Attachment structure for a profile strip

Abstract

An airfoil assembly defining an axial direction, a radial direction, and a circumferential direction, and including an airfoil and an outer strip disposed on the outer end of the airfoil in the radial direction. The outer strip includes an external attachment structure configured to secure the outer strip to an external support structure on the outer side of the outer strip.

Description

[0001] Federal government-funded research

[0002] This invention was developed with government support under contract number FA8650-15-D-2501 granted by the U.S. Air Force. The U.S. government may have certain rights to this invention. Technical Field

[0003] This topic generally relates to gas turbine engines. More specifically, this topic relates to the attachment structure of airfoil strips for airfoil components used in gas turbine engines. Background Technology

[0004] Gas turbine engines include various components that are subjected to high temperatures. As an example of such components, the turbine airfoil downstream of the combustor in a gas turbine engine is subjected to extremely high temperatures.

[0005] For components subjected to such high temperatures, unconventional high-temperature composite materials, such as ceramic matrix composites (CMCs), can be used. Composite materials typically consist of a reinforcing material and a matrix material. CMCs are a type of composite material in which both the reinforcing and matrix materials are formed of ceramic. The reinforcing and matrix materials can be formed of the same type of ceramic or different types of ceramic. Components made of CMCs have higher temperature capabilities compared to typical components (such as metal parts), which can allow for improved component performance and / or improved system temperature while reducing the cooling flow to CMC components.

[0006] However, during the design and application of CMC components and surrounding components, it may be necessary to consider the differences in mechanical properties between CMC components and conventional components. Summary of the Invention

[0007] The aspects and advantages of this disclosure will be set forth in part in the description which follows, or may be apparent from the description or may be learned by practice of the disclosure.

[0008] This disclosure relates to an airfoil assembly for a turbine engine, which defines an axial direction, a radial direction and a circumferential direction.

[0009] According to one or more embodiments, an airfoil assembly defines an axial direction, a radial direction, and a circumferential direction, and includes an airfoil and an outer strip disposed on the outer end of the airfoil in the radial direction, wherein the outer strip includes an outer attachment structure configured to secure the outer strip to an outer support structure on the outside of the outer strip.

[0010] According to one or more embodiments, the airfoil and outer band are formed of or comprise ceramic matrix composites (CMCs).

[0011] According to one or more embodiments, the external attachment structure includes: a first external hook extending radially from or near a first axial end of the outer band, and a second external hook extending radially from or near a second axial end of the outer band, wherein the first and second external hooks are configured to slide onto the external support structure in a circumferential direction to removably secure the airfoil assembly to the external support structure.

[0012] According to one or more embodiments, the ends of the first outer hook and the second outer hook extend toward each other in the axial direction.

[0013] According to one or more embodiments, the external attachment structure includes: a first outer flange extending radially from or near a first axial end of the outer band, and a second outer flange extending radially from or near a second axial end of the outer band, the first outer flange defining a first opening extending in an axial direction, the second outer flange defining a second opening extending in an axial direction, and the first and second openings being configured to allow a pin to pass through a corresponding opening on the outer support structure to removably secure the airfoil assembly to the outer support structure.

[0014] According to one or more embodiments, the first outer flange is located upstream of the outer attachment structure in the axial direction relative to the second outer flange.

[0015] According to one or more embodiments, the first opening is elongated and larger in the circumferential direction than in the radial direction.

[0016] According to one or more embodiments, the airfoil assembly further includes a radially abutting surface extending from the upper surface of the outer strip, the radially abutting surface facing upstream in the axial direction, the radially abutting surface being separate from the first outer flange and the second outer flange, and the radially abutting surface being configured to abut the corresponding abutting surface of the outer support structure.

[0017] According to one or more embodiments, the first outer flange is tabular and configured to extend radially through an opening in the outer support structure.

[0018] According to one or more embodiments, the airfoil assembly further includes a tab-shaped third outer flange configured to extend radially through another opening in the outer support structure, the third outer flange being disposed adjacent to the second outer flange in the circumferential direction, and the third outer flange having a third opening configured to allow a pin to pass through to a corresponding opening on the outer support structure.

[0019] According to one or more embodiments, the upstream surfaces of the first and second outer flanges in the axial direction are configured as radial surfaces adjacent to the outer support structure.

[0020] According to one or more embodiments, the airfoil and the outer strip are formed as separate parts.

[0021] According to one or more embodiments, it further includes an inner strip disposed on the inner end of the airfoil in the radial direction, wherein the inner strip includes an inner attachment structure configured to removably secure the inner strip to an inner support structure on the inner side of the inner strip.

[0022] According to one or more embodiments, the inner attachment structure includes: a first inner hook extending radially from or near a first axial end of the inner band, and a second inner hook extending radially from or near a second axial end of the inner band, wherein the first and second inner hooks are configured to slide in a circumferential direction onto the inner support structure to removably secure the airfoil assembly to the inner support structure.

[0023] According to one or more embodiments, the inner attachment structure includes: a first inner flange extending radially from or near a first axial end of the inner band, and a second inner flange extending radially from or near a second axial end of the inner band, the first inner flange including a first opening in the axial direction, the second inner flange including a second opening in the axial direction, and the first and second openings being configured to allow a pin to pass through a corresponding opening on the inner support structure to removably secure the airfoil assembly to the inner support structure.

[0024] According to one or more embodiments, the first inner flange is located on the upstream side of the second inner flange in the axial direction.

[0025] According to one or more embodiments, the first opening is elongated and larger in the circumferential direction than in the radial direction.

[0026] According to one or more embodiments, the downstream surface of the first inner flange and the upstream surface of the second inner flange are configured as adjacent inner support structures.

[0027] According to one or more embodiments, a gas turbine engine includes an outer support structure and an airfoil assembly, the airfoil assembly defining an axial direction, a radial direction, and a circumferential direction, and including an airfoil, an outer strip disposed at an outer end of the airfoil in the radial direction, and an inner strip disposed at an inner end of the airfoil in the radial direction, the outer strip including an outer attachment structure configured to secure the outer strip to the outer side of the outer support structure, the outer strip including the attachment structure, and the attachment structure attaching the outer strip to the outer support structure.

[0028] According to one or more embodiments, a method for assembling an airfoil assembly to an outer support structure, the airfoil assembly defining an axial direction, a radial direction, and a circumferential direction, and including an airfoil, an outer strip disposed at an outer end of the airfoil in the radial direction, and an inner strip disposed at an inner end of the airfoil in the radial direction, the method comprising: attaching the outer strip to the outer support structure via an attachment structure of the outer strip, wherein attaching the outer strip to the outer support structure includes one of: sliding a first outer hook and a second outer hook extending radially from or near an axial end of the outer strip onto the outer support structure in the circumferential direction, and causing a retaining pin to pass through a first outer flange and a second outer flange extending radially from or near an axial end of the outer strip in the axial direction, and through a flange of the outer support structure.

[0029] These and other features, aspects, and advantages of this disclosure will become better understood by referring to the following description and the appended claims. The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments of the disclosure and, together with the description, serve to explain the principles of the disclosure. Attached Figure Description

[0030] The complete and feasible disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, for those skilled in the art, wherein:

[0031] Figure 1 This is a schematic diagram of a gas turbine engine according to one or more embodiments.

[0032] Figure 2 This is a perspective view of a nozzle ring of a gas turbine engine according to one or more embodiments.

[0033] Figure 3 This is a perspective view of an airfoil assembly according to one or more embodiments, with attachment structures removed in order to clearly illustrate certain aspects of the airfoil assembly.

[0034] Figure 4 This is a perspective view of an airfoil assembly according to one or more embodiments, with attachment structures removed in order to clearly illustrate certain aspects of the airfoil assembly.

[0035] Figure 5 This is an exploded perspective view of an airfoil assembly according to one or more embodiments, with attachment structures removed in order to clearly illustrate certain aspects of the airfoil assembly.

[0036] Figure 6 An airfoil assembly having attachment structures for an outer and inner band, according to one or more embodiments, is shown as viewed from a forward-facing direction.

[0037] Figure 7An airfoil assembly having attachment structures for outer and inner bands, according to one or more embodiments, is shown as viewed from the forward and radially outward directions.

[0038] Figure 8 An airfoil assembly having attachment structures for outer and inner bands, according to one or more embodiments, is shown as viewed from the rearward and radially outward directions.

[0039] Figure 9 An airfoil assembly having attachment structures for outer and inner bands, according to one or more embodiments, is shown as viewed from the rearward and radially inward directions.

[0040] Figure 10 An airfoil assembly having attachment structures for outer and inner bands, according to one or more embodiments, is shown as viewed from the forward and radially inward directions.

[0041] Figure 11A It is a cross-sectional view of the attachment structure taken in the radial direction according to one or more embodiments.

[0042] Figure 11B It is a cross-sectional view of the attachment structure taken in the radial direction according to one or more embodiments.

[0043] Figure 11C It is a cross-sectional view of the attachment structure taken in the radial direction according to one or more embodiments.

[0044] Figure 11D It is a cross-sectional view of the attachment structure taken in the radial direction according to one or more embodiments.

[0045] Figure 11E It is a cross-sectional view of the attachment structure taken in the radial direction according to one or more embodiments.

[0046] Figure 11F It is a cross-sectional view taken in the radial direction of the attachment structure according to one or more embodiments.

[0047] Figure 12 It is a cross-sectional view taken in the circumferential direction of an airfoil assembly having attachment structures for outer and inner bands, according to one or more embodiments.

[0048] Figure 13A An outer band with an attachment structure according to one or more embodiments is shown as viewed from the radial inward direction.

[0049] Figure 13B An inner band with an attachment structure according to one or more embodiments is shown as viewed from the radially outward direction.

[0050] Figure 14AA method for assembling an airfoil assembly onto an external hanger according to one or more embodiments is shown.

[0051] Figure 14B A method for assembling an airfoil assembly onto an inner hanger according to one or more embodiments is shown.

[0052] Figure 14C A method for assembling an airfoil assembly onto an external hanger according to one or more embodiments is shown.

[0053] Figure 14D A method for assembling an airfoil assembly onto an inner hanger according to one or more embodiments is shown.

[0054] Reference numerals used repeatedly in this specification and drawings are intended to indicate the same or similar features or elements of this disclosure. Detailed Implementation

[0055] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. Each example is provided to explain the present disclosure and not to limit it. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made to the present disclosure without departing from the scope or spirit of the present disclosure. For example, features shown or described as part of one embodiment may be used with another embodiment to produce yet another embodiment. Therefore, the present disclosure is intended to cover these modifications and variations that fall within the scope of the appended claims and their equivalents.

[0056] 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 superior or better than other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0057] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of individual components. As used herein, “proximity” to the axial end of a structure can be defined as a distance from the axial end within 20% of the entire axial dimension of the structure. As used herein, the term “removably” in the context of attachment and / or fastening means that a component can be removed without damaging any attached / fastened element or any element used for attachment / fastening.

[0058] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0059] Unless otherwise stated herein, the terms “connection,” “fixed,” “attached to,” etc., refer to direct connection, fixation, or attachment, as well as indirect connection, fixation, or attachment via one or more intermediate components or features.

[0060] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0061] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0062] A turbine nozzle may comprise at least three elements exposed to the gas path: an airfoil, an inner band, and an outer band. According to one or more embodiments, these three elements are formed as a single unit, for example, by casting or composite lamination. However, according to one or more embodiments, the airfoil, inner band, and outer band may be formed separately and then assembled. Forming these elements separately simplifies manufacturing, reducing costs and increasing yield. Furthermore, forming and assembling them separately can result in reduced and / or eliminated stress at the airfoil-to-band interfaces. One or more embodiments can effectively position and attach the outer and inner bands to the outer and inner hangers, respectively. Furthermore, one or more embodiments can maintain the fit, function, and position of the band separate from the airfoil.

[0063] Figure 1 This is a schematic diagram of a gas turbine engine 10 according to one or more embodiments. The gas turbine engine 10 includes a low-pressure compressor 12, a high-pressure compressor 14, and a combustor assembly 16. The gas turbine engine 10 also includes a high-pressure turbine 18 and a low-pressure turbine 20 arranged in a series axial flow relationship on respective rotors 22 and 24. The low-pressure compressor 12 and the low-pressure turbine 20 can be connected via a first shaft 26, and the high-pressure compressor 14 and the high-pressure turbine 18 can be connected via a second shaft 28.

[0064] During operation, air flows along the central axis Ax of the gas turbine engine 10. As shown, the gas turbine engine 10 defines an axial direction A extending therefrom the central axis Ax, a circumferential direction C extending around the central axis Ax, and a radial direction R extending perpendicularly outward from the central axis Ax. The low-pressure compressor 12 compresses the incoming air, and the compressed air is then supplied to the high-pressure compressor 14, which further compresses the compressed air from the low-pressure compressor 12. The air compressed by the high-pressure compressor 14 is delivered to the combustor assembly 16 for burning the compressed air. The exhaust flow from the combustor assembly 16 drives the high-pressure turbine 18 and the low-pressure turbine 20. The high-pressure turbine 18 drives the high-pressure compressor 14 via a second shaft 28, and the low-pressure turbine 20 drives the fan or low-pressure compressor 12 via a first shaft 26. The gas turbine engine 10 also includes a fan or low-pressure compressor housing 40.

[0065] Figure 2 This is a perspective view of a nozzle ring 50 according to one or more embodiments. For example, the nozzle ring 50 may be located on the high-pressure turbine 18 and / or the low-pressure turbine 20. Figure 1 (as shown in the diagram). The nozzle ring 50 is formed by one or more turbine nozzle section assemblies 100. The nozzle section assembly 100 guides the combustion gases downstream through the support rotor 22 or 24 (as shown in the diagram). Figure 1 (As shown) a radially outward-extending subsequent rotor blade row. The nozzle ring 50 and its plurality of nozzle segment assemblies 100 can facilitate the movement of rotors 22 or 24 (as shown). Figure 1 Energy is extracted (as shown in the diagram). Additionally, the nozzle ring 50 can be used in either the high-pressure compressor 14 or the low-pressure compressor 12.

[0066] The nozzle ring 50 is formed of a plurality of nozzle segment assemblies 100. Each nozzle segment assembly 100 may include at least one airfoil assembly 102, an outer hanger 300, and an inner hanger 350. In one or more embodiments, the outer hanger 300, the inner hanger 350, or both may be a continuous ring. Alternatively, the nozzle ring 50 may include outer hangers 300 for each or more of the plurality of nozzle segment assemblies 100, and the plurality of outer hangers 300 of the plurality of nozzle segment assemblies 100 may cooperate to form an outer ring 52 of the nozzle ring 50. Similarly, in one or more embodiments, the nozzle ring 50 may include inner hangers 350 for each or more of the nozzle segment assemblies 100, and the plurality of inner hangers 350 of the plurality of nozzle segment assemblies 100 may cooperate to form an inner ring 54 of the nozzle ring 50. The outer ring 52 and the inner ring 54 extend 360 degrees circumferentially about the central axis Ax of the gas turbine engine 10. Multiple airfoil assemblies 102 can be radially arranged between the outer hanger 300 of the outer ring 52 and the inner hanger 350 of the inner ring 54.

[0067] Figure 3This is a perspective view of an airfoil assembly 102 according to one or more embodiments. For clarity of certain aspects of the airfoil assembly 102, attachment structures have been removed. The airfoil assembly 102 may include: an outer strip 110 having an outwardly facing surface 112 in the radial direction R; an inner strip 160 having an inwardly facing surface 164 in the radial direction R; and at least one airfoil 200 extending between the outer strip 110 and the inner strip 160. Each airfoil assembly 102 may include one or more airfoils 200. Figure 2 As shown, in one or more embodiments, each of the plurality of airfoil assemblies 102 may be a single unit comprising a single airfoil 200 extending between an outer band 110 and an inner band 160. Alternatively, as... Figure 3 As shown, in one or more embodiments, each of the plurality of airfoil assemblies 102 may be a twin of two airfoils 200 extending between an outer strip 110 and an inner strip 160. Alternatively, as... Figure 4 As shown, in one or more embodiments, each of the plurality of airfoil assemblies 102 may be a triplet comprising three airfoils 200 extending between an outer band 110 and an inner band 160. Furthermore, in one or more embodiments, each of the airfoil assemblies 102 may include four or more airfoils 200. For example, although discussed below... Figure 5-13B The embodiments illustrate an airfoil assembly 102 having two airfoil elements 200, but the airfoil assembly 102 depicted therein may have more or fewer airfoil elements 200. Figure 5-13B The two airfoil components 200 shown are illustrated.

[0068] According to one or more embodiments, the outer strip 110, inner strip 160, and at least one airfoil 200 may comprise a material having a low coefficient of thermal expansion. In one or more embodiments, the outer strip 110, inner strip 160, and at least one airfoil 200 may be formed of or may comprise a ceramic matrix composite (CMC) material. A CMC material is a type of composite material in which both the reinforcing material and the matrix material are formed of ceramic. The reinforcing material and the matrix material may be formed of the same type of ceramic or different types of ceramic. Alternatively, the outer strip 110, inner strip 160, and at least one airfoil 200 may be formed of other materials having a low coefficient of thermal expansion.

[0069] Figure 5This is an exploded perspective view of an airfoil assembly 102 according to one or more embodiments. For clarity of certain aspects of the airfoil assembly 102, attachment structures have been removed. The outer band 110 may include: an outwardly facing surface 112, which faces outwardly in the radial direction R; an inwardly facing surface 114, which faces inwardly in the radial direction R; and one or more openings 116 extending from the outwardly facing surface 112 through the thickness of the outer band 110 to the inwardly facing surface 114. The outwardly facing surface 112 may be a surface of the outer band 110 that faces outwardly in the radial direction R away from the central axis Ax of the gas turbine engine 10. The inwardly facing surface 114 may be a surface of the outer band 110 that faces inwardly in the radial direction R toward the central axis Ax of the gas turbine engine 10. The outwardly facing surface 112 and the inwardly facing surface 114 may be curved in the circumferential direction C. Each of the openings 116 may be shaped to receive the outer end 220 of one of the airfoils 200, such that at least a portion of the outer end 220 of the airfoil 200 passes through the opening 116 and protrudes outwardly from the outward surface 112 of the outer band 110 in the radial direction R. Alternatively, the outer end 220 of the airfoil 200 may be adjacent to the inward surface 114, such that the outer end 220 has a suitable seal between them in the flow path of the outer band 110.

[0070] The outer band 110 may also have a leading edge 120 and a trailing edge 122. The leading edge 120 may be the edge of the outer band 110 facing the engine inlet in the axial direction A. The trailing edge 122 may be the edge of the outer band 110 facing the engine outlet in the axial direction A.

[0071] According to one or more embodiments, the inner strip 160 may include: an outwardly facing surface 162, which faces outwardly in the radial direction R; an inwardly facing surface 164, which faces inwardly in the radial direction R; and one or more openings 166 extending from the outwardly facing surface 162 through the thickness of the inner strip 160 to the inwardly facing surface 164. The outwardly facing surface 162 may be a surface of the inner strip 160 that faces outwardly in the radial direction R away from the central axis Ax of the gas turbine engine 10. The inwardly facing surface 164 may be a surface of the inner strip 160 that faces inwardly in the radial direction R toward the central axis Ax of the gas turbine engine 10. The outwardly facing surface 162 and the inwardly facing surface 164 may be curved in the circumferential direction. Each opening 166 in the inner band 160 may be shaped to receive an inner end 240 of one of the airfoils 200, such that at least a portion of the inner end 240 of the airfoil 200 passes through the opening 166 and protrudes inwardly from the inward-facing surface 164 of the inner band 160 in the radial direction R. Alternatively, the inner end 240 of the airfoil 200 may abut against the outward-facing surface 162, such that the inner end 240 has a suitable seal between it and the flow path of the inner band 160.

[0072] The inner band 160 may also have a leading edge 170 and a trailing edge 172. The leading edge 170 may be the edge of the inner band 160 facing axial direction A toward the engine inlet. The trailing edge 172 may be the edge of the inner band 160 facing axial direction A toward the engine outlet.

[0073] According to one or more embodiments, the airfoil 200 may be hollow or solid. If the airfoil 200 is hollow, each airfoil 200 may include an outer surface 202 and an inner surface 204. The outer surface 202 of the airfoil 200 may be the surface of the airfoil 200 facing away from the airfoil 200 and may have an airfoil shape. The general airfoil shape of the outer surface 202 of the airfoil 200 is not particularly limited, as long as each airfoil 200 includes a suction side 218 and a pressure side 219. The inner surface 204 of the airfoil 200 may be oriented inward and may define a cavity 206 extending from the outer end 220 of the airfoil 200 through the airfoil 200 to the inner end 240.

[0074] Each airfoil 200 may have a leading edge 210 oriented in the axial direction A toward the inlet of the gas turbine engine 10 and a trailing edge 212 oriented in the axial direction A toward the outlet of the gas turbine engine 10. Each airfoil 200 includes an outer end 220 and an inner end 240. The outer end 220 of the airfoil 200 may be shaped to engage with an outer band 110. For example, the outer end 220 of the airfoil 200 may be shaped such that the outer end 220 of the airfoil 200 extends through one of the openings 116 in the outer band 110 and projects outwardly from the outwardly facing surface 112 of the outer band 110 in the radial direction R. In one or more embodiments, at least a portion of the outer end 220 of the airfoil 200 may provide an abutting surface that contacts the inwardly facing surface 114 of the outer band 110 to suitably position the airfoil 200 relative to the outer band 110. The inner end 240 of the airfoil 200 may be shaped to engage with an inner band 160. For example, the inner end 240 of the airfoil 200 may be shaped such that the inner end 240 of the airfoil 200 extends through one of the openings 166 in the inner band 160 and projects inwardly from the inward facing surface 164 of the inner band 160 in the radial direction R. In one or more embodiments, at least a portion of the inner end 240 of the airfoil 200 may provide an abutting surface that contacts the outward facing surface 162 of the inner band 160 to properly position the airfoil 200 relative to the inner band 160.

[0075] Figure 6-13B An airfoil assembly 102 with attachment structures for an outer band 410 and an inner band 460, according to various embodiments, is shown. Although not explicitly stated in the text for ease of explanation... Figure 3-5 These attachment structures are shown in the diagram, but it should be understood that... Figure 6-13BThe attachment structure shown can be combined with Figure 3-5 In the airfoil assembly shown.

[0076] Figure 6-10 An airfoil assembly 102 having attachment structures for an outer band 410 and an inner band 460, according to one or more embodiments, is shown as viewed from the forward direction, the forward and radially outward direction, the rearward and radially outward direction, the rearward and radially inward direction, and the forward and radially inward direction, respectively. According to one or more embodiments, Figure 6-10 It also includes an outer hanger 500 and an inner hanger 550, with outer and inner straps 410 and 460 attached to the outer hanger 500 and inner hanger 550 via attachment structures. According to one or more embodiments, the outer hanger 500 and inner hanger 550 are examples of an outer support structure and an inner support structure, respectively. Although pins 601, 603, 605, 607 (see...) Figure 11A-11D It can be engaged with the attachment structures and corresponding attachment structures of the outer and inner hangers 500 and 550 for proper attachment, but pins 601, 603, 605, and 607 are not in... Figure 6-10 The attachment structure is shown in the diagram so that it can be clearly seen. Exemplary embodiments of pins 601, 603, 605, and 607 are shown in... Figures 11A to 11F It is depicted in the text and described below.

[0077] General reference Figure 6-10 The airfoil assembly 102 includes an airfoil 200 extending between an outer band 410 and an inner band 460. More specifically, the airfoil 200 extends between a body 440 of the outer band 410 and a body 490 of the inner band 460. According to one or more embodiments, the airfoil 200 is formed separately from the outer band 410 and the inner band 460, and thus assembled together, for example, as... Figure 3-5 As shown. Alternatively, the airfoil 200 may be integrally formed with the outer strip 410 and the inner strip 460. According to one or more embodiments, the airfoil 200, the outer strip 410 and / or the inner strip 460 may be formed of or may include a CMC material.

[0078] Special Reference Figure 6 and Figure 7The outer strip 410 is disposed on the outer end of the airfoil 200 in the radial direction R. According to one or more embodiments, the first attachment tab 420 extends outwardly from the front end portion of the body 440 of the outer strip 410 in the radial direction R. The front end portion of the body 440 may be located at the upstream end of the body 440 in the axial direction A. The first attachment tab 420 may extend from the leading edge of the body 440 or may extend slightly downstream of the leading edge of the body 440. The base of the first attachment tab 420 may gradually taper from the front end portion of the body 440. Furthermore, the corner of the outer end of the first attachment tab 420 in the radial direction R may also be tapered. The first attachment tab 420 is tab-shaped and is an example of an outer flange.

[0079] According to one or more embodiments, the first attachment tab 420 includes an axial opening 425 formed therethrough. That is, the axial opening 425 is formed as a through-hole extending in the axial direction A through the first attachment tab 420. Figure 6-7 As shown, the axial opening 425 can be slot-shaped, extending elliptically in the circumferential direction C. As will be explained below, this configuration can allow certain benefits related to the relative thermal expansion between components.

[0080] However, it should be understood that, although Figure 6-7 The axial opening 425 is shown as a slotted ellipse, but the axial opening 425 can take other shapes. For example, the axial opening 425 can alternatively be circular or rectangular.

[0081] According to one or more embodiments, the second attachment tab 430 and the third attachment tab 431 extend outwardly from the rear end portion of the body 440 of the outer band 410 in the radial direction R. The second attachment tab 430 and the third attachment tab 431 may be spaced apart in the circumferential direction C. The rear end portion of the body 440 may be located downstream of the body 440 in the axial direction A. The second and third attachment tabs 430, 431 may extend from the rear edge of the body 440, or may extend slightly upstream of the rear edge of the body 440. The bases of the second attachment tab 430 and the third attachment tab 431 may gradually taper from the rear end portion of the body 440. Furthermore, the corners at the outer ends of the second attachment tab 430 and the third attachment tab 431 in the radial direction R may also be tapered. The second and third attachment tabs 430, 431 are tab-shaped and are examples of outer flanges.

[0082] According to one or more embodiments, the second attachment tab 430 includes an axial opening 435 formed therethrough, and the third attachment tab 431 includes an axial opening 436 formed therethrough (see especially...). Figure 7That is, the axial opening 435 is formed as a through hole extending in the axial direction A through the second attachment tab 430, and the axial opening 436 is formed as a through hole extending in the axial direction A through the third attachment tab 431. Figure 6-7 As shown, the axial openings 435 and 436 can, for example, be elongated in an elliptical shape as shown.

[0083] However, it should be understood that, although Figure 6-7 The axial openings 435 and 436 are shown as elliptical grooves extending in the circumferential direction C, but the axial openings 435 and 436 can take other shapes. For example, the axial openings 435 and 436 can alternatively be formed as circles or rectangles and extend in the circumferential direction C. Alternatively, the axial opening 436 can be circular while the axial opening 435 is elongated, or the axial opening 435 can be circular while the axial opening 436 is elongated.

[0084] According to one or more embodiments, a radially abutting surface 442 is disposed on the rear end portion of the body 440. The radially abutting surface 442 is formed as a rearward-facing surface in the axial direction A and can extend continuously from one circumferential end of the body 440 to the other circumferential end of the body 440. According to one or more embodiments, second and third attachment tabs 430, 431 can be positioned at or upstream of the radially abutting surface 442. According to one or more embodiments, the body 440 can extend further downstream from the radially abutting surface 442 in the axial direction A.

[0085] An outer band 410 is disposed on the inner side of the outer hanger 500. According to one or more embodiments, the outer hanger 500 may be formed of metal. The outer hanger 500 includes a body 540, a first radial wall 520, and a second radial wall 530. The first and second radial walls 520 and 530 are examples of flanges of the outer hanger 500.

[0086] The first radial wall 520 may extend outward in the radial direction R from the front end portion of the body 540 of the outer hanger 500. The front end portion of the body 540 may be located upstream of the body 540 in the axial direction A. The first radial wall 520 may extend from the leading edge of the body 540, or may extend slightly downstream of the leading edge of the body 540.

[0087] Now for special reference Figure 8 According to one or more embodiments, the first radial wall 520 includes an axial opening 525 formed therethrough. That is, the axial opening 525 is formed as a through-hole extending through the first radial wall 520 in the axial direction A. Figure 8 As shown, the axial opening 525 can be circular.

[0088] However, it should be understood that, although Figure 8The axial opening 525 is shown as circular, but it can take other shapes. For example, the axial opening 525 can alternatively be formed as a slotted ellipse or rectangle extending in the circumferential direction C. According to one or more embodiments, the first radial wall 520 includes additional axial openings circumferentially spaced from the axial opening 525, which can be used as alternative attachment sites for the first attachment tab 420 or for attachment to other elements. For example, additional attachment tabs (not shown) can be attached to the additional axial openings of the first radial wall 520.

[0089] According to one or more embodiments, the body 540 terminates at the first radial wall 520 in the forward axial direction A. Alternatively, the body 540 may extend further upstream from the first radial wall 520 in the axial direction A.

[0090] The second radial wall 530 may extend outward in the radial direction R from the rear end portion of the body 540 of the outer hanger 500. The rear end portion of the body 540 may be located at the downstream end of the body 540 in the axial direction A. The second radial wall 530 may extend from the rear edge of the body 540, or may extend slightly upstream of the rear edge of the body 540.

[0091] According to one or more embodiments, the second radial wall 530 includes axial openings 535, 536 formed therethrough. That is, the axial openings 535, 536 are formed as through holes extending axially through the second radial wall 530. Figure 8 As shown, the axial openings 535 and 536 can be circular.

[0092] However, it should be understood that, although Figure 8 The axial openings 535 and 536 are shown as circular, but they can take other shapes. For example, the axial openings 535 and 536 can alternatively be formed as slotted ellipses or rectangles extending in the circumferential direction C. According to one or more embodiments, the second radial wall 530 includes additional axial openings circumferentially spaced from the axial openings 535 and 536, which can be used for attachment to other elements.

[0093] According to one or more embodiments, a radially abutting surface 532 is disposed on the rear end portion of the body 540 of the outer hanger 500. The radially abutting surface 532 is formed as a forward-facing surface in the axial direction A and can extend from one circumferential end of the outer hanger 500 to the other circumferential end of the outer hanger 500. According to one or more embodiments, the radially abutting surface 532 can be a forward-facing surface of a second radial wall 530. According to one or more embodiments, the body 540 terminates at the second radial wall 530. Alternatively, the body 540 can extend further downstream from the second radial wall 530 in the axial direction A.

[0094] Briefly return to reference Figure 6 and Figure 7 The body 540 may further include radial openings 543, 544 extending therethrough. The radial openings 543, 544 are formed as through-holes extending in the radial direction R through the second radial wall 530. The radial openings 543, 544 are shaped and spaced such that the second and third attachment tabs 430, 431 can pass through them in the radial direction R. According to one or more embodiments, the radial openings 543, 544 are immediately in front of the second radial wall 530. According to one or more embodiments, the radial openings 543, 544 are rectangular. The radial openings 543, 544 are examples of orifices in the outer hanger 500.

[0095] like Figure 6-10 As shown, during assembly, the outer strap 410 is typically positioned on the inner side of the outer hanger 500 in the radial direction R. According to one or more embodiments, the outer strap 410 and the outer hanger 500 are spaced apart in the radial direction R, such that first, second, and third attachment tabs 420, 430, 431 support the radial load between the outer strap 410 and the outer hanger 500. Alternatively, the inner radial surface of the body 540 of the outer hanger 500 may at least partially abut the outer radial surface of the body 440 of the outer strap 410.

[0096] According to one or more embodiments, the radially abutting surface 442 of the outer band 410 abuts the radially abutting surface 532 of the outer hanger 500. According to one or more embodiments, the axial contact between the radially abutting surface 442 and the radially abutting surface 532 may be the only axial contact between the outer band 410 and the outer hanger 500.

[0097] According to one or more embodiments, a seal may be disposed between the radially abutting surface 442 and the outer band 410 of the radially abutting surface 532 of the outer hanger 500 to prevent airflow leakage. For example, the seal may be a line seal extending in the radial direction.

[0098] According to one or more embodiments, in addition to the axial contact between the radially adjacent surfaces 442 and 532, the first attachment tab 420 may be disposed on the front side of the first radial wall 520 in the axial direction A, such that the axial rear surface of the first attachment tab 420 abuts the axial front surface of the first radial wall 520.

[0099] According to one or more embodiments, the axial opening 425 of the first attachment tab 420 is aligned with the axial opening 525 of the first radial wall 520.

[0100] According to one or more embodiments, the second attachment tab 430 extends radially through the radial opening 543, such that the second attachment tab 430 is disposed on the front side of the second radial wall 530 in the axial direction A.

[0101] According to one or more embodiments, in addition to the axial contact between the radially abutting surfaces 442 and 532 and / or the axial contact between the first attaching tab 420 and the first radial wall 520, the axial rear surface of the second attaching tab 430 may abut the axial front surface of the second radial wall 530. According to one or more embodiments, the axial opening 435 of the second attaching tab 430 is aligned with the axial opening 535 of the second radial wall 530.

[0102] According to one or more embodiments, the third attachment tab 431 extends radially through the radial opening 544, such that the third attachment tab 431 is disposed on the front side of the second radial wall 530 in the axial direction A.

[0103] According to one or more embodiments, in addition to the axial contact between the radially adjacent surfaces 442 and 532, the axial contact between the first attachment tab 420 and the first radial wall 520, and / or the axial contact between the second attachment tab 430 and the second radial wall 530, the axial rear surface of the third attachment tab 431 may abut the axial front surface of the second radial wall 530, wherein the axial opening 436 of the third attachment tab 431 is aligned with the axial opening 536 of the second radial wall 530.

[0104] The inner band 460 is disposed on the inner end of the airfoil 200 in the radial direction R. According to one or more embodiments, a first radial wall 470 extends inwardly from the front end portion of the body 490 of the inner band 460 in the radial direction R. The front end portion of the body 490 may be located at the upstream end of the body 490 in the axial direction A. The first radial wall 470 may extend from the leading edge of the body 490, or may extend slightly downstream of the leading edge of the body 490. The first radial wall 470 is an example of an inner flange.

[0105] According to one or more embodiments, the first radial wall 470 includes an axial opening 475 formed therethrough. That is, the axial opening 475 is formed as a through-hole extending through the first radial wall 470 in the axial direction A. Figure 6-7 As shown in Figure 10, the axial opening 475 can be a groove shape that extends in the circumferential direction C. Although Figure 6-7 The axial opening 475 in 10 is shown as a slotted ellipse, but the axial opening 475 can take other shapes. For example, the axial opening 475 can alternatively be circular or rectangular.

[0106] According to one or more embodiments, a second radial wall 480 extends inwardly from the rear end portion of the body 490 of the inner band 460 in the radial direction R. The rear end portion of the body 490 may be located at the downstream end of the body 490 in the axial direction A. The second radial wall 480 may extend from the rear edge of the body 490, or may extend slightly upstream of the rear edge of the body 490. According to one or more embodiments, the second radial wall 480 may include axial openings 485, 486 formed therethrough. The second radial wall 480 is an example of an inner flange.

[0107] An inner band 460 is disposed on the outer side of the inner hanger 550. According to one or more embodiments, the inner hanger 550 may be formed of metal. The inner hanger 550 includes a body 590, a first radial wall 570, and a second radial wall 580. The first and second radial walls 570 and 580 are examples of flanges of the inner hanger 550.

[0108] The first radial wall 570 may extend inwardly from the front end portion of the body 590 of the inner hanger 550 in the radial direction R. The front end portion of the body 590 may be located at the upstream end of the body 590 in the axial direction A. The first radial wall 570 may extend from the leading edge of the body 590, or may extend slightly downstream of the leading edge of the body 590.

[0109] According to one or more embodiments, the first radial wall 570 includes an axial opening 575 formed therethrough. That is, the axial opening 575 is formed as a through-hole extending through the first radial wall 570 in the axial direction A. Figure 9 As shown, the axial opening 575 can be circular. Although Figure 9 The axial opening 575 is shown as circular, but it can take other shapes. For example, the axial opening 575 can alternatively be shaped as a slotted ellipse or rectangle extending in the circumferential direction C. Although not shown, according to one or more embodiments, the first radial wall 570 may include additional axial openings circumferentially spaced from the axial opening 575, which may serve as alternative attachment sites for the first radial wall 470 or may be used for attachment to other elements.

[0110] According to one or more embodiments, the body 590 terminates at the first radial wall 570 in the forward axial direction A. Alternatively, the body 590 may extend further upstream from the first radial wall 570 in the axial direction A.

[0111] The second radial wall 580 may extend inwardly from the rear end portion of the body 590 of the inner hanger 550 in the radial direction R. The rear end portion of the body 590 may be located at the downstream end of the body 590 in the axial direction A. The second radial wall 580 may extend from the rear edge of the body 590, or may extend slightly upstream of the rear edge of the body 590.

[0112] According to one or more embodiments, the second radial wall 580 may include an axial opening for attaching the inner band 460, and may further include additional axial openings circumferentially spaced from the axial opening for attachment to other elements. For example, the second radial wall 580 may include axial openings 585, 586 formed as blind holes on its front surface. That is, as Figure 11E-11F As shown, the axial openings 585 and 586 may not extend continuously through the radial wall 580 to its rear surface. Alternatively, the axial openings 585 and 586 may be formed as through holes.

[0113] According to one or more embodiments, the body 590 terminates at the second radial wall 580. Alternatively, the body 590 may extend further downstream from the second radial wall 580 in the axial direction A.

[0114] like Figure 6-10 As shown, during assembly, the inner belt 460 is positioned on the outer side of the inner hanger 550 in the radial direction R. According to one or more embodiments, the inner belt 460 and the inner hanger 550 are spaced apart in the radial direction R, such that a first radial wall 470 supports the radial load between the inner belt 460 and the inner hanger 550. Alternatively, the outer radial surface of the body 590 of the inner hanger 550 may at least partially abut the inner radial surface of the body 490 of the inner belt 460.

[0115] According to one or more embodiments, a first radial wall 470 is disposed on the front side of the first radial wall 570 in the axial direction A, such that the axial rear surface of the first radial wall 470 abuts the axial front surface of the first radial wall 570, wherein the axial opening 475 of the first radial wall 470 is aligned with the axial opening 575 of the first radial wall 570.

[0116] According to one or more embodiments, a second radial wall 480 is disposed on the rear side of the second radial wall 580 in the axial direction A, and the axial front surface of the second radial wall 480 abuts the axial rear surface of the second radial wall 580. Although not shown, the second radial wall 480 of the inner band and the second radial wall 580 of the inner hanger may include axial openings, and in this case, the axial opening of the second radial wall 480 may be aligned with the axial opening of the second radial wall 580.

[0117] Figure 11AThis is a cross-sectional view taken in the radial direction of an attachment structure for attaching the first attachment tab 420 of the outer strap 410 to the first radial wall 520 of the outer hanger 500, according to one or more embodiments. During assembly, the axial opening 425 of the first attachment tab 420 of the outer strap 410 is axially aligned with the axial opening 525 of the first radial wall 520 of the outer hanger 500. This alignment of the axial openings 425, 525 allows the pin 601 to pass through them. For example, Figure 11A The pin 601 is shown to be a nut and bolt structure.

[0118] However, in other exemplary embodiments, any other suitable structure may be employed that extends through the axial openings 425, 525 to allow attachment of the first attachment tab 420 to the first radial wall 520. For example, the pin 601 may be any elongated member, such as an elongated fastener, an elongated rotatable fastener, or an elongated permanent fastening device (e.g., welded together, to one of the components, etc.). The diameter of the pin 601 may correspond to the inner diameter of the axial opening 525 of the first radial wall 520 and the height of the axial opening 425 of the first attachment tab 420.

[0119] As described above, the outer belt 410 and the outer hanger 500 can be formed of different materials. For example, the outer belt 410 can be formed of or include CMC material, and the outer hanger 500 can be formed of metal. This can result in different rates of thermal expansion between the outer belt 410 and the outer hanger 500. For example, when the outer hanger 500 and the outer belt 410 are exposed to heat during engine operation, the outer hanger 500 can expand faster than the outer belt 410.

[0120] However, the axial opening 425 of the first attachment tab 420 can be as follows: Figure 11A As shown, the axial opening 425 elongates in the circumferential direction C, therefore, the circumferential dimension of the axial opening 425 can be significantly larger than the diameter of the pin 601 (e.g., at least 10%, at least 20%, at least 50%, or up to 500%). Thus, if one of the outer strap 410 and the outer hanger 500 expands faster than the other, the pin 601 can be displaced within the elongated axial opening 425, thereby allowing the first attachment tab 420 to be displaced relative to the first radial wall 520 in the circumferential direction C. This displacement between the first attachment tab 420 and the first radial wall 520 prevents stress that may occur due to different rates of expansion.

[0121] Figure 11BThis is a cross-sectional view taken in the radial direction of an attachment structure for attaching the first radial wall 470 of the inner strap 460 to the first radial wall 570 of the inner hanger 550, according to one or more embodiments. During assembly, the axial opening 475 of the first radial wall 470 of the inner strap 460 is axially aligned with the axial opening 575 of the first radial wall 570 of the inner hanger 550. This alignment of the axial openings 475 and 575 allows the pin 603 to pass through them. For example, Figure 11B The pin 603 is shown as a nut and bolt configuration. However, other suitable configurations can be employed that pass through axial openings 475, 575 to allow attachment of the first radial wall 470 to the first radial wall 570. For example, the pin 601 can be any elongated member, such as an elongated fastener, an elongated rotatable fastener, or an elongated permanent fastener (e.g., welded together, to one of the components, etc.). The diameter of the pin 603 can correspond to the inner diameter of the axial opening 575 of the first radial wall 570 and the height of the axial opening 475 of the first radial wall 470.

[0122] As described above, the inner belt 460 and the inner hanger 550 can be formed of different materials. For example, the inner belt 460 can be formed of or include CMC material, and the inner hanger 550 can be formed of metal. This may result in different rates of thermal expansion between the inner belt 460 and the inner hanger 550. For example, when the inner hanger 550 and the inner belt 460 are exposed to heat during engine operation, the inner hanger 550 may expand faster than the inner belt 460.

[0123] However, the axial opening 475 of the first radial wall 470 can be as follows: Figure 11B As shown, the axial opening 475 elongates in the circumferential direction C, therefore, the circumferential dimension of the axial opening 475 can be significantly larger than the diameter of the pin 603. Thus, if one of the inner band 460 and the inner hanger 550 expands faster than the other, the pin 603 can be displaced within the elongated axial opening 475, thereby allowing the first radial wall 470 to be displaced relative to the first radial wall 570 in the circumferential direction C. This displacement between the first radial wall 470 and the first radial wall 570 prevents stress that may occur due to their different rates of expansion.

[0124] Figure 11C This is a cross-sectional view taken in the radial direction of an attachment structure for attaching the second attachment tab 430 of the outer strap 410 to the second radial wall 530 of the outer hanger 500, according to one or more embodiments. During assembly, the axial opening 435 of the second attachment tab 430 of the outer strap 410 is axially aligned with the axial opening 535 of the second radial wall 530 of the outer hanger 500. This alignment of the axial openings 435, 535 allows the pin 605 to pass through them. For example, Figure 11CThe pin 605 is shown as a nut and bolt configuration. However, other suitable configurations can be employed, passing through axial openings 435, 535 to allow attachment of the second attachment tab 430 to the second radial wall 530. For example, the pin 601 can be any elongated member, such as an elongated fastener, an elongated rotatable fastener, or an elongated permanent fastener (e.g., welded together, to one of the components, etc.). The diameter of the pin 605 can correspond to the inner diameter of the axial opening 535 of the second radial wall 530 and the height of the axial opening 435 of the second attachment tab 430.

[0125] Figure 11D This is a cross-sectional view taken in the radial direction of an attachment structure for attaching the third attachment tab 431 of the outer strap 410 to the second radial wall 530 of the outer hanger 500, according to one or more embodiments. During assembly, the axial opening 436 of the third attachment tab 431 of the outer strap 410 is axially aligned with the axial opening 536 of the second radial wall 530 of the outer hanger 500. This alignment of the axial openings 436, 536 allows the pin 607 to pass through them. For example, Figure 11D The pin 607 is shown as a nut and bolt configuration. However, other suitable configurations can be employed, passing through axial openings 436, 536 to allow attachment of the third attachment tab 431 to the second radial wall 530. For example, the pin 601 can be any elongated member, such as an elongated fastener, an elongated rotatable fastener, or an elongated permanent fastener (e.g., welded together, to one of the components, etc.). The diameter of the pin 607 can correspond to the inner diameter of the axial opening 536 of the second radial wall 531 and the height of the axial opening 436 of the third attachment tab 431.

[0126] Figure 11E-11F This is a cross-sectional view taken in the radial direction of an attachment structure for attaching the second radial wall 480 of the inner band 460 to the second radial wall 580 of the inner hanger 550, according to one or more embodiments. During assembly, the axial openings 485, 486 of the second radial wall 480 of the inner band 460 are axially aligned with the axial openings 585, 586 of the second radial wall 580 of the inner hanger 550. This alignment of the axial openings 485, 486, 585, 586 allows pins 608, 609 to pass through them. For example, Figure 11E and 11FPins 608 and 609 are shown as nut and bolt structures. However, other suitable structures can be employed to allow attachment of the second radial wall 480 to the second radial wall 580 through axial openings 485, 486, 585, 586. For example, pin 601 can be any elongated member, such as an elongated fastener, an elongated rotatable fastener, or an elongated permanent fastener (e.g., welded together, to one of the components, etc.). The diameters of pins 608 and 609 can correspond to the inner diameters of the axial openings 585 and 586 of the second radial wall 580 and the heights of the axial openings 485 and 486 of the second radial wall 480.

[0127] During operation, axial airflow can abut the front surface of airfoil 200 to generate a rearward axial force on airfoil 200 that is transmitted to outer and inner belts 410, 460. Using outer belt 410, the rearward axial force can be transmitted from the radially abutting surface 442 of body 440 to the corresponding radially abutting surface 532 of second radial wall 530. Alternatively or additionally, the rearward axial force can be transmitted from the rear surface of first attachment tab 420 to the front surface of first radial wall 520, and from the rear surfaces of second and third attachment tabs 430, 431 to the front surface of second radial wall 530. Thus, the rearward axial force is transmitted from outer belt 410 to outer hanger 500, while the first, second, and third attachment tabs 420, 430, 431 secure outer belt 410 to outer hanger 500. Using inner belt 460, the rearward axial force can be transmitted from the rear surface of first radial wall 470 to the front surface of first radial wall 570. Therefore, the rearward axial force can be transmitted from the inner band 460 to the inner hanger 550, and the first radial wall 470 secures the inner band 460 to the inner hanger 550. Furthermore, although not shown, additional attachment structures can also attach the outer band 410 to the outer hanger 500 and the inner band 460 to the inner hanger 550. Alternatively, the rearward axial force from the airfoil load can be transmitted directly to the outer hanger 500 and inner hanger 550 via, or instead of, different attachment features (not shown) of the outer band 410 and inner band 460.

[0128] Additionally, according to one or more embodiments, a seal may be disposed between the front surface of the second radial wall 480 of the inner band and the rear surface of the second radial wall 580 of the inner hanger to prevent airflow leakage therebetween. Alternatively or additionally, a seal may be disposed between the rear surface of the first radial wall 470 and the front surface of the first radial wall 570. For example, the seal may be a line seal extending in the circumferential direction C.

[0129] Figure 12 It is a cross-sectional view taken in the circumferential direction C of an airfoil assembly 102 having attachment structures for an outer band 710 and an inner band 760, according to one or more embodiments. Figure 13AAn outer band 710 with an attachment structure according to one or more embodiments is shown as viewed from the radial inward direction. Figure 13B An inner band with an attachment structure according to one or more embodiments is shown as viewed from the radially outward direction.

[0130] The attachment structure for the outer strap 710 is in the form of first, second, third, and fourth hooks 711, 713, 715, and 717. According to one or more embodiments, the hook can be defined as an element shaped with a curved or bent portion configured to secure the structure therein. Figure 12 and 13A As shown, each of the first, second, third, and fourth hooks 711, 713, 715, and 717 extends radially away from the airfoil 200 and toward the outer hanger 500. The first hook 711 and the third hook 715 are located at opposite circumferential ends of the downstream axial end of the outer belt 710, and the second hook 713 and the fourth hook 717 are located at opposite circumferential ends of the upstream axial end of the outer belt 710. The first and third hooks 711 and 715 slide onto the axial flange 911 at the downstream end of the outer hanger 500, and the second and fourth hooks 713 and 717 slide onto the axial flange 913 at the upstream end of the outer hanger 500. The end of each of the first, second, third, and fourth hooks 711, 713, 715, and 717 may abut against the radial wall of the outer hanger 500. The ends of the first and second hooks 711 and 713 can extend toward each other in the axial direction A, and the ends of the third and fourth hooks 715 and 717 can extend toward each other in the axial direction A.

[0131] The attachment structures used for the internal 760 are in the form of hooks 761, 763, 765, and 767, namely the first, second, third, and fourth hooks. For example... Figure 12 and 13B As shown, each of the first, second, third, and fourth hooks 761, 763, 765, and 767 extends radially away from the airfoil 200 and toward the inner hanger 500. The first hook 761 and the third hook 765 are located at opposite circumferential ends of the downstream axial end of the inner belt 760, and the second hook 763 and the fourth hook 767 are located at opposite circumferential ends of the upstream axial end of the inner belt 760. The first and third hooks 761 and 765 slide onto the axial flange 961 at the downstream end of the inner hanger 550, and the second and fourth hooks 763 and 767 slide onto the axial flange 963 at the upstream end of the inner hanger 550. The end of each of the first, second, third, and fourth hooks 761, 763, 765, and 767 may abut against the radial wall of the inner hanger 550. The ends of the first and second hooks 761 and 763 can extend toward each other in the axial direction A, and the ends of the third and fourth hooks 765 and 767 can extend toward each other in the axial direction A.

[0132] Once the first, second, third, and fourth hooks 711, 713, 715, and 717 are secured to the axial flanges 911 and 913 of the outer hanger 500, and the first, second, third, and fourth hooks 761, 763, 765, and 767 are secured to the axial flanges 961 and 963 of the inner hanger 550, the outer belt 710 and the inner belt 760, along with the airfoil 200 extending therebetween, are removably attached to the outer hanger 500 and the inner hanger 550.

[0133] Figure 14A A method 800 for assembling an airfoil assembly 102 onto an outer hanger 500 according to one or more embodiments is illustrated. Method 800 removably attaches an outer strap 710 to the outer hanger 500 via first, second, third, and fourth hooks 711, 713, 715, 717. Method 800 includes forming a plurality of outer straps 710 at S801. According to one or more embodiments, the outer straps 710 may be formed of or comprise CMC material. Method 800 also includes, at S802, sliding the first, second, third, and fourth hooks 711, 713, 715, 717, which extend radially in the circumferential direction C from or near the axial end of each outer strap 710, onto the outer hanger 500.

[0134] Figure 14B A method 810 for assembling an airfoil assembly 102 onto an inner hanger 550 according to one or more embodiments is illustrated. Method 810 removably attaches an inner strip 760 to the inner hanger 550 via first, second, third, and fourth hooks 761, 763, 765, and 767. Method 810 includes forming a plurality of inner strips 760 at S811. According to one or more embodiments, the inner strips 760 may be formed of or comprise CMC material. Method 810 also includes, at S812, sliding the first, second, third, and fourth hooks 761, 763, 765, and 767, which extend radially in the circumferential direction C from or near the axial end of each inner strip 760, onto the inner hanger 550.

[0135] Figure 14C A method 820 for assembling an airfoil assembly 102 onto an outer hanger 500 according to one or more embodiments is illustrated. Method 820 removably attaches an outer strip 410 to the outer hanger 500 via first, second, and third attachment tabs 420, 430, 431. Method 820 includes forming a plurality of outer strips 410 at S821. According to one or more embodiments, the outer strips 410 may be formed of or comprise CMC material. Method 820 also includes causing pins 601, 605, 607 to pass in the axial direction A through the first, second, and third attachment tabs 420, 430, 431 extending radially from or near the axial end of the outer strip 410, and through the first and second radial walls 520, 530 of the outer hanger 500.

[0136] Figure 14D A method 830 for assembling an airfoil assembly 102 onto an inner hanger 550 according to one or more embodiments is illustrated. Method 830 removably attaches an inner strip 460 to the inner hanger 500 via first and second radial walls. Method 830 includes forming a plurality of inner strips 460 at S831. According to one or more embodiments, the inner strips 460 may be formed of or comprise CMC material. Method 830 also includes passing a pin 603 in the axial direction A through a first radial wall 470 extending radially from or near an axial end of the inner strip 460, and through a first radial wall 570 of the inner hanger 550. Method 830 may further include passing a pin (not shown) in the axial direction A through a second radial wall 480 extending radially from or near an axial end of the inner strip 460, and through a second radial wall 580 of the inner hanger 550.

[0137] One or more of the above embodiments can simplify manufacturing, thereby reducing costs and increasing production volume. Furthermore, one or more of the above embodiments can reduce and / or eliminate stress at the airfoil-to-strip interface. One or more embodiments can effectively position and attach the outer and inner strips to the outer and inner hangers.

[0138] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any device or system and performing any combination of methods. The patent scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0139] Further aspects are provided by the following topics:

[0140] An airfoil assembly defining an axial direction, a radial direction, and a circumferential direction includes: an airfoil; and an outer band disposed on an outer end of the airfoil in the radial direction, wherein the outer band includes an external attachment structure configured to secure the outer band to an external support structure on the outside of the outer band.

[0141] According to one or more of these clauses, the airfoil assembly, wherein the airfoil and the outer strip are formed of or comprise ceramic matrix composites (CMCs).

[0142] According to one or more of these clauses, the airfoil assembly, wherein the external attachment structure includes: a first external hook extending radially from or near a first axial end of the outer band, and a second external hook extending radially from or near a second axial end of the outer band, wherein the first and second external hooks are configured to slide onto the external support structure in the circumferential direction to removably secure the airfoil assembly to the external support structure.

[0143] According to one or more of these clauses, the ends of the first outer hook and the second outer hook extend toward each other in the axial direction.

[0144] According to one or more of these clauses, the airfoil assembly, wherein the external attachment structure includes: a first outer flange extending radially from or near a first axial end of the outer band, and a second outer flange extending radially from or near a second axial end of the outer band, wherein the first outer flange defines a first opening extending in the axial direction, wherein the second outer flange defines a second opening extending in the axial direction, and wherein the first opening and the second opening are configured to allow a pin to pass through a corresponding opening therein on the outer support structure to removably secure the airfoil assembly to the outer support structure.

[0145] According to one or more of these clauses, the airfoil assembly wherein the first outer flange is located upstream of the outer attachment structure in the axial direction relative to the second outer flange.

[0146] According to one or more of these clauses, the airfoil assembly wherein the first opening is elongated and larger in the circumferential direction than in the radial direction.

[0147] According to one or more of these clauses, the airfoil assembly further includes: a radially abutting surface extending from the upper surface of the outer strip, wherein the radially abutting surface faces upstream in the axial direction, wherein the radially abutting surface is separate from the first outer flange and the second outer flange, and wherein the radially abutting surface is configured to abut a corresponding abutting surface of the outer support structure.

[0148] According to one or more of these clauses, the airfoil assembly wherein the second outer flange is tabular and configured to extend radially through an opening in the outer support structure.

[0149] According to one or more of these clauses, the airfoil assembly further includes: a third outer flange, the third outer flange being tabular, wherein the third outer flange is configured to extend radially through another aperture in the outer support structure, wherein the third outer flange is disposed adjacent to the second outer flange in the circumferential direction, and wherein the third outer flange has a third opening configured to allow a pin to pass through to a corresponding opening on the outer support structure.

[0150] According to one or more of these clauses, the airfoil assembly wherein the upstream surfaces of the first and second outer flanges in the axial direction are configured to adjoin the radial surfaces of the outer support structure.

[0151] According to one or more of these clauses, the airfoil assembly, wherein the airfoil and the outer band are formed as separate pieces.

[0152] According to one or more of these clauses, the airfoil assembly further includes: an inner strip disposed on the inner end of the airfoil in the radial direction, wherein the inner strip includes an inner attachment structure configured to removably secure the inner strip to an inner support structure on the inner side of the inner strip.

[0153] According to one or more of these clauses, the airfoil assembly, wherein the inner attachment structure includes: a first inner hook extending radially from or near a first axial end of the inner band, and a second inner hook extending radially from or near a second axial end of the inner band, wherein the first inner hook and the second inner hook are configured to slide onto the inner support structure in the circumferential direction to removably secure the airfoil assembly to the inner support structure.

[0154] According to one or more of these clauses, the airfoil assembly, wherein the inner attachment structure includes: a first inner flange extending radially from or near a first axial end of the inner band, and a second inner flange extending radially from or near a second axial end of the inner band, wherein the first inner flange includes a first opening in the axial direction, wherein the second inner flange includes a second opening in the axial direction, and wherein the first opening and the second opening are configured to allow a pin to pass through a corresponding opening therein on the inner support structure to removably secure the airfoil assembly to the inner support structure.

[0155] According to one or more of these clauses, the airfoil assembly wherein the first inner flange is located upstream of the second inner flange in the axial direction.

[0156] According to one or more of these clauses, the airfoil assembly wherein the first opening is elongated and larger in the circumferential direction than in the radial direction.

[0157] According to one or more of these clauses, the downstream surface of the first inner flange and the upstream surface of the second inner flange are configured to adjoin the inner support structure.

[0158] A gas turbine engine includes: an outer support structure; and an airfoil assembly defining an axial direction, a radial direction, and a circumferential direction, and comprising: an airfoil; an outer strip disposed on an outer end of the airfoil in the radial direction; and an inner strip disposed on an inner end of the airfoil in the radial direction, wherein the outer strip includes an outer attachment structure configured to secure the outer strip to an outer side of the outer support structure, wherein the outer strip includes the attachment structure, and wherein the attachment structure attaches the outer strip to the outer support structure.

[0159] A method for assembling an airfoil assembly to an outer support structure, the airfoil assembly defining an axial direction, a radial direction, and a circumferential direction, and including an airfoil, an outer strip disposed at an outer end of the airfoil in the radial direction, and an inner strip disposed at an inner end of the airfoil in the radial direction, the method comprising: attaching the outer strip to the outer support structure via an attachment structure of the outer strip, wherein attaching the outer strip to the outer support structure includes one of: sliding a first outer hook and a second outer hook extending radially from or near an axial end of the outer strip onto the outer support structure in the circumferential direction, and causing a retaining pin to pass through a first outer flange and a second outer flange extending radially from or near an axial end of the outer strip in the axial direction, and through a flange of the outer support structure.

Claims

1. An airfoil assembly defining axial, radial, and circumferential directions, characterized in that, include: airfoil components; as well as The outer strip is disposed on the outer end of the airfoil in the radial direction. The outer strap includes an external attachment structure, which is configured as an external support structure to fix the outer strap to the outside of the outer strap. The external attachment structure includes: A first outer flange, the first outer flange extending radially from or near the first axial end of the outer band, and The second outer flange extends radially from or near the second axial end of the outer band. The first outer flange defines a first opening extending in the axial direction. Wherein, the second outer flange defines a second opening extending in the axial direction, and The first opening and the second opening are configured to allow a pin to pass through a corresponding opening in the outer support structure to removably secure the airfoil assembly to the outer support structure. The second outer flange is tabular and configured to extend radially through an opening in the outer support structure; The third outer flange is a sheet-like structure. The third outer flange is configured to extend radially through another opening in the outer support structure. Wherein, the third outer flange is disposed adjacent to the second outer flange in the circumferential direction, and The third outer flange has a third opening, which is configured to allow the pin to pass through to a corresponding opening on the outer support structure.

2. The airfoil assembly according to claim 1, characterized in that, in, The airfoil and the outer band are formed of or comprise ceramic matrix composites (CMCs).

3. The airfoil assembly according to claim 1, characterized in that, in, The first outer flange is located upstream of the outer attachment structure in the axial direction relative to the second outer flange.

4. The airfoil assembly according to claim 3, characterized in that, in, The first opening is elongated and is larger in the circumferential direction than in the radial direction.

5. The airfoil assembly according to claim 1, characterized in that, Further includes: A radially adjacent surface, the radially adjacent surface extending from the upper surface of the outer band, Wherein, the radially adjacent surface faces the upstream side in the axial direction. Wherein, the radially adjacent surface is separated from the first outer flange and the second outer flange, and The radially adjacent surface is configured to be adjacent to the corresponding adjacent surface of the outer support structure.

6. The airfoil assembly according to claim 1, characterized in that, in, The upstream surfaces of the first and second outer flanges in the axial direction are configured to be adjacent to the radial surfaces of the outer support structure.

7. The airfoil assembly according to claim 1, characterized in that, in, The airfoil and the outer band are formed as separate pieces.

8. The airfoil assembly according to claim 1, characterized in that, Further includes: An inner strip, the inner strip being disposed on the inner end of the airfoil in the radial direction, The inner band includes an inner attachment structure configured as an inner support structure that removably secures the inner band to the inside of the inner band.

9. The airfoil assembly according to claim 8, characterized in that, in, The internal attachment structure includes: A first inner flange, the first inner flange extending radially from or near the first axial end of the inner band, and The second inner flange extends radially from or near the second axial end of the inner band. The first inner flange includes a first opening in the axial direction. Wherein, the second inner flange includes a second opening in the axial direction, and The first opening of the first inner flange and the second opening of the second inner flange are configured to allow a pin to pass through a corresponding opening on the inner support structure to removably secure the airfoil assembly to the inner support structure.

10. The airfoil assembly according to claim 9, characterized in that, in, The first inner flange is located upstream of the second inner flange in the axial direction.

11. The airfoil assembly according to claim 9, characterized in that, in, The first opening of the first inner flange is elongated and larger in the circumferential direction than in the radial direction.

12. The airfoil assembly according to claim 9, characterized in that, in, The downstream surface of the first inner flange and the upstream surface of the second inner flange are configured to be adjacent to the inner support structure.

13. A gas turbine engine, characterized in that, include: External support structure; as well as An airfoil assembly defining axial, radial, and circumferential directions, and comprising: airfoil components; and An outer band, the outer band being disposed on the outer end of the airfoil in the radial direction and defining an outer side, wherein the outer band includes an attachment structure that secures the outer band to the outer support structure on the outer side of the outer band; The attachment structure includes: A first outer flange, the first outer flange extending radially from or near the first axial end of the outer band, and The second outer flange extends radially from or near the second axial end of the outer band. The first outer flange defines a first opening extending in the axial direction. Wherein, the second outer flange defines a second opening extending in the axial direction, and The first opening and the second opening are configured to allow a pin to pass through a corresponding opening in the outer support structure to removably secure the airfoil assembly to the outer support structure. The second outer flange is tabular and configured to extend radially through an opening in the outer support structure; The third outer flange is a convex plate-shaped flange. The third outer flange is configured to extend radially through another opening in the outer support structure. Wherein, the third outer flange is disposed adjacent to the second outer flange in the circumferential direction, and The third outer flange has a third opening, which is configured to allow the pin to pass through to a corresponding opening on the outer support structure.

14. A method for assembling an airfoil assembly onto an external support structure, the airfoil assembly defining an axial direction, a radial direction, and a circumferential direction, and comprising an airfoil, an outer strip disposed on an outer end of the airfoil in the radial direction, and an inner strip disposed on an inner end of the airfoil in the radial direction, characterized in that, The method includes: The outer strap is attached to the outer support structure via the attachment structure of the outer strap. Attaching the outer band to the outer support structure includes: The fixing pin passes through the first and second outer flanges, which extend radially from or near the axial end of the outer belt, in the axial direction, and also passes through the flange of the outer support structure. The attachment structure includes: A first outer flange, the first outer flange extending radially from or near the first axial end of the outer band, and The second outer flange extends radially from or near the second axial end of the outer band. The first outer flange defines a first opening extending in the axial direction. Wherein, the second outer flange defines a second opening extending in the axial direction, and The first opening and the second opening are configured to allow a pin to pass through a corresponding opening in the outer support structure to removably secure the airfoil assembly to the outer support structure. The second outer flange is tabular and configured to extend radially through an opening in the outer support structure; The third outer flange is a convex plate-shaped flange. The third outer flange is configured to extend radially through another opening in the outer support structure. Wherein, the third outer flange is disposed adjacent to the second outer flange in the circumferential direction, and The third outer flange has a third opening, which is configured to allow the pin to pass through to a corresponding opening on the outer support structure.

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