the plurality of protrusions 246, the boss 216, and into a second protrusion 264 of the plurality of protrusions 246. The first protrusion 262 may extend from the base plate 53 and may be disposed adjacent to the leading edge hook rail 258 and / or adjacent to the leading edge 60 of the airfoil 56. The second protrusion 264 may extend from the base plate 53 and be disposed at (or adjacent to) the suction side chamfer 252. Specifically, the leading edge pin 213 may extend through the first protrusion 262, through the shank pressure side 228, across the cavity 92, through the shank suction side 226 (at the undercut surface 244), and into the second protrusion 264.

[0069] In addition, regarding the leading edge pin 213, as Figure 7 As best shown, the leading edge pin 213 may be oriented generally perpendicular to the axial direction A of the gas turbine engine 10. In other words, the leading edge pin 213 may be oriented generally perpendicular to the flow direction 268 ( Figure 5) orientation. Aerodynamic loads on the airfoil 56 generally along the flow direction 268 (and / or the axial direction A) create a build-up moment on the stator guide vane assembly 200. Thus, orienting the leading edge pin 213 perpendicular to the axial direction A and positioning the leading edge pin 213 adjacent the leading edge 60 advantageously allows the leading edge pin 213 to counteract aerodynamic loads, thereby increasing the robustness (and overall hardware life) of the stator guide vane assembly 200.

[0070] refer to Figure 7 and Figure 8 , the trailing edge pin 214 may extend through the third protrusion 266 of the plurality of protrusions 246, the solid shank 230, and into the trailing edge hook rail 260. The trailing edge pin 214 may be oriented to counteract the moment received from the leading edge pin 213. Specifically, the trailing edge pin 213 may be oriented obliquely to the axial direction A and / or the flow direction 268.

[0071] Reference now Fig. 9 and 10 , the inner retaining pin 217 (or inner leading edge pin) may extend through the inner boss 73 adjacent the leading edge 60 of the airfoil 56. However, unlike the leading edge pin 213 and the trailing edge pin 214 at the outer platform 204, the inner retaining pin 217 may not extend completely through the continuous protrusion 248 such that at least one end of the retaining pin 217 is received within the protrusion 248. For example, the inner retaining pin 217 may be installed through an opening in one side of the inner boss 73 and may extend through the inner boss 73 and extend into (but not through) the continuous protrusion 248 on the opposite side of the inner boss 73. The inner boss 73 may include a mounting hole 280 that may allow the inner retaining pin 217 to be installed in the manner depicted. The mounting hole 280 may be generally radially oriented and defined in the inner boss 73. The inner retaining pin 217 may be disposed on the undercut surface 244. The inner retaining pin 217 may be oriented generally parallel to the leading edge pin 213 (e.g., generally perpendicular to the axial direction A).

[0072] In various embodiments, the metallurgical bond 211 may be disposed between the platforms 202, 204 and the corresponding bosses 73, 75 of the airfoil section 206 and fixedly couple the platforms to the corresponding bosses of the airfoil section. In many embodiments, the metallurgical bond 211 may extend annularly around (or around) the shoulder 218 so as to couple the shoulder 218 of the bosses 73, 75 to the corresponding platforms 202, 204. In an exemplary embodiment, the metallurgical bond 211 may be a brazed joint. In such an embodiment, the brazing material 107 may be disposed between the boss 216 and the boundary of the opening 102 (at both the inner platform 202 and the outer platform 204). The entire stator guide vane assembly 200 may then be placed in a brazing furnace to melt the brazing material 107, and subsequently, the brazing material 107 may solidify, thereby joining the inner platform 202 and the outer platform 204 to the corresponding bosses 216 of the airfoil section 206. The brazing material 107 may include copper, nickel, silver, gold, aluminum, or other suitable brazing metals.

[0073] In many embodiments, such as Figure 6 As shown, the height 270 (e.g., radial height) of the metallurgical bond 211 may be equal to (such as, about 100%) or greater than (such as, greater than 200% or greater than 300%) the thickness 272 of the walls 64, 66 of the airfoil 56. Specifically, for the connection between the outer boss 75 and the outer platform 204, the height 270 of the metallurgical bond 211 may be equal to (such as, about 100%) or greater than (such as, greater than 200% or greater than 300%) the thickness 272 of the walls 64, 66 of the airfoil 56 at about 90% of the span of the airfoil 56. Similarly, for the connection between the inner boss 73 and the inner platform 202 , the height 270 of the metallurgical bond 211 may be equal to (such as, approximately 100%) or greater than (such as greater than 200% or such as greater than 300%) the thickness 272 of the walls 64 , 66 of the airfoil 56 at approximately 10% of the span of the airfoil 56 .

[0074] As used herein, “% span” may refer to a spanwise position of the airfoil 56 extending radially from the base 68 to the tip 70 of the airfoil 56. For example, 0% span may refer to the base 68 of the airfoil 56, 100% span may refer to the tip 70 of the airfoil 56, and 50% span may refer to a position midway between the base 68 and the tip 70 of the airfoil 56. The height 270 of the metallurgical bond 211 being greater than 300% of the thickness 272 of the walls 64, 66 of the airfoil 56 advantageously ensures that the metallurgical bond 211 may be stronger (e.g., in shear strength) than the walls 64, 66 of the airfoil 56 such that the walls 64, 66 will fail before the metallurgical bond 211 (if failure were to occur).

[0075] Reference now Fig.11, a perspective cross-sectional view of a stator guide vane assembly 200 is shown according to an alternative embodiment of the present disclosure, the perspective cross-sectional view depicting the connection between the inner boss 73 and the inner platform 202. Fig.11 As shown, in some embodiments, the inner retaining pin 217 can extend completely through the continuous protrusion 248 on either side, exposing both ends of the inner retaining pin 217. For example, the inner retaining pin 217 can extend through a single protrusion 248 at a first position, through the inner boss 73, and through the single protrusion 248 at a second position different from the first position.

[0076] Forming the stator vane assembly 200 as three separate components advantageously increases the repairability of the stator vane assembly 200. For example, if a portion of the airfoil segment 206 is damaged, the entire stator vane assembly 200 will not need to be replaced. Instead, the mechanical connection can be released (e.g., by removing one or more pins 212) to disconnect the airfoil segment 206 from the platform 202, 204, and a new airfoil segment 206 can be employed or the old airfoil can be repaired. Similarly, if improvements to the airfoil segment cooling scheme are developed, the improved airfoil segment can be retrofitted into an existing platform, thereby improving turbine efficiency and minimizing manufacturing costs.

[0077] This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any device or system and performing any combined method. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. If these other examples include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ substantially from the literal language of the claims, these other examples are intended to be within the scope of the claims.

[0078] Further aspects of the invention are provided by the subject matter of the following clauses (the attorney completes this section after the claims are finalized):

[0079] A stator guide vane assembly, the stator guide vane assembly comprising: a platform defining an opening; an airfoil section having an airfoil and a boss, the airfoil comprising a leading edge, a trailing edge, a suction sidewall and a pressure sidewall, the airfoil extending radially between a base and a top end, the boss extending from at least one of the base or the top end of the airfoil, the boss being disposed in the opening of the platform; and a mechanical retaining device coupling the platform to the boss of the airfoil section.

[0080] A stator vane assembly according to any preceding clause, wherein a metallurgical bond is provided between the platform and the boss of the airfoil segment and fixedly couples the platform to the boss of the airfoil segment.

[0081] A stator vane assembly according to any preceding clause, wherein the height of the metallurgical bond is greater than about 300% of the thickness of one of the pressure side wall or the suction side wall.

[0082] Stator vane assembly according to any preceding clause, wherein the mechanical retaining means comprises one or more retaining pins extending through the platform and the boss of the airfoil section.

[0083] A stator vane assembly according to any preceding clause, wherein the one or more retaining pins comprise a leading edge pin and a trailing edge pin.

[0084] A stator guide vane assembly according to any preceding clause, wherein the boss comprises a shoulder and a shank, the shoulder extending from and surrounding at least one of the base or the top end of the airfoil, the shank extending radially from the shoulder.

[0085] A stator vane assembly according to any preceding clause, wherein the shank comprises a shank leading edge, a shank trailing edge, a shank suction side and a shank pressure side, and wherein the shank comprises a solid shank tail extending from the shank suction side to the shank pressure side adjacent the trailing edge.

[0086] A stator vane assembly according to any preceding clause, wherein a leading edge pin extends through the platform, the shank pressure side and the shank suction side adjacent the leading edge, and wherein a trailing edge pin extends through the platform and the solid shank tail.

[0087] A stator vane assembly according to any preceding clause, wherein the platform comprises a base plate and one or more protrusions extending radially from the base plate, and wherein the mechanical retaining means couples one of the one or more protrusions of the platform to the boss of the airfoil section.

[0088] A stator guide vane assembly according to any preceding clause, wherein the platform comprises a pressure side chamfer, a suction side chamfer, a leading edge face and a trailing edge face, the leading edge face and the trailing edge face each extending between the pressure side chamfer and the suction side chamfer; and wherein the platform comprises a leading edge hook rail and a trailing edge hook rail extending from the base plate.

[0089] A stator guide vane assembly according to any preceding clause, wherein the mechanical retention device is a leading edge pin, which extends through a first protrusion of the one or more protrusions, the boss, and extends into a second protrusion of the one or more protrusions, and the second protrusion of the one or more protrusions is arranged at the pressure side slope.

[0090] A stator vane assembly according to any preceding clause, wherein the mechanical retention means is a trailing edge pin extending through a first of the one or more protrusions, the solid shank, and into the trailing edge hook rail.

[0091] A stator guide vane assembly according to any preceding clause, wherein the platform defining an opening is an outer platform, and the boss extending from at least one of the base or the top end of the airfoil is a first boss extending from the top end of the airfoil; and wherein the stator guide vane assembly further comprises an inner platform defining an inner platform opening, and a second boss extends from the base of the airfoil and is coupled to the inner platform by an inner retaining pin.

[0092] A turbine, the turbine defining an axial direction, a radial direction and a circumferential direction, the turbine comprising: a compressor segment; a combustion segment, the combustion segment being located downstream of the compressor segment; and a turbine segment, the turbine segment being located downstream of the combustion segment, wherein at least one of the compressor segment or the turbine segment comprises a stator guide vane assembly, the stator guide vane assembly comprising: a platform defining an opening; an airfoil section, the airfoil section having an airfoil and a boss, the airfoil comprising a leading edge, a trailing edge, a suction sidewall and a pressure sidewall, the airfoil extending radially between a base and a top end, the boss extending from at least one of the base or the top end of the airfoil, the boss being disposed in the opening of the platform; and a mechanical retaining device, the mechanical retaining device coupling the platform to the boss of the airfoil section.

[0093] A turbine according to any preceding clause, wherein a metallurgical bond is provided between the platform and the boss of the airfoil segment and fixedly couples the platform to the boss of the airfoil segment.

[0094] A turbine according to any preceding clause, wherein the mechanical retaining means comprises one or more retaining pins extending through the platform and the boss of the airfoil section.

[0095] A turbine as claimed in any preceding clause, wherein the one or more retaining pins comprise a leading edge pin and a trailing edge pin; and wherein the leading edge pin is oriented substantially perpendicular to the axial direction.

[0096] A turbine according to any preceding clause, wherein the boss comprises a shoulder and a shank, the shoulder extending from and surrounding at least one of the base or the top end of the airfoil, the shank extending radially from the shoulder and comprising a shank leading edge, a shank trailing edge, a shank suction side and a shank pressure side, and wherein the shank comprises a solid shank tail extending from the shank suction side to the shank pressure side adjacent the trailing edge.

[0097] A turbine according to any preceding clause, wherein the mechanical retention means comprises a leading edge pin and a trailing edge pin, the leading edge pin extending through the platform, the shank pressure side and the shank suction side adjacent the shank leading edge, and the trailing edge pin extending through the platform and the solid shank tail.

[0098] A turbine according to any preceding clause, wherein the platform defining an opening is an outer platform, and the boss extending from at least one of the base or the top end of the airfoil is a first boss extending from the top end of the airfoil; and wherein the stator guide vane assembly further comprises an inner platform defining an inner platform opening, and a second boss extends from the base of the airfoil and is coupled to the inner platform by an inner retaining pin.

Claims

1. A stator guide vane assembly (200), comprising: a platform (201) defining an opening (102); an airfoil section (206), the airfoil section having an airfoil (56) and a boss (216), the airfoil (56) including a leading edge (60), a trailing edge (62), a suction sidewall (66) and a pressure sidewall (64), the airfoil (56) extending radially between a base (68) and a tip (70), the boss (216) extending from one of the base (68) or the tip (70) of the airfoil (56), the boss (216) being disposed in the opening (102) of the platform (201); and A mechanical retaining device (210) couples the platform (201) to the boss (216) of the airfoil segment (206).

2. The stator guide vane assembly (200) of claim 1, wherein a metallurgical bond (211) is disposed between the platform (201) and the boss (216) of the airfoil segment (206) and fixedly couples the platform to the boss of the airfoil segment.

3. The stator vane assembly (200) of claim 2, wherein a height of the metallurgical bond (211) is greater than about 300% of a thickness of one of the pressure side wall (64) or the suction side wall (66).

4. The stator vane assembly (200) of claim 1, wherein the mechanical retention device (210) comprises one or more retention pins (212) extending through the platform and the boss of the airfoil segment.

5. The stator guide vane assembly (200) according to claim 4, wherein the one or more retaining pins (212) include a leading edge pin (213) and a trailing edge pin (214); and wherein the leading edge pin (213) is oriented perpendicular to the axial direction of the turbine (10) in which the stator guide vane assembly (200) is installed.

6. The stator guide vane assembly (200) of claim 1, wherein the boss (216) includes a shoulder (218) extending from and surrounding one of the base (68) or the top end (70) of the airfoil (56) and a shank (220) extending radially from the shoulder (218).

7. The stator guide vane assembly (200) of claim 6, wherein the shank (220) includes a shank leading edge (222), a shank trailing edge (224), a shank suction side (226), and a shank pressure side (228); and wherein the shank (220) includes a solid shank tail (230) extending from the shank suction side (226) to the shank pressure side (228) adjacent the shank trailing edge (224).

8. The stator guide vane assembly (200) of claim 7, wherein the leading edge pin (213) extends through the platform (201), the shank pressure side (228), and the shank suction side (226) adjacent the shank leading edge (222); and wherein the trailing edge pin (214) extends through the platform (201) and the solid shank tail (230).

9. The stator guide vane assembly (200) of claim 1, wherein the platform (201) comprises a base plate (53) and one or more protrusions (80) extending radially from the base plate (53); and wherein the mechanical retention device (210) couples one of the one or more protrusions (80) of the platform (201) to the boss (216) of the airfoil segment (206).

10. The stator guide vane assembly (200) of claim 9, wherein the platform (201) comprises a pressure side ramp (250), a suction side ramp (252), a leading edge surface (254), and a trailing edge surface (256), wherein the leading edge surface (254) and the trailing edge surface (256) each extend between the pressure side ramp (250) and the suction side ramp (252); and wherein the platform (201) comprises a leading edge hook rail (258) and a trailing edge hook rail (260) extending from the base plate (53).

11. The stator guide vane assembly (200) of claim 10, wherein the mechanical retention device (210) is a leading edge pin (213), the leading edge pin extending through a first protrusion (262) of the one or more protrusions (80, 246), the boss (216), and extending into a second protrusion (264) of the one or more protrusions (80, 246), the second protrusion (264) of the one or more protrusions (80, 246) being disposed at the pressure side ramp (250).

12. The stator guide vane assembly (200) of claim 10, wherein the mechanical retention device (210) is a trailing edge pin (214) extending through a first protrusion (266) of the one or more protrusions (80, 246), the solid shank (230), and into the trailing edge hook rail (260).

13. The stator guide vane assembly (200) of claim 1, wherein the platform (201) defining an opening (102) is an outer platform (204), and the boss (216) extending from one of the base (68) or the top end (70) of the airfoil (56) is a first boss extending from the top end (70) of the airfoil (56); and wherein the stator guide vane assembly (200) further includes an inner platform (202) defining an inner platform opening (102), and a second boss (216) extends from the base (68) of the airfoil (56) and is coupled to the inner platform (202) by an inner retaining pin (217).

14. A turbine (10), the turbine defining an axial direction (A), a radial direction (R) and a circumferential direction (C) relative to an axial centerline (30) of the turbine (10), the turbine (10) comprising: Compressor section (12); a combustion section (18) located downstream of the compressor section (12); and A turbine segment (22) located downstream of the combustion segment (18), wherein at least one of the compressor segment (12) or the turbine segment (22) comprises a stator guide vane assembly (200) according to any one of claims 1 to 13.

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