CMC nozzle assembly for manufacture of gas turbine engines

Abstract

A nozzle segment assembly (100) for a gas turbine engine (10) includes an outer band (110), an inner band (160), and at least one airfoil body (200) between the outer band (110) and the inner band (160). The airfoil body (200) includes: an outer end (220) extending through the outer band (110) and having an outer end reinforcement wall portion (224) engaged with the outer band (110); and an inner end (240) extending through the inner band (160) and having an inner end reinforcement wall portion (244) engaged with the inner band (160). The outer end reinforcement wall portion (224) and the inner end reinforcement wall portion (244) each have a thickness greater than a thickness of a central wall portion (208) of the airfoil body (200) to reduce stress in the airfoil body (200). The outer band (110), the inner band (160), and the airfoil body (200) are of a ceramic matrix composite (CMC) material. Mounting the airfoil body (200) directly to the inner hanger (350) and the outer hanger (300) of the nozzle (50) further reduces stress.

Description

[0001] This application is a divisional application of the invention patent application with application number 202111265763.5 filed on October 28, 2021 and invention name “CMC nozzle assembly for the manufacture of gas turbine engines”. Technical Field

[0002] The present description relates generally to nozzle assemblies for gas turbine engines and, more particularly, to airfoil assemblies including ceramic matrix composite (CMC) components and a framework for joining the CMC components to each other and to metal components. Background Art

[0003] At least some known gas turbine engines include a core having a high pressure compressor, a combustor, and a high pressure turbine (HPT) in a serial flow relationship. The core engine is operable to generate a primary airflow. The high pressure turbine includes an annular array ("row") of stationary vanes or nozzles that directs the gas leaving the combustor into rotating blades or moving blades. A row of nozzles and a row of blades together constitute a "stage". Typically, two or more stages are used in a serial flow relationship. These components operate in an extremely high temperature environment and can be cooled by airflow to ensure adequate service life.

[0004] HPT nozzles are typically constructed as an array of airfoil-shaped vanes extending between an annular inner and outer bands, which define the main flow path through the nozzle. Due to the operating temperatures within the gas turbine engine, materials with low thermal expansion coefficients are used. For example, in order to operate effectively under such adverse temperature and pressure conditions, ceramic matrix composite (CMC) materials can be used. These low thermal expansion coefficient materials have higher temperature capabilities than similar metal parts, so when operating at higher operating temperatures, the engine can operate at higher engine efficiency. However, such CMC materials have mechanical properties that must be considered during the design and application of CMCs. Compared with metal materials, CMC materials have relatively low tensile ductility or low failure strain. In addition, the thermal expansion coefficient of CMC materials is significantly different from that of metal alloys used as constrained supports or hangers for CMC-type materials. Therefore, if a CMC component is constrained and cooled on one surface during operation, stress concentration may occur, resulting in a shortened life of the segment.

[0005] Heretofore, nozzles formed from CMC materials have experienced localized stresses that exceed the capabilities of the CMC material, resulting in shortened nozzle life. The stresses have been found to be due to moment stresses applied to the nozzle and associated attachment features, differential thermal growth between parts of different material types, and loads in concentrated paths at the interface between the nozzle and associated attachment features. Summary of the invention

[0006] The manufacture of CMC nozzle components has proven to be expensive, which may be due in part to the complex geometry that is difficult to lay up and compact, resulting in high contact time and low yield. Simpler preform designs can alleviate this problem; however, the complex geometry of the nozzle must be retained. One solution to this is to form the airfoil body and the band portion (e.g., the outer band and the inner band) separately, and then join the airfoil body and the band portion in a joining operation to form an airfoil assembly. When the airfoil body, the outer band and the inner band are formed and assembled together to form the airfoil assembly, the joint between the airfoil body and the outer band and between the airfoil body and the inner band becomes the main load-bearing feature to maintain the fit and function of the airfoil assembly. During the operation of the nozzle, the local stress at the joint between the airfoil body and the outer band and the inner band will exceed the stress capacity of the CMC material, which may result in a shortened life of the airfoil assembly. Therefore, there is a continuous demand for the design of the airfoil assembly and the nozzle segment assembly to minimize the local stress on the airfoil body at the joint with the outer band and the inner band and to improve the life of the airfoil assembly.

[0007] The present disclosure meets these needs by providing an airfoil assembly having an outer band, an inner band, and one or more airfoil bodies, wherein each airfoil body includes an outer end reinforcing wall portion, an inner end reinforcing wall portion, or both. The outer end reinforcing wall portion and the inner end reinforcing wall portion may be positioned at the junction of the airfoil body with the outer band and the inner band, respectively, and may each have a greater thickness or wall thickness than the remainder of the airfoil body. The greater thickness of the outer end reinforcing wall portion and the inner end reinforcing wall portion may reduce stress at the junction between the airfoil body and the outer band and the inner band, and may prevent cracks from forming at the junction by shifting stress concentrations away from the junction.

[0008] The protrusion of the outer and inner ends of the airfoil body from the outer and inner bands can enable the airfoil body to be directly mounted to the turbine structural member by engaging with the outer and inner hangers. During operation, most of the stress is borne by the airfoil body. Therefore, compared with mounting the airfoil assembly to the turbine structural member by engaging the outer and inner bands with the outer and inner hangers, respectively, mounting the airfoil body directly to the inner and outer hangers can further reduce the local stress at the joint between the airfoil body and the outer and inner bands.

[0009] According to one or more aspects disclosed herein, a nozzle segment assembly for a gas turbine engine includes an airfoil assembly having an outer band, an inner band, and at least one airfoil body extending between the outer band and the inner band. At least one airfoil body may include an outer end extending through the outer band and having an outer end reinforcing wall portion protruding from the outer surface of at least one airfoil body to engage with the outer band. At least one airfoil body may also include an inner end extending through the inner band and having an inner end reinforcing wall portion protruding from the outer surface of at least one airfoil body to engage with the inner band. The thickness of the outer end reinforcing wall portion and the thickness of the inner end reinforcing wall portion may both be greater than the thickness of the central wall portion of at least one airfoil body. The outer band, the inner band, and at least one airfoil body may include a ceramic matrix composite (CMC) material.

[0010] According to one or more additional aspects disclosed herein, a nozzle segment assembly for a gas turbine engine may include an inner hanger, an outer hanger, and an airfoil assembly. The airfoil assembly may include an outer band including a radially outwardly facing surface; an inner band including a radially inwardly facing surface; and at least one airfoil body extending between the outer band and the inner band. At least one airfoil body may include an outer end extending through the outer band and projecting outwardly from the radially outwardly facing surface of the outer band. The at least one airfoil body may also include an inner end extending through the inner band and projecting radially inwardly from the radially inwardly facing surface of the inner band. The outer hanger may be disposed radially outwardly from the outer band, and the inner hanger may be disposed radially inwardly from the inner band. The outer end of at least one airfoil body may engage with the outer hanger and the inner end of at least one airfoil body may engage with the inner hanger to position and constrain the airfoil assembly. The outer band, the inner band, and at least one airfoil body may include a ceramic matrix composite (CMC) material.

[0011] It is to be understood that both the foregoing general description and the following detailed description describe various embodiments and are intended to provide an overview or framework for understanding the nature and character of the claimed subject matter. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] The accompanying drawings are included to provide a further understanding of the various embodiments and are incorporated in and constitute a part of this specification. The accompanying drawings illustrate the various embodiments described herein, and together with the description serve to explain the principles and operations of the claimed subject matter.

[0013] Figure 1 schematically depicts a gas turbine engine according to the embodiments shown and described herein;

[0014] Figure 2 Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 1 Nozzle rings of gas turbine engines;

[0015] Figure 3 Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 2 A perspective view of an airfoil assembly of a nozzle ring;

[0016] Figure 4 Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 2 A perspective view of another embodiment of an airfoil assembly of a nozzle ring;

[0017] Figure 5 Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 2 An exploded perspective view of a nozzle segment assembly of a nozzle ring;

[0018] Fig. 6A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 a cross-sectional view of a portion of a nozzle segment assembly;

[0019] Figure 6B Schematically depicts a nozzle having a strut passing through an airfoil body of a nozzle segment assembly according to embodiments shown and described herein. Figure 5 a cross-sectional view of a portion of a nozzle segment assembly;

[0020] Fig. 7A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 a cross-sectional view of a portion of a junction between an airfoil body and an outer band of a nozzle segment assembly;

[0021] Figure 7B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 a cross-sectional view of a portion of a junction between an airfoil body and an inner band of a nozzle segment assembly;

[0022] Fig. 8A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 a cross-sectional view of a portion of another embodiment of a junction between an airfoil body and an outer band of a nozzle segment assembly;

[0023] Figure 8B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 a cross-sectional view of a portion of another embodiment of a junction between an airfoil body and an inner band of a nozzle segment assembly;

[0024] Fig. 9A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 A top view of an airfoil body of a nozzle segment assembly;

[0025] Fig. 9B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 A top view of another embodiment of an airfoil body of a nozzle segment assembly;

[0026] Fig. 10A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 A perspective cross-sectional view of an embodiment of a nozzle segment assembly;

[0027] Fig. 10B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig. 10A A top cross-sectional view of an embodiment of a nozzle segment assembly;

[0028] Fig.11A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 A perspective cross-sectional view of another embodiment of a nozzle segment assembly;

[0029] Fig. 11B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig.11A A top cross-sectional view of an embodiment of a nozzle segment assembly;

[0030] Fig. 11C Schematically depicts a schematic diagram of a circuit according to the embodiments shown and described herein. Fig. 11B The reference plane 11C-11C in Fig. 11B A side cross-sectional view of an embodiment of a nozzle segment assembly;

[0031] Fig. 12A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 A three-dimensional cross-sectional view of another embodiment of a nozzle segment assembly;

[0032] Fig. 12B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig. 12A A top cross-sectional view of an embodiment of a nozzle segment assembly;

[0033] Fig.13A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 A three-dimensional cross-sectional view of another embodiment of a nozzle segment assembly;

[0034] Fig. 13B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig.13A A top cross-sectional view of an embodiment of a nozzle segment assembly;

[0035] Fig. 13CSchematically depicts a schematic diagram of a circuit according to the embodiments shown and described herein. Fig. 13B The reference plane 13C-13C in Fig. 13B A side cross-sectional view of an embodiment of a nozzle segment assembly;

[0036] Fig.14A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 A three-dimensional cross-sectional view of another embodiment of a nozzle segment assembly;

[0037] Fig. 14B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig.14A A top cross-sectional view of an embodiment of a nozzle segment assembly;

[0038] Fig. 14C Schematically depicts a schematic diagram of a circuit according to the embodiments shown and described herein. Fig. 14B The reference plane 14C-14C in Fig. 14B A side cross-sectional view of an embodiment of a nozzle segment assembly;

[0039] Fig.15A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 A three-dimensional cross-sectional view of another embodiment of a nozzle segment assembly;

[0040] Fig. 15B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig.15A A top cross-sectional view of an embodiment of a nozzle segment assembly;

[0041] Fig. 15C Schematically depicts a schematic diagram of a circuit according to the embodiments shown and described herein. Fig. 15B The reference plane 15C-15C in Fig. 15B A side cross-sectional view of an embodiment of a nozzle segment assembly;

[0042] Fig.16A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 A three-dimensional cross-sectional view of another embodiment of a nozzle segment assembly;

[0043] Fig. 16B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig.16A A top cross-sectional view of an embodiment of a nozzle segment assembly;

[0044] Fig.17 Schematically depicts a schematic diagram showing an embodiment according to the present invention shown and described Figure 5 A side perspective view of a radially mounted airfoil assembly of a nozzle segment assembly;

[0045] Fig.18A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Figure 5 Another embodiment of the airfoil assembly of the nozzle segment assembly, wherein the airfoil body is separated from the outer band and the inner band;

[0046] Fig.18B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig.18A An exploded perspective view of an airfoil assembly;

[0047] Fig.19A Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig.18A A perspective view of an outer band of an airfoil assembly; and

[0048] Fig.19B Schematically depicts a schematic diagram of a system according to the embodiments shown and described herein. Fig.19A Another stereoscopic view of the takeout.

[0049] The drawings are not intended to be to scale and certain dimensions and proportions in the drawings may be exaggerated for illustrative purposes. DETAILED DESCRIPTION

[0050] Reference will now be made in detail to an embodiment of a nozzle segment assembly for a nozzle ring of a gas turbine engine according to the present disclosure. Whenever possible, the same reference numerals will be used throughout the drawings and the detailed description to refer to the same or like parts. Figure 5 and 6A, schematically depicts an embodiment of a nozzle segment assembly 100 for a nozzle ring of a gas turbine engine. The nozzle segment assembly 100 may include an airfoil assembly 102 having an outer band 110 having a radially outwardly facing surface 112; an inner band 160 having a radially inwardly facing surface 164; and at least one airfoil body 200 extending between the outer band 110 and the inner band 160. The at least one airfoil body 200 may include an outer end 220 extending through the outer band 110 and having an outer end reinforcement wall portion 224 protruding from an outer surface 202 of the airfoil body 200 to engage the outer band 110. The airfoil body 200 may also include an inner end 240 extending through the inner band 160 and having an inner end reinforcement wall portion 244 protruding from an outer surface 202 of the airfoil body 200 to engage the inner band 160. The thickness of the outer end reinforcement wall portion 224 and the thickness of the inner end reinforcement wall portion 244 may both be greater than the thickness of the central wall portion 208 of the airfoil body 200. The outer band 110, the inner band 160 and the airfoil body 200 may be made of a ceramic matrix composite (CMC) material. The reinforcement wall portion may reduce the local stress at the joints 223, 243 between the airfoil body 200 and the outer band 110 and the inner band 160, which may increase the stress capacity of the airfoil body 200 made of the CMC material and may improve the service life of the hollow airfoil body 200.

[0051] The nozzle segment assembly 100 may additionally include an outer pylon 300 and an inner pylon 350, each of which may include one or more mounting features 310. The mounting features 310 may enable the airfoil body 200 to be mounted directly to the outer pylon 300 and the inner pylon 350. Mounting the airfoil body 200 directly to the outer pylon 300 and the inner pylon 350 may further reduce localized stresses in the airfoil body 200 as compared to coupling the outer band 110 and the inner band 160 to the outer pylon 300 and the inner pylon 350, respectively, and then transferring forces between the engine and the airfoil body 200 via the joint 223 with the outer band 110, the joint 243 with the inner band 160, or both. Other benefits may be apparent to one of ordinary skill in the art upon considering the information contained in this disclosure.

[0052] Unless otherwise expressly stated, any method set forth herein is in no way intended to be construed as requiring that its steps be performed in a particular order, nor is it intended that any apparatus require a particular orientation. Thus, if a method claim does not actually recite the order in which its steps are to be followed, or any apparatus claim does not actually recite the order or orientation of individual components, or if there is no other specific statement in the claim or specification that the steps are limited to a particular order, or if no particular order or orientation of apparatus components is recited, then no order or orientation is intended to be inferred in any respect. This applies to any possible non-explicit basis for interpretation, including: logical issues relating to arrangement of steps, operational flow, order of components, or orientation of components; plain meaning derived from grammatical organization or punctuation; and the number or type of embodiments described in the specification.

[0053] Directional terms used herein (eg, up, down, right, left, front, back, top, bottom) are made solely with reference to the drawings drawn and the coordinate axes provided therewith, and are not intended to imply an absolute orientation.

[0054] As used herein, the singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise. Thus, for example, reference to "a" component includes aspects having two or more such components unless the context clearly dictates otherwise.

[0055] Unless limited otherwise, the terms "connected," "coupled," and "mounted" and variations thereof are used broadly herein and include direct and indirect connections, couplings, and mountings. Furthermore, the terms "connected" and "coupled" and variations thereof are not limited to physical or mechanical connections or couplings. When used as a noun, the term "mounted" may refer to structure operable to position and / or restrain one or more components within an assembly.

[0056] As used herein, the term "axial" or "axially" refers to a dimension along the longitudinal axis of the engine. The term "front" used in conjunction with "axial" or "axially" refers to movement in a direction toward the engine inlet, or a component being relatively closer to the engine inlet than another component. The term "rear" used in conjunction with "axial" or "axially" refers to movement in a direction toward the rear of the engine.

[0057] As used herein, the term "radial" or "radially" refers to the direction of the engine's central longitudinal axis (i.e., Figure 1 The term "inwardly" may refer to the dimension extending between the central axis A of the engine 10 and the outer engine circumference. Figure 1 ) direction, which is the direction in the -r direction of the cylindrical coordinate axis in the figure. The term "outward" may refer to a direction radially away from the central axis A of the engine 10, which is the direction in the +r direction of the cylindrical coordinate axis in the figure.

[0058] As used herein, the term "angled" or "angledly" refers to a direction along which the engine 10 ( Figure 1 ) and characterized by increasing or decreasing angles. As used herein, the term "tangential" may refer to a dimension extending along a line tangential to the circumference of a circle centered on the central axis A of the engine and passing through a portion of a nozzle segment assembly. Over the angular width represented by a single nozzle segment assembly 100, the difference between the tangential direction and the angular direction may be small, such that "tangential" and "angled" may be used interchangeably in the context of describing a single nozzle segment assembly 100 or airfoil assembly 102.

[0059] The following description refers to the drawings, in which like numerals in different drawings represent similar elements unless otherwise indicated.

[0060] Figure 1 is a schematic diagram of an exemplary gas turbine engine 10. The engine 10 includes a low-pressure compressor 12, a high-pressure compressor 14, and a combustor assembly 16. The engine 10 also includes a high-pressure turbine 18 and a low-pressure turbine 20 arranged in a serial axial flow relationship on respective rotors 22 and 24. The compressor 12 and the turbine 20 may be coupled by a first shaft 26, while the compressor 14 and the turbine 18 may be coupled by a second shaft 28.

[0061] During operation, air flows along the central axis A of the engine 10, and compressed air is supplied to the high pressure compressor 14. The highly compressed air is delivered to the combustor 16. The exhaust gas flow ( Figure 1 The gas turbine engine 10 also includes a fan or low-pressure compressor containment casing 40.

[0062] Figure 2 is a perspective view of a nozzle ring 50 according to an exemplary embodiment of the present disclosure. In an exemplary embodiment, the nozzle ring 50 may be located at the high pressure turbine 18 and / or the low pressure turbine 20 ( Figure 1 ) in the nozzle ring 50. The nozzle ring 50 is formed by one or more nozzle segment assemblies 100. The nozzle segment assembly 100 directs the combustion gases downstream through the support rotor 22 or 24 ( Figure 1 The nozzle ring 50 and the plurality of nozzle segment assemblies 100 defining the nozzle ring 50 facilitate passage of the nozzle through the rotor 22 or 24 ( Figure 1 In addition, the nozzle ring 50 can be used for the high pressure compressor 14, which can be a high pressure or low pressure compressor.

[0063] The nozzle ring 50 is formed by 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 an embodiment, the outer hanger 300, the inner hanger, or both may be a continuous ring. In some embodiments, the nozzle ring 50 may include an outer hanger 300 for each 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 an embodiment, the nozzle ring 50 may include an inner hanger 350 for each nozzle segment assembly 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 circumferentially 360 degrees around the central axis A of the gas turbine engine 10. The plurality of airfoil assemblies 102 may be radially disposed between the outer hanger 300 of the outer ring 52 and the inner hanger 350 of the inner ring 54.

[0064] refer to Figure 3 , schematically depicts a perspective view of an airfoil assembly 102 according to the present disclosure. The airfoil assembly 102 may include: an outer band 110 having a radially outwardly facing surface 112; an inner band 160 having a radially inwardly facing surface 164; and at least one airfoil body 200 extending between the outer band 110 and the inner band 160. The airfoil assembly 102 may include one or more airfoil bodies 200, such as 1, 2, 3, 4, or more than 4 airfoil bodies 200. Reference Figure 2 In some embodiments, each of the plurality of airfoil assemblies 102 may be a single body including a single airfoil body 200 extending between the outer band 110 and the inner band 160 . Figure 3 As shown, in an embodiment, each of the plurality of airfoil assemblies 102 may be a duplex including two airfoil bodies 200 extending between an outer band 110 and an inner band 160 . Figure 4 In an embodiment, each of the plurality of airfoil assemblies 102 may be a triplet including three airfoil bodies 200 extending between the outer band 110 and the inner band 160. Although not shown in the figures, in an embodiment, each airfoil assembly 102 may include four or more airfoil bodies 200. Various features of the present disclosure will be described herein in the context of an airfoil assembly 102 having two airfoil bodies 200, however, it should be understood that an airfoil assembly 102 may have more or less than two airfoil bodies 200 without departing from the scope of the present disclosure.

[0065] Reference again Figure 3, the outer band 110, the inner band 160 and the at least one airfoil body 200 may include a material having a low coefficient of thermal expansion. In an embodiment, the outer band 110, the inner band 160 and the at least one airfoil body 200 may include a ceramic matrix composite (CMC) material. Other materials having a low coefficient of thermal expansion are also contemplated.

[0066] Reference now Figure 5 , schematically depicts an exploded view of nozzle segment assembly 100. Outer band 110 may include: a radially outward facing surface 112; a radially inward facing surface 114; and one or more openings 116 extending through the thickness of outer band 110 from radially outward facing surface 112 to radially inward facing surface 114. Radially outward facing surface 112 may be the outer band 110 away from the central axis A ( Figure 2 ) radially outward (i.e., at Figure 5 The radially inwardly facing surface 114 may be a surface of the outer band 110 that faces radially inwardly (ie, in the +r direction of the cylindrical coordinate axis in FIG. 1 ) toward the central axis A of the engine 10. Figure 5 The radially outwardly facing surface 112 and the radially inwardly facing surface 114 may be angularly (i.e., in the -r direction of the cylindrical coordinate axis of the cylindrical coordinate axis). Figure 5 Each opening 116 may be shaped to receive an outer end 220 of one of the airfoil bodies 200 such that at least a portion of the outer end 220 of the airfoil body 200 passes through the opening 116 and protrudes radially outward from the radially outwardly facing surface 112 of the outer band 110.

[0067] The outer band 110 may also have a leading edge 120 and a trailing edge 122. The leading edge 120 may be the outer band 110 in the axial direction toward the engine inlet (i.e., at Figure 5 The trailing edge 122 may be the edge of the outer band 110 that faces in the axial direction toward the engine outlet (i.e., in the +X direction of the cylindrical coordinate axis in FIG. 1 ). Figure 5 The edge facing the -X direction of the cylindrical coordinate axis in the circle.

[0068] Reference again Figure 5 , the inner band 160 may include: a radially outwardly facing surface 162; a radially inwardly facing surface 164; and one or more openings 166 extending from the radially outwardly facing surface 162 through the thickness of the inner band 160 to the radially inwardly facing surface 164. The radially outwardly facing surface 162 may be the inner band 160 away from the central axis A ( Figure 2 ) radially outward (i.e., at Figure 5The radially inwardly facing surface 164 may be a surface of the inner band 160 that faces radially inwardly (ie, in the +r direction of the cylindrical coordinate axis in FIG. 1 ) toward the center axis A of the engine 10. Figure 5 The radially outwardly facing surface 162 and the radially inwardly facing surface 164 may be angularly (i.e., in the -r direction of the cylindrical coordinate axis of the cylindrical coordinate axis). Figure 5 Each opening 166 in the inner band 160 may be shaped to receive an inner end 240 of one of the airfoil bodies 200 such that at least a portion of the inner end 240 of the airfoil body 200 passes through the opening 166 and protrudes radially inward from the radially inwardly facing surface 164 of the inner band 160.

[0069] The inner band 160 may also have a leading edge 170 and a trailing edge 172. The leading edge 170 may be the inner band 160 in the axial direction toward the engine inlet (i.e., at Figure 5 The trailing edge 172 may be the edge of the inner band 160 that faces in the axial direction toward the engine outlet (i.e., in the +X direction of the cylindrical coordinate axis in FIG. 1 ). Figure 5 The edge facing the -X direction of the cylindrical coordinate axis in the circle.

[0070] Reference again Figure 5 , the airfoil body 200 may be a hollow airfoil body or a solid airfoil body. When the airfoil body 200 is a hollow airfoil body, each of the airfoil bodies 200 may include an outer surface 202 and an inner surface 204. The outer surface 202 of the airfoil body 200 may be a surface of the airfoil body 200 that faces away from the airfoil body 200 and may have an airfoil shape. The general airfoil shape of the outer surface 202 of the airfoil body 200 is not particularly limited as long as each airfoil body 200 includes a suction side 218 and a pressure side 219. The inner surface 204 of the airfoil body 200 may be oriented inwardly facing and may define a cavity 206 extending through the airfoil body 200 from the outer end 220 of the airfoil body 200 to the inner end 240. Embodiments of the present disclosure will be described in the context of the airfoil body 200 being a hollow airfoil body; however, it should be understood that various features of the airfoil assembly 102 may also be applied to a solid airfoil body.

[0071] Each airfoil body 200 may have a leading edge 210 that faces the inlet of the engine 10 in the axial direction (ie, at Figure 5 and a trailing edge 212 which is oriented in the axial direction toward the outlet of the engine 10 (ie, in the +X direction of the cylindrical coordinate axis in the +X direction); Figure 5110). Each airfoil body 200 includes an outer end 220 and an inner end 240. The outer end 220 of the airfoil body 200 may be shaped to engage with the outer band 110. In particular, the outer end 220 of the airfoil body 200 may be shaped such that the outer end 220 of the airfoil body 200 extends through one of the openings 116 in the outer band 110 and protrudes radially outward from the radially outward facing surface 112 of the outer band 110. In an embodiment, at least a portion of the outer end 220 of the airfoil body 200 may provide an abutment surface that contacts the radially inward facing surface 114 of the outer band 110 to properly position the airfoil body 200 relative to the outer band 110. The inner end 240 of the airfoil body 200 may be shaped to engage with the inner band 160. In particular, the inner end 240 of the airfoil body 200 may be shaped such that the inner end 240 of the airfoil body 200 extends through one of the openings 166 in the inner band 160 and protrudes radially inward from the radially inward facing surface 164 of the inner band 160. In embodiments, at least a portion of the inner end 240 of the airfoil body 200 may provide an abutment surface that contacts the radially outward facing surface 162 of the inner band 160 to properly position the airfoil body 200 relative to the inner band 160.

[0072] Reference now Fig. 6A , schematically depicts a cross-sectional view of the nozzle segment assembly 100 . Fig. 6A The drawings are not drawn to scale and relative sizes may be exaggerated for illustrative purposes. Fig. 6A , the outer end 220 of the airfoil body 200 may extend through one of the openings 116 in the outer band 110 such that at least a portion of the outer end 220 protrudes radially outward from the radially outwardly facing surface 112 of the outer band 110, and the inner end 240 of the airfoil body 200 may extend through one of the openings 166 in the inner band 160 such that at least a portion of the inner end 240 protrudes radially inward from the radially inwardly facing surface 164 of the inner band 160. Thus, the outer end 220 of the airfoil body 200 may be used to engage with the outer hanger 300, and the inner end 240 of the airfoil body 200 may be used to engage with the inner hanger 350.

[0073] The airfoil body 200 may be rigidly and mechanically coupled to the outer band 110 at a joint 223 between the outer band 110 and the outer end 220, and rigidly and mechanically coupled to the inner band 160 at a joint 243 between the inner band 160 and the inner end 240. The airfoil body 200 may be rigidly coupled to the outer band 110 by bonding or adhering the outer surface 202 of the airfoil body 200 to the outer band 110 at the opening 116. The airfoil body 200 may be bonded to the outer band 110 by sintering or brazing, or by applying a bonding agent to the airfoil body 200, the outer band 110, or both at the joint 223 and curing the bonding agent. The airfoil body 200 may be adhered to the outer band 110 by applying an adhesive or glue to the outer surface 202 of the airfoil body 200 at the joint 223, and then contacting the adhesive on the outer surface 202 with the surface of the outer band 110 at the opening 116. Rigidly coupling the outer end 220 of the airfoil body 200 to the outer band 110 may prevent axial, radial, and / or angular movement of the airfoil body 200 relative to the outer band 110. The airfoil body 200 may also be rigidly and mechanically coupled to the inner band 160 at a joint 243 between the inner band 160 and the inner end 240 of the airfoil body 200. According to the above-described method for coupling the outer band 110 to the airfoil body 200, the airfoil body 200 may be rigidly coupled to the inner band 160 by bonding or adhering the outer surface 202 of the airfoil body 200 to the inner band 160 at the opening 166. Rigidly and mechanically coupling the inner end 240 of the airfoil body 200 to the inner band 160 may prevent axial, radial, and angular movement of the airfoil body 200 relative to the inner band 160.

[0074] In an embodiment, the airfoil body 200 may be mechanically separated from the outer band 110, the inner band 160, or both, prior to assembly to the nozzle segment assembly 100, which may enable the airfoil body 200 to move relative to the outer band 110, the inner band 160, or both in an axial, radial, and / or angular direction. Mechanically separating the airfoil body 200 from the outer band 110 and / or the inner band 160 may open a leak path between the airfoil body 200 and the outer band 110 and / or the inner band 160. The leak path may be sealed to prevent gas leakage between the airfoil body 200 and the outer band 110 and / or the inner band 160. The sealing may be accomplished using known sealing compounds or employing mechanical sealing techniques. When the airfoil body 200 is mechanically separated from the outer band 110 and / or the inner band 160, the airfoil body 200, the outer band 110, and the inner band 160 may all be separately mounted to the nozzle segment assembly 100, such as to the outer hanger 300 and / or the inner hanger 350.

[0075] Regardless of whether the airfoil body 200 is rigidly and mechanically coupled to the outer band 110, the inner band 160, or both, local stresses at the outer joint 223 between the outer band 110 and the airfoil body 200 and / or local stresses at the inner joint 243 between the inner band 160 and the airfoil body 200 may exceed the stress capacity of the CMC material of the airfoil body 200, which may shorten the life of the airfoil body 200. As previously described, the local stresses at the joint 223 between the airfoil body 200 and the outer band 110 and the local stresses at the joint 243 between the airfoil body 200 and the inner band 160 may be reduced by providing the airfoil body 200 with reinforced wall portions at the joint 223 with the outer band 110 and at the joint 243 with the inner band 160.

[0076] Reference now Fig. 7A , schematically depicts a cross-section of a portion of an airfoil body 200 at a junction 223 with an outer band 110. The airfoil body 200 may have an outer end reinforcing wall portion 224 disposed proximate to an outer end 220 of the airfoil body 200 at a junction 223 between the airfoil body 200 and the outer band 110. The outer end reinforcing wall portion 224 may protrude from an outer surface 202 of at least one airfoil body 200 to engage with the outer band 110. The outer end reinforcing wall portion 224 may be angularly oriented (e.g., Fig. 7A + / -Theta direction of the coordinate axis), axial direction (for example, Fig. 7A The thickness t1 of the outer end reinforcement wall portion 224 may be greater than the thickness t2 of the central wall region 208 of the airfoil body 200. c The central wall region 208 may be a portion of the airfoil body 200 that is radially disposed between an outer end reinforcement wall portion 224 at the outer end 220 of the airfoil body 200 and an inner end reinforcement wall portion 244 at the inner end 240 of the airfoil body 200 ( Figure 7B ). Again refer to Fig. 7A The greater thickness t1 of the outer end reinforcing wall portion 224 as compared to the central wall region 208 may increase the stress capacity of the airfoil body 200 in the region of the junction 223 with the outer band 110. The outer end reinforcing wall portion 224 may further include a fillet 225, wherein the thickness of the wall of the airfoil body 200 may be reduced from the thickness t1 of the outer end reinforcing wall portion 224 to the smaller thickness t1 of the central wall region 208. c The fillet 225 may operate to further distribute the stress concentration over a larger area, thereby effectively moving at least some of the stress away from the joint 223 and the connection between the outer end 220 and the outer band 110 .

[0077] The inner end 240 of the airfoil body 200 may also have a reinforced wall portion. Figure 7B , schematically depicts a cross-section of a portion of an airfoil body 200 at a junction 243 with an inner band 160. The airfoil body 200 may have an inner end reinforcing wall portion 244 disposed proximate to the inner end 240 of the airfoil body 200 at a junction 243 between the airfoil body 200 and the inner band 160. The inner end reinforcing wall portion 244 may protrude from the outer surface 202 of at least one airfoil body 200 to engage with the inner band 160. The inner end reinforcing wall portion 244 may be angularly oriented (e.g., Figure 7B + / -Theta direction of the coordinate axis), axial direction (for example, Figure 7B The thickness t2 of the inner end reinforcement wall portion 244 may be greater than the thickness t2 of the central wall region 208 of the airfoil body 200. c The greater thickness t2 of the inner end reinforcing wall portion 244 as compared to the central wall region 208 may increase the stress capacity of the airfoil body 200 in the region of the junction 243 with the inner band 160. The thickness t2 of the inner end reinforcing wall portion 244 may be the same as or different from the thickness t1 of the outer end reinforcing wall portion 224. The inner end reinforcing wall portion 244 may further include a fillet 225 where the thickness of the wall of the airfoil body 200 decreases from the thickness t2 of the inner end reinforcing wall portion 244 to the smaller thickness t1 of the central wall region 208. c The fillet 225 may operate to further distribute the stress concentration over a wider area, thereby effectively moving at least some of the stress away from the joint 243 .

[0078] Reference now Fig. 8A , schematically depicts another embodiment of the outer end reinforcement wall portion 224. Fig. 8A As shown, in an embodiment, the outer end reinforcement wall portion 224 may include a stepped configuration including an outer end flange 226 extending from the outer surface 202 at the outer end reinforcement wall portion 224 of the airfoil body 200. The outer end reinforcement wall portion 224 may further include a fillet 225 extending between the outer end flange 226 and the central wall region 208. As previously described, the fillet 225 at the outer end reinforcement wall portion 224 may be characterized by Fig. 8A The wall thickness decreases in the -r direction of the coordinate axis of the , starting from the maximum thickness at the outer end flange 226 and ending at the thickness t of the central wall region 208 cThe fillet 225 may operate to distribute localized stresses over a wider surface area, thereby moving the stresses away from the joint 223. The outer end flange 226 may include a radially outer surface 228 that may abut a portion of the radially inwardly facing surface 114 of the outer band 110. The stepped configuration of the outer end flange 226 and the abutment between the radially outer surface 228 of the outer end flange 226 and the radially inwardly facing surface 114 of the outer band 110 may reduce gas leakage between the airfoil body 200 and the outer band 110. Furthermore, the stepped configuration may help to properly position the outer band 110 relative to the airfoil body 200 during assembly and / or bonding. In some embodiments, the radially inwardly facing surface 114 of the outer band 110 may include a recess 124 that may provide a radial engagement surface 126 that may abut a radially facing surface 228 of the outer end flange 226 when the airfoil assembly 102 is assembled (e.g., when the outer band 110 is engaged with the airfoil body 200). The abutment of the radially outer surface 228 of the outer end flange 226 against the radially inwardly facing surface 114 of the outer band 110 or against the radial engagement surface 126 of the recess 124 may limit radial movement of the outer band 110 in a radially inward direction relative to the position of the airfoil body 200.

[0079] Reference now Figure 8B , the inner end reinforcement wall portion 244 may also have a stepped configuration including an inner end flange 246 extending from the outer surface 202 at the inner end reinforcement wall portion 244 of the airfoil body 200. The inner end reinforcement wall portion 244 may further include a fillet 225 extending between the inner end flange 246 and the central wall region 208. As previously described, the fillet 225 at the inner end reinforcement wall portion 244 may be characterized by Figure 8B The wall thickness decreases in the +r direction of the coordinate axis of the inner end flange 246, starting from the maximum thickness at the inner end flange 246 and ending at the thickness t of the central wall region 208. cThe fillet 225 may operate to distribute localized stresses over a wider surface area, thereby moving the stresses away from the joint 243. The inner end flange 246 may include a radially facing surface 248 that may abut a portion of the radially outward facing surface 162 of the inner band 160. The stepped configuration of the inner end flange 246 and the abutment between the radially facing surface 248 of the inner end flange 246 and the radially outward facing surface 162 of the inner band 160 may reduce or prevent gas leakage between the airfoil body 200 and the inner band 160. Furthermore, the stepped configuration may help to properly position the inner band 160 relative to the airfoil body 200 during assembly and / or bonding. In an embodiment, the radially outward facing surface 162 of the inner band 160 may include a recess 174 that may provide a radial engagement surface 176 that may abut against a radially facing surface 248 of the inner end flange 246 when the airfoil assembly 102 is assembled (e.g., when the inner band 160 is engaged with the airfoil body 200). The abutment of the radially facing surface 248 of the outer end flange 226 against the radially outward facing surface 162 of the inner band 160 or against the radial engagement surface 176 of the recess 174 may limit radial movement of the inner band 160 in a radially outward direction relative to the position of the airfoil body 200.

[0080] The outer end reinforcing wall portion 224, the inner end reinforcing wall portion 244, or both may extend at least partially or completely around the outer surface 202 of at least one airfoil body 200, proximate a junction 223, 243 between the airfoil body 200 and the outer band 110, the inner band 160, or both, respectively. Referring now to Fig. 9A and 9B , depicting a direction parallel to the center axis A ( Figure 2 ) plane (e.g., parallel to Fig. 9A A top cross-sectional view of an embodiment of an airfoil body 200 taken along a plane that is tangent to the + / -X direction of the coordinate axis in the + / -Theta direction. Fig. 9A As shown, in an embodiment, the outer end reinforcement wall portion 224 may extend all the way around the circumference of the outer surface 202 of the airfoil body 200. Similar to the outer end reinforcement wall portion 224, the inner end reinforcement wall portion 244 may also extend all the way around the circumference of the outer surface 202 of the airfoil body 200.

[0081] like Fig. 9BAs shown, in other embodiments, the outer end reinforcement wall portion 224 may extend around only a portion of the circumference of the outer surface 202 of the airfoil body 200. In the remaining portion of the circumference of the outer surface 202, the wall thickness of the airfoil body 200 may be less than the thickness t1 of the outer end reinforcement wall portion 224. In some embodiments, the thickness of the remaining portion of the circumference of the outer surface 202 may be equal to the thickness t1 of the central wall portion 208 of the airfoil body 200. c . Similar to Fig. 9B Unlike the outer end reinforcement wall portion 224 , the inner end reinforcement wall portion 244 may also extend around only a portion of the circumference of the outer surface 202 of the airfoil body 200 .

[0082] Additionally or alternatively, local stresses at the joints 223 and 243 may be further reduced by mounting the airfoil body 200 directly to the nozzle segment assembly 100 rather than mounting the outer band 110 and the inner band 160 to the nozzle segment assembly 100 and transferring forces to or from the airfoil body 200 through the joints 223, 243 with the outer band 110 and the inner band 160. By mounting the airfoil body 200 directly to the nozzle segment assembly 100, forces may react directly between the engine and the airfoil body 200 rather than reacting forces through the joints 223 and 243 with the outer band 110, the inner band 160, or both, which may result in increased local stresses in the airfoil body 200.

[0083] Reference again Figure 5 and 6A , the nozzle segment assembly 100 may include an outer hanger 300 and an inner hanger 350 that may operate to position and at least partially constrain the airfoil assembly 102 within the nozzle segment assembly 100. The outer hanger 300, the inner hanger 350, or both may be part of a continuous ring centered on the central axis A of the engine 10. Alternatively or additionally, the outer hanger 300, the inner hanger 350, or both may be segments of a ring such that when multiple nozzle segment assemblies 100 are assembled together, multiple outer hangers 300 form an outer ring 52 and multiple inner hangers 350 form an inner ring 54 ( Figure 2 ).

[0084] Reference again Figure 5 and Fig. 6A As previously described, the outer end 220 of the airfoil body 200 may pass through the opening 116 in the outer band 110 so that the outer end 220 may extend radially outward from the radially outwardly facing surface 112 of the outer band 110 (ie, at Figure 5 and 6ASimilarly, the inner end 240 of the airfoil body 200 may pass through the opening 166 of the inner band 160 so that the inner end 240 may be radially inward (i.e., in the +r direction) from the radially inwardly facing surface 164 of the inner band 160. Figure 5 and 6A The outer hanger 300 may be configured to be engageable with at least the outer end 220 of the airfoil body 200, and the inner hanger 350 may be configured to be engageable with at least the inner end 240 of the airfoil body 200 to install the airfoil body 200 in the nozzle segment assembly 100. The engagement of the outer end 220 and the inner end 240 of the airfoil body 200 with the outer hanger 300 and the inner hanger 350, respectively, may enable forces to be directly transferred between the engine 10 and the airfoil body 200, rather than reacting forces through the outer band 110 and the inner band 160. In an embodiment, the outer hanger 300 may engage with the outer end 220 of at least one of the airfoil body 200 and the radially outward facing surface 112 of the outer band 110, for example, when the airfoil body 200 is mechanically separated from the outer band 110. In embodiments, the inner hanger 350 may engage the inner end 240 of at least one airfoil body 200 and the radially inward facing surface 164 of the inner band 160 , such as when the airfoil body 200 is mechanically separated from the inner band 160 .

[0085] Reference again Figure 5 and Fig. 6A The outer hanger 300 may have an outwardly facing surface 302 and an inwardly facing surface 304. The outer hanger 300 may be radially outward (ie, at the position of the outer end 220 of the outer band 110 and the airfoil body 200). Figure 5 and 6A 10 (in the +r direction of the coordinate axis of the airfoil) such that the inwardly facing surface 304 of the outer hanger 300 faces radially inwardly toward the outer end 220 of the airfoil body 200 and the radially outwardly facing surface 112 of the outer band 110. The inner hanger 350 may have an outwardly facing surface 352 and an inwardly facing surface 354. The inner hanger 350 may be radially inwardly (i.e., at the inner end 240 of the inner band 160 and the airfoil body 200) from the inner band 160. Figure 5 and 6A 160) such that the outwardly facing surface 352 of the inner hanger 350 faces radially outwardly toward the inner end 240 of the airfoil body 200 and the radially inwardly facing surface 164 of the inner band 160. The outer hanger 300 and the inner hanger 350 may be a different material than the CMC material of the outer band 110, the inner band 160, and the airfoil body 200. For example, the outer hanger 300, the inner hanger 350, or both may be a metal having a different coefficient of thermal expansion than the CMC material of the outer band 110, the inner band 160, and the airfoil body 200.

[0086] The outer hanger 300 may have one or more mounting features 310 that protrude from an inwardly facing surface 304 in a radially inward direction toward the outer end 220 of the airfoil body 200 and the radially outwardly facing surface 112 of the outer band 110. Similarly, the inner hanger 350 may include one or more mounting features 310 that protrude from an outwardly facing surface 352 in a radially outward direction toward the inner end 240 of the airfoil body 200 and the radially inwardly facing surface 164 of the inner band 160. Fig. 6A , each of the mounting features 310 may include a mounting surface 312 that may be oriented to contact a portion of the outer surface 202 of the airfoil body 200, or a surface of the outer band 110 or the inner band 160. The contact between the mounting surface 312 and the outer surface 202 of the airfoil body 200 may operate to position the airfoil assembly 102 and at least partially constrain the airfoil body 200, the outer band 110, the inner band 160, or a combination thereof in an axial direction, an angular direction, or both (i.e., in Figure 5 and 6A The inwardly facing surface 304 of the outer pylon 300 and the outwardly facing surface 352 of the inner pylon 350 may at least partially limit the movement of the airfoil assembly 102 in the radial direction (i.e., the + / -X direction, the + / -Theta direction, or both) relative to the outer pylon 300, the inner pylon 350, or both, while also transmitting forces between the outer pylon 300, the inner pylon 350, or both and the airfoil body 200. Figure 5 and 6A Movement in the + / -r direction of the coordinate axis.

[0087] Reference now Figure 6B , the nozzle segment assembly 100 may additionally include one or more struts 360 extending between the outer pylon 300 and the inner pylon 350. Each of the struts 360 may extend through the cavity 206 of one of the airfoil bodies 200 and may be mechanically coupled to the outer pylon 300, the inner pylon 350, or both.

[0088] Now refer to Figures 10A to 16B Various configurations of mounting features 310 for mounting the airfoil assembly 102 in the nozzle segment assembly 100 are described in further detail. Fig. 10A , 10B , 11A, 11B, 12A, 12B, 13A, 13B, 14A, 14B, 15A, 15B, 16A and 16B are along Fig. 6A10. A cross-sectional view taken along reference line 10-10 in FIG. 10. For ease of illustration, the cross-sectional view removes the body of the outer hanger 300 from view to better illustrate the positioning of the mounting features 310 relative to the airfoil body 200. However, it should be understood that the various mounting features 310 are mechanically and rigidly coupled to the outer hanger 300. The various mounting configurations will be described in the context of engagement between the outer end 220 of the airfoil body 200 and the outer hanger 300. However, it should be understood that any of the described mounting configurations may be applicable to engagement of the inner end 240 of the airfoil body 200 with the inner hanger 350.

[0089] Reference now Fig. 10A and 10B , an embodiment of the nozzle segment assembly 100 is shown in cross-sectional view. The outer hanger 300, the inner hanger 350, or both ( Fig. 6A ) may have a plurality of mounting features 310. The mounting features 310 may include one or more axial mounting members 320. Fig. 6A The axial mounting member 320 coupled to the outer hanger 300 may be radially inward (ie, at Fig. 6A The axial mounting member 320 coupled to the inner hanger 350 may be radially outward (i.e., in the -r direction) from the outwardly facing surface 352 of the inner hanger 350. Fig. 6A The coordinate axis of the Fig. 10A and 10B , each axial mount 320 may include an axial engagement surface 322 that engages at least a portion of the outer surface 202 or at least a portion of the inner surface 204 of the airfoil body 200. The engagement of the axial engagement surface 322 with the outer surface 202 or the inner surface 204 of the airfoil body 200 may at least partially limit the axial movement of the airfoil body 200 relative to the outer hanger 300 or the inner hanger 350. The engagement of the axial engagement surface 322 with the outer surface 202 or the inner surface 204 of the airfoil body 200 may at least partially limit the axial movement of the airfoil body 200 relative to the outer hanger 300 or the inner hanger 350 while still allowing axial expansion to accommodate thermal expansion differences between the CMC material of the airfoil body 200 and the metal or other non-CMC material of the outer hanger 300 and the inner hanger 350.

[0090] As previously described, the nozzle segment assembly 100 may include a plurality of airfoil bodies 200. When the nozzle segment assembly 100 includes a plurality of airfoil bodies 200, the outer hanger 300, the inner hanger 350, or both may each include a plurality of axial mounts 320, and the axial engagement surface 322 of each of the plurality of axial mounts 320 may engage the outer surface 202 or the inner surface 204 of one of the airfoil bodies 200. In an embodiment, the outer hanger 300, the inner hanger 350, or both may include at least one axial mount 320 for each of the airfoil bodies 200.

[0091] refer to Fig. 10B , the axial engagement surface 322 of each axial mounting member 320 may at least partially face the axial direction (ie, at least partially face the Fig. 10B 0 in the + / -X direction of the coordinate axis in the axial mounting member 320). A line perpendicular to the plane of the axial engaging surface 322 of the axial mounting member 320 is not perpendicular to the axial direction (e.g., the line perpendicular to the axial engaging surface 322 has a non-zero vector component in the + / -X direction). In other words, the line perpendicular to the plane of the axial engaging surface 322 is not perpendicular to the axial line passing through the point (i.e., a line parallel to the central axis A of the engine 10) at which the line perpendicular to the plane of the axial engaging surface 322 passes through the plane of the axial engaging surface 322. In an embodiment, the axial mounting member 320 may be oriented such that the axial engaging surface 322 of at least one axial mounting member 320 may be aligned with a contour of a portion of the outer surface 202 of the airfoil body 200. In an embodiment, the line perpendicular to the axial engaging surface 322 of the axial mounting member 320 may be non-parallel to the axial direction (i.e., a line parallel to the central axis A of the engine 10) such that the axial engaging surface 322 forms an angle with the axial direction. In other words, a line perpendicular to the plane of the axial engagement surface 322 may include a non-zero vector component in the radial direction (+ / -r direction) and / or in the tangential direction (i.e., along a line tangent to a circle centered on the central axis A of the engine 10 and passing through the point where the normal intersects the plane of the axial engagement surface 322). Fig. 10A and 10B In an embodiment, the axial mount 320 may be positioned to engage the outer surface 202 of the airfoil body 200 at the suction side 218 of the airfoil body 200 .

[0092] Reference again Fig. 10A and 10B , the mounting feature 310 may include one or more tangential mounting members 330. Fig. 10A and 10B As shown, the outer hanger 300, the inner hanger 350, or both may include at least one tangential mount 330. The tangential mount 330 coupled to the outer hanger 300 may extend radially inward (i.e., at the inner surface 304 of the outer hanger 300). Fig. 10A and 10B The tangential mounting member 330 coupled to the inner hanger 350 may extend radially outward (i.e., in the -r direction) from the outwardly facing surface 352 of the inner hanger 350. Fig. 10A and 10B Each tangential mount 330 may include a tangential engagement surface 332 that may engage at least a portion of an outer surface 202 or an inner surface 204 of at least one of the airfoil bodies 200. The engagement of the tangential engagement surface 332 of the tangential mount 330 with the outer surface 202 or the inner surface 204 of the airfoil body 200 may at least partially limit tangential or angular movement of the airfoil body 200 relative to the outer hanger 300 or the inner hanger 350. The engagement of the tangential engagement surface 332 with the outer surface 202 or the inner surface 204 of the airfoil body 200 may at least partially limit tangential or angular movement of the airfoil body 200 relative to the outer hanger 300 or the inner hanger 350 while still allowing axial expansion to accommodate thermal expansion differences between the CMC material of the airfoil body 200 and the metal or other non-CMC material of the outer hanger 300 and the inner hanger 350.

[0093] In an embodiment, each nozzle segment assembly 100 may include a single tangential mount 330 coupled to the outer hanger 300 and a single tangential mount 330 coupled to the inner hanger 350. When the nozzle segment assembly 100 includes multiple airfoil bodies 200, a single 330 on the outer hanger 300 and a single 330 on the inner hanger 350 may be sufficient to constrain tangential or angular movement of the airfoil assembly 102 relative to the outer hanger 300 and the inner hanger 350, respectively. When each nozzle segment assembly 100 includes multiple airfoil bodies 200, including a tangential mount 330 for each airfoil body 200 on the outer hanger 300 and the inner hanger 350 may over-constrain the airfoil assembly 102.

[0094] The tangential engagement surface 332 of the tangential mount 330 may be at least partially tangentially oriented (e.g., Fig. 10A and 10B The tangential direction may be along the direction of the engine 10 ( Figure 1 ) as the central axis A and passing through the tangential engagement surface 332. In other words, a line perpendicular to the tangential engagement surface 332 may have a non-zero vector component in the tangential and / or angular directions. In an embodiment, at least one tangential mount 330 may be positioned to engage the outer surface 202 of at least one airfoil body 200 proximate the leading edge 210 at the suction side 218 of at least one airfoil body 200.

[0095] In an embodiment, the outer hanger 300 may include at least one tangential mount 330 extending radially inward from the inwardly facing surface 304 of the outer hanger 300. In an embodiment, the inner hanger 350 may include at least one tangential mount 330 extending radially outward from the outwardly facing surface 352 of the inner hanger 350. Fig. 10A and 10B As shown, the combination of the axial mounts 320 and the tangential mounts 330 may cooperate to constrain the airfoil assembly 102 in the axial and angular directions relative to the outer pylon 300 and the inner pylon 350 .

[0096] Reference now Fig.11A and 11B , the outer hanger 300, the inner hanger 350, or both may not include the tangential mount 330. Instead, the nozzle segment assembly 100 may include a pin 340 that may be inserted through a bore 342 that extends through one of the axial mounts 320 and through at least a portion of one of the airfoil bodies 200. The pin 340 is operable to engage the airfoil body 200 and the axial mount 320 to provide a tangential connection between the airfoil body 200 and the nozzle segment. Fig.11A and 11B In other words, engagement of the pin 340 with one airfoil body 200 and one axial mount 320 may limit movement of one airfoil body 200 and airfoil assembly 102 relative to the outer hanger 300 or the inner hanger 350 in an angular or tangential direction.

[0097] When the pin 340 is used to constrain the airfoil assembly 102 in the angular / tangential direction, the axial mount 320 through which the pin 340 is inserted may have a substantially angular orientation relative to the axial direction (ie, Fig.11A In other words, the axial mount 320 may be angled relative to the axial direction such that a line perpendicular to the axial engagement surface 322 of the axial mount 320 may not be parallel to the axial direction (i.e., a line parallel to the central axis A of the engine 10). In an embodiment, a line perpendicular to the plane of the axial engagement surface 322 may include a non-zero vector component in at least a tangential direction (i.e., a line tangent to a circle centered on the central axis A of the engine 10 and passing through the point where the normal intersects the plane of the axial engagement surface 322).

[0098] Reference now Fig. 11C , Fig. 11B The cross section of the nozzle segment assembly 100 is along Fig. 11B The reference line 11C-11C in FIG. Fig. 11CAs shown, the pin 340 may extend through a bore 342 that extends through a portion of the airfoil body 200 and the axial mount 320 to provide a tangential / angular connection relative to the airfoil body 200. Fig. 11C The outer hanger 300 in the axial mount 320 at least partially constrains the airfoil body 200. Although not shown, the pin 340 may be fixed or retained in the bore 342 by any means known in the art for such purposes, and the method of fixing the pin 340 in the bore 342 is not particularly limited. Non-limiting examples may include incorporating flanges on one or both ends of the pin 340, such as utilizing rivets or using fasteners such as snap rings, split pins, clips, etc. on one or both ends of the pin 340. In an embodiment, one end of the pin 340 may be press-fit or friction-fit into a portion of the bore 342 in the axial mount 320, and the other end of the pin 340 may be inserted into the other portion of the bore in the airfoil body 200, but is not mechanically and rigidly coupled to the airfoil body 200. Other methods of fixing the pin 340 in the bore 342 will be apparent to those of ordinary skill in the art.

[0099] When the nozzle segment assembly 100 includes multiple airfoil bodies 200, the nozzle segment assembly 100 may include only a single pin 340 for the outer hanger 300, the single pin 340 engaging a single airfoil body 200 and a single axial mount 320. The outer hanger 300 may include multiple axial mounts 320, but may include only one pin 340. Likewise, the inner hanger 350 may also include a single pin 340 engaging a single airfoil body 200 and a single axial mount 320 coupled to the inner hanger 350. Multiple pins 340 used on either the outer hanger 300 or the inner hanger 350 may result in over-constraint of the airfoil assembly 102 relative to the outer hanger 300 and / or the inner hanger 350.

[0100] Reference now Fig. 12A and 12B , schematically depicts another mounting configuration for mounting the airfoil body 200 directly to the outer hanger 300 and / or the inner hanger 350. Fig. 12A and 12B As shown, in an embodiment, one or more of the axial mounting members 320 can be oriented so that the axial engagement surface 322 is in the axial direction (ie, in Fig. 12A and 12BIn an embodiment, the plane of the axial engagement surface 322 may be perpendicular to the axial direction. In an embodiment, a line perpendicular to the axial engagement surface 322 may be parallel to a plane formed by the axial direction (+ / -X direction) and the radial direction (+ / -r direction) at the axial engagement surface 322. In an embodiment, the axial engagement surface 322 may be parallel to the tangential direction (i.e., parallel to a line tangent to a circle centered on the central axis A of the engine and passing through the axial engagement surface 322). In an embodiment, a line perpendicular to the axial engagement surface 322 may have a vector component that is substantially zero in the tangential direction. However, in an embodiment, a line perpendicular to the axial engagement surface 322 may have a non-zero vector component in the radial direction.

[0101] At least one of the airfoil bodies 200 may include an axially facing outer surface 230 at the outer end 220, the inner end 240, or both of the airfoil body 200. The axially facing outer surface 230 may be oriented to engage with an axial engagement surface 322 of an axial mount 320. The engagement of the axially facing outer surface 230 with the axial engagement surface 322 of the axial mount 320 may at least partially constrain the airfoil body 200 in the axial direction. An axial mount 320 (e.g., having an axial engagement surface 322 that is angled relative to the axial direction) may be used to at least partially constrain the airfoil body 200. Fig. 10A and 10B The engagement between the axially facing outer surface 230 and the axial engagement surface 322 may provide a more definitive and stable axial restraint of the airfoil body 200 as compared to the illustrated embodiment.

[0102] Reference again Fig. 12A and 12B , the axially facing outer surface 230 of the airfoil body 200 may be the surface of a protrusion 232 extending from the outer surface 202 of the airfoil body 200 at the outer end 220, the inner end 240, or both. The protrusion 232 may be integrally formed as a part of the airfoil body 200 or may be formed separately and bonded to the airfoil body 200. In an embodiment, the protrusion 232 may be formed on or bonded to the airfoil body 200 proximate the trailing edge 212 of the airfoil body 200. The protrusion 232 may additionally provide a radially facing surface that may provide a secondary retention feature that may be used to at least partially constrain the airfoil body 200 in a radially outward direction.

[0103] In an embodiment, the nozzle segment assembly 100 may include a plurality of airfoil bodies 200, each airfoil body 200 having an axially facing outer surface 230, and the outer hanger 300, the inner hanger 350, or both may each include a plurality of axial mounts 320, the plurality of axial mounts 320 may be oriented such that the axial engagement surface 322 is oriented in the axial direction (i.e., in the Fig. 12A and 12B The outer pylon 300, the inner pylon 350, or both may additionally include at least one tangential mount 330 operable to move the outer pylon 300 in a tangential / angular direction (e.g., in the + / -X direction of the cylindrical coordinate axis of the airfoil) and engage with an axially facing outer surface 230 of one of the airfoil bodies 200. The outer pylon 300, the inner pylon 350, or both may additionally include at least one tangential mount 330 operable to move the outer pylon 300 in a tangential / angular direction (e.g., in the Fig. 12A and 12B The airfoil assembly 102 is constrained in the + / -Theta direction of the coordinate axis in FIG.

[0104] Reference now Fig.13A and 13B In embodiments, the tangential mounts 330 of the outer pylons 300 and / or the inner pylons 350 may engage a tangentially facing surface 402 of a spine 400 extending from the outer band 110, the inner band 160, or both. The engagement between the tangentially facing surface 402 of the spine 400 and the tangential mounts 330 may at least partially constrain the airfoil assembly 102 in a tangential and / or angular direction relative to the outer pylons 300, the inner pylons 350, or both. In these embodiments, the airfoil assembly 102 may be constrained in a tangential and / or angular direction by engagement between the tangential mounts 330 and the outer band 110, the inner band 160, or both, rather than engagement of the tangential mounts 330 directly with one of the airfoil bodies 200.

[0105] The outer band 110 may have a ridge 400 extending radially outward from a radially outward facing surface 112 of the outer band 110. The ridge 400 may include a tangentially facing surface 402 that may be generally tangentially oriented (e.g., in the Fig.13A and 13B The ridges 400 may be formed integrally with the outer band 110, or may be formed separately and bonded to the radially outwardly facing surface 112 of the outer band 110. The outer hanger 300 may include a tangential mount 330 having a tangential engagement surface 332 that may be substantially parallel to the axial direction (e.g., parallel to Figure 1 The tangential mount 330 may be positioned on the outer pylon 300 such that the tangential engagement surface 332 may engage the tangentially facing surface 402 of the ridge 400 when the nozzle segment assembly 100 is assembled. Fig. 13C Schematically depicts the Fig. 13B A cross-sectional view of a portion of the nozzle segment assembly 100 taken along reference line 13C-13C in FIG. Fig. 13C The interaction between the tangential mounts 330 and the ridges 400 is schematically illustrated to constrain the airfoil assembly 102 in the tangential and / or angular directions.

[0106] Despite Figures 13A-13C164, but alternatively or additionally, the radially inwardly facing surface 164 of the inner band 160 may also include a ridge 400 extending radially inwardly from the radially inwardly facing surface 164 of the inner band 160. The ridge 400 may include a tangentially facing surface 402, which may generally face in a tangential direction. The ridge 400 may be integrally formed with the inner band 160, or may be formed separately and bonded to the radially inwardly facing surface 164 of the inner band 160. The inner hanger 350 may include a tangential mount 330 having a tangential engagement surface 332 that is generally parallel to the axial direction (e.g., parallel to the Figure 1 The tangential mount 330 may be positioned on the inner hanger 350 such that the tangential engagement surface 332 may engage the tangentially facing surface 402 of the ridge 400 on the inner band 160 when the nozzle segment assembly 100 is assembled. Fig.13A and 13B The embodiments shown in can have any axial mounting configuration disclosed herein.

[0107] Reference now Figures 14A to 14C In an embodiment, the airfoil body 200 may be a hollow airfoil body having a cavity 206 defined by the inner surface 204 of the airfoil body 200. One or more mounting features 310 may be positioned to extend into the cavity 206 defined by the inner surface 204 of the airfoil body 200 such that a mounting surface 312 of at least one mounting feature 310 may engage at least a portion of the inner surface 204 of the airfoil body 200. The engagement of the mounting surface 312 of the mounting feature 310 with the inner surface 204 of the airfoil body 200 may at least partially constrain the airfoil body 200 and the airfoil assembly 102 at least in the axial direction. Depending on the positioning of the mounting feature 310 within the cavity 206 of the airfoil body 200, the mounting feature 310 may additionally constrain the airfoil body 200 and the airfoil assembly 102 in the tangential and / or angular directions. The mounting feature 310 may be an axial mount 320, a tangential mount 330, or both, depending on the orientation of the mounting surface 312 relative to the inner surface 204 of the airfoil body 200. In some embodiments, the mounting feature 310 may be a post (e.g., a post) that extends all the way through the cavity 206 and is coupled to the outer hanger 300 and the inner hanger 350. Figure 6B 360). Again, refer to Figures 14A-14C, the outer hanger 300, the inner hanger 350, or both may each include one or more mounting features 310 extending into the cavity 206 of one of the airfoil bodies 200. In conjunction with any of the tangential and / or angular restraint methods disclosed herein (such as, but not limited to, engaging a tangential mount 330 with the outer surface 202 of one of the airfoil bodies 200 or with a ridge on the outer band 110, the inner band 160, or both), the airfoil assembly 102 may be axially restrained relative to the outer hanger 300, the inner hanger 350, or both by incorporating mounting features 310 extending into the cavity 206 of the airfoil body 200 to engage the inner surface 204 of the airfoil body 200.

[0108] Reference now Figures 15A-15C In an embodiment, the tangential mounts 330 of the outer hanger 300, the inner hanger 350, or both may be positioned to engage the trailing edge 212 of the airfoil body 200 at the outer end 220 or the inner end 240 of the airfoil body, respectively. The outer hanger 300, the inner hanger 350, or both may include at least one tangential mount 330 including a tangential engagement surface 332 that engages at least a portion of the outer surface 202 at the trailing edge 212 of at least one of the airfoil bodies 200. The engagement of the tangential mount 330 with the outer surface 202 at the trailing edge 212 of the airfoil body 200 may at least partially constrain movement of at least one airfoil body 200 and the airfoil assembly 102 in a tangential and / or angular direction relative to the outer hanger 300, the inner hanger 350, or both.

[0109] At least one of the airfoil bodies 200 may include a tangentially facing surface 234 disposed proximate the trailing edge 212 of the airfoil body 200. The tangentially facing surface 234 may be at least partially oriented in a tangential direction (eg, generally in the Figures 15A-15C 200). However, in embodiments, a line perpendicular to the tangentially facing surface 234 of the airfoil body 200 may have a non-zero vector component in the radial direction (+ / -r direction), the axial direction (+ / -X direction), or both. The outer end 220, the inner end 240, or both of the airfoil body 200 may include a tangentially facing surface 234 positioned to engage a tangential engagement surface 332 of a tangential mount 330 on the outer hanger 300, the inner hanger 350, or both, respectively. The positioning of the tangential mount 330 engaging the outer surface 202 of the airfoil body 200 at the leading edge 210 or the trailing edge 212 may be determined by the shape of the outer surface 202 of the airfoil body 200, which may affect the direction of the load pushing on the airfoil body 200.

[0110] Reference now Fig.16A and 16B, schematically depicts another configuration for mounting and / or restraining an airfoil assembly 102 in a nozzle segment assembly 100. Fig.16A and 16B As shown, in an embodiment, the nozzle segment assembly 100 may include a plurality of airfoil bodies 200. The nozzle segment assembly 100 may additionally include a mounting rod 410 that may be mechanically coupled and / or bonded to the outer ends 220 of all of the plurality of airfoil bodies 200 of the nozzle segment assembly 100 or the inner ends 220 of all of the plurality of airfoil bodies 200 of the nozzle segment assembly 100. The nozzle segment assembly 100 may have two mounting rods 410: one mounting rod 410 coupled to the outer ends 220 of the airfoil bodies 200 and a second mounting rod 410 coupled to the inner ends 240 of the airfoil bodies 200. Alternatively or additionally, in an embodiment, the mounting rod 410 may be bonded to the radially outwardly facing surface 112 of the outer band 110 or the radially inwardly facing surface 164 of the inner band 160. In an embodiment, each mounting rod 410 may conform to the slightly curved contour of the radially outwardly facing surface 112 of the outer band 110 or the radially inwardly facing surface 164 of the inner band 160. The mounting rods 410 may extend the entire angular length of the nozzle segment assembly 100 such that the mounting rods 410 may form a seal between the band member (outer band 110 or inner band 160) and the adjacent hanger (outer hanger 300 or inner hanger 350, respectively).

[0111] Each mounting rod 410 may include a mounting rod axial surface 412 that may at least partially face the axial direction. In an embodiment, the mounting rod axial surface 412 may directly face the axial direction (e.g., a line perpendicular to the mounting rod axial surface 412 may be at least partially facing the axial direction). Fig.16A and 16B The mounting rod axial surface 412 may engage with the axial engagement surface 322 of one or more axial mounts 320. The engagement of the mounting rod axial surface 412 with the axial engagement surface 322 of one or more axial mounts 320 may at least partially constrain the airfoil body 200 and the airfoil assembly 102 at least in the axial direction (i.e., Fig.16A and 16B The + / -X direction of the coordinate axis in the engine 10 is parallel to the central axis A) of the engine 10.

[0112] Reference now Fig.17 Each of the plurality of airfoil bodies 200 may additionally be arranged in a radial direction (ie, in Fig.17In an embodiment, the airfoil body 200 may be constrained in the radial direction by contact between the outer end surface 214 of the airfoil body 200 and the inwardly facing surface 304 of the outer hanger 300 and / or between the inner end surface 216 of the airfoil body 200 and the outwardly facing surface 352 of the inner hanger 350. The outer end surface 214 may be a radially outwardly facing surface at the outer end 220 of the airfoil body 200. The inner end surface 216 may be a radially inwardly facing surface at the inner end 240 of the airfoil body 200.

[0113] Reference again Fig.17 In an embodiment, at least one of the airfoil bodies 200 may include a pin hole 420 in the outer surface 202 of the airfoil body 200 proximate one of the outer end 220 or the inner end 240 and a slot 422 in the outer surface 202 of the airfoil body 200 proximate the other of the outer end 220 or the inner end 240. Each of the pin hole 420 and the slot 422 may be shaped to receive a locating pin (not shown) coupled to the outer hanger 300 or the inner hanger 350. The engagement of the locating pin (not shown) with the pin hole 420 and the slot 422 may operate to properly position the airfoil assembly 102 relative to the outer hanger 300 and the inner hanger 350, and may at least partially constrain the airfoil assembly 102 in at least a radial direction. The slot 422 may enable one end of the airfoil body 200 to move in an axial and / or angular direction to prevent over-constraining of the airfoil assembly 102. Fig.17 The outer end 220 of the airfoil body 200 is shown with a pin hole 420 and the inner end 240 with a slot 422. However, it is understood that the inner end 240 of the airfoil body 200 may have the pin hole 420 and the outer end 220 of the airfoil body 200 may have the slot 422. In some embodiments, each nozzle segment assembly 100 may include multiple airfoil bodies 200. In these embodiments, only one of the airfoil bodies 200 may include the pin hole 420 and the slot 422. Any of these mounting configurations may be used to mount an airfoil assembly 102 having 1, 2, 3, 4, or more than 4 airfoil bodies 200.

[0114] As previously described, each of the airfoil bodies 200 may be mechanically and rigidly coupled to the outer band 110 and the inner band 160. When the airfoil bodies 200 are mechanically and rigidly coupled to the outer band 110 and the inner band 160, mounting and constraining the airfoil bodies 200 through the interaction of the outer end 220 and the inner end 240 with the outer pylon 300 and the inner pylon 350, respectively, may be sufficient to constrain the outer band 110 and the inner band 160. In other words, the engagement of the outer pylon 300 with the outer end 220 of the airfoil body 200 and the inner pylon 350 with the inner end 240 of the airfoil body 200 may enable forces to be transferred between the engine 10 and the airfoil body 200, in which case the outer band 110 and the inner band 160 are positioned and carried together with the airfoil body 200 by being mechanically coupled to the airfoil body 200.

[0115] However, when the airfoil body 200 is mechanically decoupled from the outer and inner bands 110 , 160 , additional structure may be employed to properly position and restrain the outer and inner bands 110 , 160 relative to the airfoil body 200 , outer hanger 300 , and inner hanger 350 .

[0116] Reference now Fig.18A and 18B , the airfoil body 200 may be mechanically decoupled from the outer band 110, the inner band 160, or both. In other words, at least before the airfoil assembly 102 is mounted to the outer hanger 300 and the inner hanger 350 to form the nozzle segment assembly 100, the outer band 110, the inner band 160, or both may be able to move relative to the airfoil body 200 in at least one of a radial direction, an axial direction, or an angular direction. The outer band 110 may include at least one outer band flange 130 projecting radially outward from the radially outward facing surface 112. At least one of the outer band flanges 130 may be positioned to engage at least one axial mount 320 coupled to the outer hanger 300. The engagement between the outer band flange 130 and the axial mount 320 coupled to the outer hanger 300 may at least partially constrain axial movement of the outer band 110 relative to the outer hanger 300. Additionally, the inner band 160 may include at least one inner band flange 180 that projects radially inward from the radially inward facing surface 164 of the inner band 160. At least one of the inner band flanges 180 may be positioned to engage at least one axial mount 320 coupled to the inner hanger 350. The engagement between the inner band flange 180 and the axial mount 320 coupled to the inner hanger 350 may at least partially constrain axial movement of the inner band 160 relative to the inner hanger 350.

[0117] Reference now Fig.19A and 19B , schematically depicting two perspective views of the outer belt 110. Fig.19AIn an embodiment, the outer band flange 130 may have a radially facing surface 132 that may engage the inwardly facing surface 304 of the outer hanger 300. The engagement of the radially facing surface 132 of the outer band flange 130 with the inwardly facing surface 304 of the outer hanger 300 may at least partially constrain the movement of the outer band 110 in a radially outward direction relative to the outer hanger 300. Fig.19B Alternatively or additionally, in an embodiment, the outer belt flange 130 may include one or more outer belt flange pin holes 134 extending at least partially through the outer belt flange 130. The outer belt flange pin holes 134 may be shaped to receive metal pins (not shown). The metal pins may be coupled to the mounting features 310 ( Fig. 6A ) (e.g., but not limited to, axial mount 320), and a portion of the metal pin may be received in the outer band flange pin hole 134 of the outer band flange 130. The engagement of the metal pin in the outer band flange pin hole 134 of the outer band flange 130 may at least partially constrain the movement of the outer band 110 in the radial direction relative to the outer hanger 300. The engagement of the metal pin in the pin hole 134 of the outer band flange 130 may also at least partially constrain the outer band 110 in the tangential / angular direction (e.g., in Fig.19B Movement of the outer hanger 300 in the + / -Theta direction of the coordinate axes in the coordinate system.

[0118] Although not depicted in the figures, it should be understood that the inner band flange 180 of the inner band 160 can also include a radially facing surface that can engage the outwardly facing surface 352 of the inner hanger 350 to at least partially constrain the movement of the inner band 160 in a radially inward direction relative to the inner hanger 350. The inner band flange 180 can also include one or more inner band flange pin holes (not shown) extending at least partially through one or more of the inner band flanges 180. The inner band flange pin holes can be shaped to receive a metal pin (not shown). The metal pin can be coupled to the mounting feature 310 ( Fig. 6A ) (such as but not limited to the axial mount 320), and a portion of the metal pin can be received in the inner belt flange pin hole of the inner belt flange 180. The engagement of the metal pin in the inner belt flange pin hole of the inner belt flange 180 can at least partially constrain the movement of the inner band 160 in the radial direction relative to the inner hanger 350. The engagement of the metal pin in the inner belt flange pin hole of the inner belt flange 180 can also at least partially constrain the movement of the inner band 160 in the tangential / angular direction relative to the inner hanger 350.

[0119] The methods and structures for installing the outer band 110, the inner band 160, or both in the nozzle segment assembly 100 when the outer band 110, the inner band 160, or both are separated from the airfoil body 200 may be used in conjunction with any one or more of the configurations for mounting the airfoil body 200 to the outer pylon 300, the inner pylon 350, or both previously described herein.

[0120] A first aspect of the present disclosure may include a nozzle segment assembly for a gas turbine engine. The nozzle segment assembly may include an airfoil assembly having an outer band, an inner band, and at least one airfoil body extending between the outer band and the inner band. At least one airfoil body may include an outer end extending through the outer band and having an outer end reinforcing wall portion protruding from an outer surface of at least one airfoil body to engage with the outer band. At least one airfoil body may also include an inner end extending through the inner band and having an inner end reinforcing wall portion protruding from an outer surface of at least one airfoil body to engage with the inner band. The thickness of the outer end reinforcing wall portion and the thickness of the inner end reinforcing wall portion may both be greater than the thickness of the central wall portion of at least one airfoil body, and the outer band, the inner band, and at least one airfoil body may include a ceramic matrix composite (CMC) material.

[0121] A second aspect of the present disclosure may include the first aspect, wherein the at least one airfoil body may include a plurality of airfoil bodies.

[0122] A third aspect of the present disclosure may include any of the first or second aspects, wherein the outer end reinforcing wall portion, the inner end reinforcing wall portion, or both may extend around the outer surface of at least one airfoil body at the junction between at least one airfoil body and the outer band, the inner band, or both, respectively.

[0123] A fourth aspect of the present disclosure may include any one of the first to third aspects, wherein the outer end reinforcement wall portion of at least one airfoil body may include an outer end flange extending from the outer surface at the outer end reinforcement wall portion, the outer end flange including a radially outer surface that abuts a portion of the radially inward facing surface of the outer band, or the inner end reinforcement wall portion of at least one airfoil body may include an inner end flange extending from the outer surface at the inner end reinforcement wall portion, the inner end flange including a radially inner surface that abuts a portion of the radially outward facing surface of the inner band.

[0124] A fifth aspect of the present disclosure may include the fourth aspect, wherein the radially inward facing surface of the outer band may include a recess providing a radial engagement surface that abuts against the radially outer surface of the outer end flange of at least one airfoil body, or the radially outward facing surface of the inner band may include a recess providing a radial engagement surface that abuts against the radially inner surface of the inner end flange of at least one airfoil body.

[0125] The sixth aspect of the present disclosure may include any one of the fourth to fifth aspects, wherein the radially outer surface of the outer end flange abuts against the radially inward facing surface of the outer band to limit the radial movement of the outer band in the radially inward direction relative to the position of at least one airfoil body, or the radially inner surface of the inner end flange abuts against the radially outward facing surface of the inner band to limit the radial movement of the inner band in the radially outward direction relative to the position of at least one airfoil body.

[0126] A seventh aspect of the present disclosure may include any one of the first to sixth aspects, wherein the outer band can be directly mechanically connected to the outer surface of at least one airfoil body at the outer end reinforcing wall portion, and the inner band can be directly mechanically connected to the outer surface of at least one airfoil body at the inner end reinforcing wall portion.

[0127] An eighth aspect of the present disclosure may include any one of the first to sixth aspects, further including an inner hanger, an outer hanger, or both, wherein the inner hanger may be engaged with at least an inner end of at least one airfoil body, and the outer hanger may be engaged with at least an outer end of at least one airfoil body.

[0128] A ninth aspect of the present disclosure may include any one of aspects one to eight, wherein at least a portion of an outer end of at least one airfoil body may protrude radially outward from a radially outwardly facing surface of an outer band, and / or at least a portion of an inner end of at least one airfoil body may protrude radially inward from a radially inwardly facing surface of an inner band.

[0129] The tenth aspect of the present disclosure may include any aspect of the eighth or ninth aspect, wherein the inner hanger may engage with the inner end of at least one airfoil body and the radially inward facing surface of the inner band, and / or the outer hanger may engage with the outer end of at least one airfoil body and the radially outward facing surface of the outer band.

[0130] An eleventh aspect of the present disclosure may include any one of the eighth to tenth aspects, wherein the inner hanger, the outer hanger, or both may include at least one axial mount having an axial engagement surface that engages with at least a portion of an outer surface or at least a portion of an inner surface of at least one airfoil body, the engagement limiting axial movement of at least one airfoil body relative to the inner hanger, the outer hanger, or both.

[0131] A twelfth aspect of the present disclosure may include the eleventh aspect, wherein the outer hanger may include at least one axial mount extending radially inwardly from a radially inwardly facing surface of the outer hanger.

[0132] A thirteenth aspect of the present disclosure may include any of the eleventh aspect or the twelfth aspect, wherein the inner hanger may include at least one axial mount extending radially outward from a radially outward facing surface of the inner hanger.

[0133] The fourteenth aspect of the present disclosure may include any one of the eleventh to thirteenth aspects, wherein the axial engagement surface of at least one axial mounting member may at least partially face the axial direction, or a line perpendicular to the plane of the axial engagement surface of the axial mounting member is not perpendicular to the axial direction.

[0134] A fifteenth aspect of the present disclosure may include any one of aspects eleven to fourteen, including a plurality of airfoil bodies, wherein the inner hanger, the outer hanger, or both may include a plurality of axial mounts, and an axial engagement surface of each of the plurality of axial mounts engages with an outer surface or an inner surface of one of the plurality of airfoil bodies.

[0135] A sixteenth aspect of the present disclosure may include any one of aspects eleven to fifteen, wherein at least one axial mount may be oriented so that an axial engagement surface of at least one axial mount may be aligned at an outer end or an inner end with a contour of a portion of an outer surface or a portion of an inner surface of at least one airfoil body.

[0136] A seventeenth aspect of the present disclosure may include any one of the eleventh to sixteenth aspects, wherein a line perpendicular to the axial engagement surface of at least one axial mount may not be parallel to the axial direction.

[0137] An eighteenth aspect of the present disclosure may include any one of the eleventh to sixteenth aspects, wherein a line perpendicular to the axial engagement surface of at least one axial mount may be parallel to a plane formed by a radial direction and an axial direction.

[0138] A nineteenth aspect of the present disclosure may include the eighteenth aspect, wherein at least one airfoil body may include an axially facing outer surface at an outer end, an inner end, or both of at least one airfoil body, the axially facing outer surface oriented to engage with an axial engagement surface of at least one axial mount.

[0139] A twentieth aspect of the present disclosure may include the nineteenth aspect, wherein the axially facing outer surface may include a surface of a projection extending from an outer surface of the at least one airfoil body at an outer end, an inner end, or both.

[0140] A twenty-first aspect of the present disclosure may include the eighteenth aspect, including a plurality of airfoil bodies and at least one mounting rod mechanically coupled to the outer ends of all of the airfoil bodies in the plurality of airfoil bodies or coupled to the inner ends of all of the airfoil bodies in the plurality of airfoil bodies. The mounting rod may include an axial surface of the mounting rod positioned to engage an axial engagement surface of at least one axial mount, engagement of the axial surface of the mounting rod with the axial engagement surface of the at least one axial mount at least partially constraining axial movement of the plurality of airfoil bodies relative to the outer hanger or the inner hanger.

[0141] The twenty-second aspect of the present disclosure may include any one of aspects eleven to seventeen, wherein at least one of the axial mounting members may extend into a cavity defined by an inner surface of at least one airfoil body so that an axial engagement surface of at least one axial mounting member may engage with at least a portion of the inner surface of at least one airfoil body.

[0142] A twenty-third aspect of the present disclosure may include any one of aspects 11 to 22, further comprising at least one pin extending through at least a portion of an outer end or an inner end of at least one airfoil body and at least one axial mount. Engagement of the at least one pin with a portion of an outer end or an inner end of at least one airfoil body and at least one axial mount may at least partially constrain movement of the at least one airfoil body in a tangential direction relative to the outer hanger or the inner hanger, respectively.

[0143] The twenty-fourth aspect of the present disclosure may include any one of the eighth to twenty-third aspects, wherein the outer hanger, the inner hanger or both may further include at least one tangential mounting member, the at least one tangential mounting member including a tangential engagement surface engaged with at least a portion of an outer surface or at least a portion of an inner surface of at least one airfoil body, the engagement at least partially constraining tangential movement of at least one airfoil body relative to the outer hanger, the inner hanger or both, respectively.

[0144] A twenty-fifth aspect of the present disclosure may include the twenty-fourth aspect, wherein the outer hanger may include at least one tangential mount extending radially inward from a radially inward facing surface of the outer hanger.

[0145] A twenty-sixth aspect of the present disclosure may include any of the twenty-fourth or twenty-fifth aspects, wherein the inner hanger may include at least one tangential mount extending radially outward from a radially outward facing surface of the inner hanger.

[0146] A twenty-seventh aspect of the present disclosure may include any of aspects twenty-four to twenty-six, wherein at least one tangential mount may be positioned to engage an outer surface of at least one airfoil body proximate a leading edge of the at least one airfoil body.

[0147] A twenty-eighth aspect of the present disclosure may include any of aspects twenty-four to twenty-six, wherein at least one tangential mount may be positioned to engage an outer surface of at least one airfoil body proximate a trailing edge of the at least one airfoil body.

[0148] A twenty-ninth aspect of the present disclosure may include aspect twenty-eight, wherein at least one airfoil body includes a tangentially facing surface proximate a trailing edge of at least one airfoil body, the tangentially engaging surface engaging the tangentially facing surface to at least partially constrain tangential movement of at least one airfoil body relative to an outer hanger, an inner hanger, or both.

[0149] A thirtieth aspect of the present disclosure may include any of aspects eleven to twenty-third, wherein the outer band may include a ridge extending radially outward from a radially outward facing surface, the ridge including a tangentially facing surface. The outer hanger may include at least one tangential mount extending radially inward from a radially inward facing surface of the outer hanger, wherein the tangential mount may include a tangential engagement surface. The tangential engagement surface of the tangential mount may engage with the tangentially facing surface of the ridge to limit tangential movement of the outer band relative to the outer hanger.

[0150] A thirty-first aspect of the present disclosure may include any of the first to twenty-third or thirtieth aspects, wherein the inner band may include a ridge extending radially inward from a radially inward facing surface, the ridge including a tangentially facing surface. The inner hanger may include at least one tangential mount extending radially outward from a radially outward facing surface of the inner hanger, wherein the tangential mount may include a tangential engagement surface. The tangential engagement surface of the tangential mount may engage with the tangentially facing surface of the ridge to limit tangential movement of the inner band relative to the inner hanger.

[0151] Aspect thirty-second of the present disclosure may include any one of aspects eight to thirty-first, wherein one of the inner end or the outer end of at least one airfoil body may include a locating pin hole, the other of the inner end or the outer end may include a locating slot, and the locating pin hole and the locating slot may be operated to position at least one airfoil body within the nozzle segment assembly, constrain at least one airfoil body in a radial direction, or both.

[0152] The thirty-third aspect of the present disclosure may include any one of the eighth to thirty-second aspects, wherein the outer end surface and the inner end surface of at least one airfoil body may be respectively engaged with the outer hanger and the inner hanger to constrain the at least one airfoil body in the radial direction.

[0153] The thirty-fourth aspect of the present disclosure may include any one of the first to sixth aspects or the eighth to thirty-third aspects, wherein the outer surface of at least one airfoil body may be directly mechanically connected to the outer band, the inner band, or both at the outer end reinforcement wall portion, the inner end reinforcement wall portion, or both, respectively.

[0154] The thirty-fifth aspect of the present disclosure may include any one of aspects one to six or aspects eight to thirty-three, wherein at least one airfoil body may be mechanically separated from the outer band, the inner band, or both, or wherein the outer band, the inner band, or both are capable of moving relative to at least one airfoil body in at least one of a radial direction, an axial direction, or an angular direction.

[0155] The thirty-sixth aspect of the present disclosure may include the thirty-fourth aspect, wherein the outer band may include at least one outer band flange protruding radially outward from a radially outwardly facing surface, at least one outer band flange being positioned to engage at least one of an axial mount, a tangential mount, or both coupled to an outer hanger, and / or the inner band may include at least one inner band flange protruding radially inward from a radially inwardly facing surface, at least one inner band flange being positioned to engage at least one of an axial mount, a tangential mount, or both coupled to an inner hanger.

[0156] A thirty-seventh aspect of the present disclosure may include any one of the first to twenty-first aspects or the twenty-third to thirty-sixth aspects, wherein at least one airfoil body may be a hollow airfoil body.

[0157] A thirty-eighth aspect of the present disclosure may include any one of the first to thirty-sixth aspects, wherein at least one airfoil body may be a solid airfoil body.

[0158] A thirty-ninth aspect of the present disclosure may include a nozzle segment assembly for a gas turbine engine. The nozzle segment assembly may include an inner hanger, an outer hanger, and an airfoil assembly. The airfoil assembly may include: an outer band including a radially outwardly facing surface; an inner band including a radially inwardly facing surface; and at least one airfoil body extending between the outer band and the inner band. At least one airfoil body may include an outer end extending through the outer band and projecting outwardly from the radially outwardly facing surface of the outer band and an inner end extending through the inner band and projecting radially inwardly from the radially inwardly facing surface of the inner band. The outer hanger may be disposed radially outwardly from the outer band, and the inner hanger may be disposed radially inwardly from the inner band. The outer end of at least one airfoil body may engage with the outer hanger and the inner end of at least one airfoil body may engage with the inner hanger to position and constrain the airfoil assembly. The outer band, the inner band, and at least one airfoil body may include a ceramic matrix composite (CMC) material.

[0159] A fortieth aspect of the present disclosure may include the thirty-ninth aspect, wherein the inner hanger, the outer hanger, or both may include at least one axial mount, the at least one axial mount having an axial engagement surface that engages at least a portion of an outer surface or at least a portion of an inner surface of at least one airfoil body. The engagement may limit axial movement of at least one airfoil body relative to the inner hanger, the outer hanger, or both.

[0160] A forty-first aspect of the present disclosure may include any of the thirty-ninth or fortieth aspects, wherein the outer hanger may include at least one axial mount extending radially inward from a radially inward facing surface of the outer hanger.

[0161] A forty-second aspect of the present disclosure may include any of the thirty-ninth or fortieth aspects, wherein the inner hanger may include at least one axial mount extending radially outward from a radially outward facing surface of the inner hanger.

[0162] The forty-third aspect of the present disclosure may include any one of aspects 40 to 42, wherein the axial engagement surface of at least one axial mounting member may at least partially face the axial direction, or a line perpendicular to the plane of the axial engagement surface of the axial mounting member is not perpendicular to the axial direction.

[0163] The forty-fourth aspect of the present disclosure may include any one of aspects thirty-nine to forty-third, including a plurality of airfoil bodies, wherein the inner hanger, the outer hanger, or both may include a plurality of axial mounts, and the axial engagement surface of each of the plurality of axial mounts may engage with an outer surface or an inner surface of one of the plurality of airfoil bodies.

[0164] Aspect 45 of the present disclosure may include any one of aspects 40 to 44, wherein at least one axial mount may be oriented so that an axial engagement surface of at least one axial mount may be aligned with a contour of a portion of an outer surface of at least one airfoil body at an outer end or an inner end.

[0165] A forty-sixth aspect of the present disclosure may include any one of the fortieth to forty-fifth aspects, wherein a line perpendicular to the axial engagement surface of at least one axial mount may not be parallel to the axial direction.

[0166] A forty-seventh aspect of the present disclosure may include any one of the fortieth to forty-fifth aspects, wherein a line perpendicular to the axial engagement surface of at least one axial mount is parallel to a plane formed by a radial direction and an axial direction.

[0167] Aspect 48 of the present disclosure may include aspect 47, wherein at least one airfoil body may include an axially facing outer surface at an outer end, an inner end, or both of at least one airfoil body, the axially facing outer surface being oriented to engage with an axial engagement surface of at least one axial mount.

[0168] A forty-ninth aspect of the present disclosure may include the forty-eighth aspect, wherein the axially facing outer surface may include a surface of a protrusion extending from an outer surface of the at least one airfoil body at an outer end, an inner end, or both.

[0169] A fiftieth aspect of the present disclosure may include any one of aspects 40 to 47, including a plurality of airfoil bodies and at least one mounting rod mechanically coupled to the outer ends of all of the airfoil bodies in the plurality of airfoil bodies or coupled to the inner ends of all of the airfoil bodies in the plurality of airfoil bodies. The mounting rod may include an axial surface of the mounting rod positioned to engage an axial engagement surface of at least one axial mount. The engagement of the axial surface of the mounting rod with the axial engagement surface of the at least one axial mount may at least partially constrain axial movement of the plurality of airfoil bodies relative to the outer hanger or the inner hanger.

[0170] The fifty-first aspect of the present disclosure may include any one of aspects 40 to 47, wherein at least one of the axial mounting members may extend into a cavity defined by an inner surface of at least one of the airfoil bodies such that an axial engagement surface of at least one axial mounting member may engage with at least a portion of the inner surface of at least one airfoil body.

[0171] The fifty-second aspect of the present disclosure may include any one of the forties to fifty-first aspects, and further includes at least one pin extending through at least a portion of the outer end or inner end of at least one airfoil body and at least one axial mounting member, wherein the engagement of at least one pin with a portion of the outer end or inner end of at least one airfoil body and at least one axial mounting member can limit the movement of at least one airfoil body in an angular direction relative to an outer hanger or an inner hanger, respectively.

[0172] Aspect fifty-third of the present disclosure may include any one of aspects thirty-nine to fifty-second, wherein the outer hanger, the inner hanger, or both may further include at least one tangential mounting member, the at least one tangential mounting member including a tangential engagement surface that can be engaged with at least a portion of the outer surface or at least a portion of the inner surface of at least one airfoil body, the engagement limiting the angular movement of at least one airfoil body relative to the outer hanger, the inner hanger, or both.

[0173] A fifty-fourth aspect of the present disclosure may include aspects thirty-ninth to fifty-second, wherein the outer hanger may include at least one tangential mount extending radially inward from a radially inward facing surface of the outer hanger.

[0174] A fifty-fifth aspect of the present disclosure may include aspects thirty-nine to fifty-second, wherein the inner hanger may include at least one tangential mount extending radially outward from a radially outward facing surface of the inner hanger.

[0175] A fifty-sixth aspect of the present disclosure may include any of aspects fifty-three to fifty-fifth, wherein at least one tangential mount may be positioned to engage an outer surface of at least one airfoil body proximate a leading edge of the at least one airfoil body.

[0176] A fifty-seventh aspect of the present disclosure may include any of aspects fifty-three to fifty-fifth, wherein at least one tangential mount may be positioned to engage an outer surface of at least one airfoil body proximate a trailing edge of the at least one airfoil body.

[0177] Aspect fifty-eight of the present disclosure may include aspect fifty-seven, wherein at least one airfoil body may include a tangentially facing surface proximate a trailing edge of at least one airfoil body, the tangentially engaging surface engaging the tangentially facing surface to limit tangential movement of at least one airfoil body relative to an outer hanger or an inner hanger.

[0178] A fifty-ninth aspect of the present disclosure may include any of aspects 40 to 55, wherein the outer band may include a ridge extending radially outward from a radially outward facing surface, the ridge including a tangentially facing surface. The outer hanger may also include at least one tangential mount extending radially inward from a radially inward facing surface of the outer hanger, wherein the tangential mount may include a tangential engagement surface. The tangential engagement surface of the tangential mount may engage with the tangentially facing surface of the ridge to limit tangential movement of the outer band relative to the outer hanger.

[0179] A sixtieth aspect of the present disclosure may include any of aspects 40 to 55 or 59, wherein the inner band may include a ridge extending radially inward from a radially inward facing surface, the ridge including a tangentially facing surface. The inner hanger may include at least one tangential mount extending radially outward from a radially outward facing surface of the inner hanger, wherein the tangential mount may include a tangential engagement surface. The tangential engagement surface of the tangential mount may engage with the tangentially facing surface of the ridge to limit tangential movement of the inner band relative to the inner hanger.

[0180] The sixty-first aspect of the present disclosure may include any aspect of aspects thirty-nine to sixty, wherein one of the inner end or the outer end of at least one airfoil body may include a locating pin hole, the other of the inner end or the outer end may include a locating slot, and the locating pin hole and the locating slot may be operated to position at least one airfoil body within the nozzle segment assembly, constrain at least one airfoil body in a radial direction, or both.

[0181] The sixty-second aspect of the present disclosure may include any one of aspects thirty-ninth to sixty-first, wherein the outer end surface and the inner end surface of at least one airfoil body may be respectively engaged with an outer hanger and an inner hanger to constrain at least one airfoil body in a radial direction.

[0182] The sixty-third aspect of the present disclosure may include any one of aspects thirty-nine to sixty-second, wherein the outer surface of at least one airfoil body may be directly mechanically connected to the outer band, the inner band, or both at the outer end reinforcement wall portion, the inner end reinforcement wall portion, or both, respectively.

[0183] The sixty-fourth aspect of the present disclosure may include any one of aspects thirty-nine to sixty-second, wherein at least one airfoil body may be mechanically separated from the outer band, the inner band, or both, or wherein at least one airfoil body may be moved in at least one of a radial direction, an axial direction, or an angular direction relative to the outer band, the inner band, or both.

[0184] The sixty-fifth aspect of the present disclosure may include the sixty-fourth aspect, wherein the outer band may include at least one outer band flange protruding radially outward from a radially outwardly facing surface, at least one outer band flange being positioned to engage at least one of an axial mount, a tangential mount, or both connected to an outer hanger, and / or the inner band may include at least one inner band flange protruding radially inward from a radially inwardly facing surface, at least one inner band flange being positioned to engage at least one of an axial mount, a tangential mount, or both connected to an inner hanger.

[0185] A sixty-sixth aspect of the present disclosure may include any one of aspects thirty-nine to sixty-fifth, wherein at least one airfoil body may be a hollow airfoil body.

[0186] A sixty-seventh aspect of the present disclosure may include any one of the thirty-ninth to fiftieth aspects or the fifty-second to sixty-fifth aspects, wherein at least one airfoil body may be a solid airfoil body.

[0187] Although various embodiments of dilution devices and cleaner systems including dilution devices have been described herein, it should be understood that it is contemplated that each of these embodiments and techniques can be used alone or in combination with one or more embodiments and techniques. It will be apparent to those skilled in the art that various modifications and variations of the embodiments described herein may be made without departing from the spirit and scope of the claimed subject matter. Therefore, this specification is intended to cover modifications and variations of the various embodiments described herein, provided that such modifications and variations fall within the scope of the appended claims and their equivalents.

Claims

1. A nozzle segment assembly for a gas turbine engine, the nozzle segment assembly comprising an airfoil assembly, characterized in that: The airfoil assembly comprises: Takeaway; Inner belt; as well as at least one airfoil body extending between the outer band and the inner band, the at least one airfoil body comprising: an outer end extending through the outer band and having an outer end reinforcing wall portion projecting from an outer surface of the at least one airfoil body to engage the outer band; and an inner end extending through the inner band and having an inner end reinforcement wall portion projecting from the outer surface of the at least one airfoil body to engage the inner band; wherein the thickness of the outer end reinforcement wall portion and the thickness of the inner end reinforcement wall portion are both greater than the thickness of the central wall portion of the at least one airfoil body; Wherein the outer band, the inner band and the at least one airfoil body comprise a ceramic matrix composite (CMC) material.

2. The nozzle segment assembly according to claim 1, characterized in that: Wherein the at least one airfoil body comprises a plurality of airfoil bodies.

3. The nozzle segment assembly according to claim 1, characterized in that: wherein the outer end reinforcing wall portion of the at least one airfoil body includes an outer end flange extending from the outer surface at the outer end reinforcing wall portion, the outer end flange including a radially outer surface that abuts a portion of a radially inwardly facing surface of the outer band to limit radial movement of the outer band in a radially inward direction relative to the position of the at least one airfoil body.

4. The nozzle segment assembly according to claim 3, characterized in that: Wherein the radially inwardly facing surface of the outer band includes a recess providing a radial engagement surface against the radially outer surface of the outer end flange of the at least one airfoil body.

5. The nozzle segment assembly according to claim 3, characterized in that: The outer end reinforcing wall portion further includes a fillet extending between the outer end flange and the central wall portion, wherein the fillet includes a wall thickness that decreases with decreasing radial position from the outer end flange to the central wall region.

6. The nozzle segment assembly according to claim 1, characterized in that: wherein the inner end reinforcing wall portion of the at least one airfoil body includes an inner end flange extending from the outer surface at the inner end reinforcing wall portion, the inner end flange including a radially inner surface that abuts a portion of a radially outwardly facing surface of the inner band to limit radial movement of the inner band in a radially outward direction relative to the position of the at least one airfoil body.

7. The nozzle segment assembly according to claim 6, characterized in that: Wherein the radially outwardly facing surface of the inner band includes a recess providing a radial engagement surface against the radially inner surface of the inner end flange of the at least one airfoil body.

8. The nozzle segment assembly according to claim 6, characterized in that: The inner end reinforcing wall portion further includes a fillet extending between the inner end flange and the central wall portion, wherein the fillet includes a wall thickness that decreases with increasing radial position from the inner end flange to the central wall region.

9. The nozzle segment assembly according to claim 1, characterized in that: wherein the outer band is directly mechanically coupled to the outer surface of the at least one airfoil body at the outer end reinforcement wall portion, and the inner band is directly mechanically coupled to the outer surface of the at least one airfoil body at the inner end reinforcement wall portion.

10. The nozzle segment assembly according to claim 1, characterized in that: The outer end reinforcing wall portion further includes a fillet extending between the outer end reinforcing wall portion and the central wall portion, wherein the fillet includes a wall thickness that decreases with decreasing radial position from the outer end reinforcing wall portion to the central wall region.

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