Engine components

Abstract

An engine component of a turbine engine. The engine component has a composite structure and a cover structure. The composite structure has a composite structure outer wall and a composite structure edge. The cover structure encloses at least a portion of the composite structure outer wall. The cover structure has a main body. The main body extends along at least a portion of the composite structure outer wall.

Description

Technical Field

[0001] The present invention generally relates to an engine component, and more specifically, to an engine component for a turbine engine having a composite structure. Background Technology

[0002] Turbine engines, particularly gas or combustion turbine engines, are rotary engines that extract energy from an airflow that passes through a fan with multiple fan blades, then through a series of compressor stages into the engine, through a combustor, and then through a series of turbine stages. The compressor stages consist of pairs of rotating blades and stationary impellers, while the turbine stages consist of pairs of rotating blades and stationary impellers. The blades are mounted to a rotating disk, while the impellers are mounted to a stator disk.

[0003] During operation, air enters the compressor section through the fan section, where it is pressurized and mixed with fuel in the combustor, where it is ignited to produce hot combustion gases. These hot combustion gases flow downstream through the turbine stage, where the air expands and exits through the exhaust section. The expansion of air in the turbine section drives the rotating sections of the fan and compressor sections. The intake, pressurization, and expansion of air are accomplished by the rotation of various rotating blades on disks respectively mounted to the fan, compressor, and turbine sections. The rotation of the blades applies mechanical stress along various portions of the blades, particularly at the locations where the blades are mounted to the disks. Attached Figure Description

[0004] The complete and practicable aspects of this disclosure, including its best mode, are set forth in detail in the specification with reference to the accompanying drawings for those skilled in the art, wherein:

[0005] Figure 1 This is a schematic cross-sectional view of a turbine engine according to an exemplary embodiment of the present disclosure.

[0006] Figure 2 It is applicable Figure 1 An exploded view of an engine component inside a turbine engine, which includes an airfoil section and a cover structure.

[0007] Figure 3 It is along Figure 2 A schematic cross-sectional view of the engine component taken from section line III-III further shows the extensions of the body and cover structure.

[0008] Figure 4 It is applicable Figure 2 A schematic cross-sectional view of the engine components, further showing the cover structure and airfoil portion, the cover structure having a set of alignment devices.

[0009] Figure 5 It is applicable Figure 2 A schematic cross-sectional view of the engine component, further showing the extension with a triangular shape.

[0010] Figure 6 It is applicable Figure 2 A schematic cross-sectional view of the engine component, further showing the forked extension.

[0011] Figure 7 It is applicable Figure 2 A schematic cross-sectional view of the engine component, further showing the extension with a barb shape.

[0012] Figure 8 It is applicable Figure 2 A schematic cross-sectional view of an engine component, which is a fan housing with a composite structure, and a cover structure disposed along a corresponding portion of the composite structure.

[0013] Figure 9 It is applicable Figure 2 A schematic cross-sectional view of an engine component, which is a fan housing with a composite structure, and the engine component has a cover structure mechanically connected to the composite structure.

[0014] Figure 10 It is applicable Figure 2 A schematic cross-sectional view of an engine component, which is an airfoil assembly having a mid-span shroud with a composite structure and a cover structure disposed along the composite structure.

[0015] Figure 11 From Figure 10 The schematic cross-sectional view of the engine component seen through section line XI-XI further illustrates the extension of the cover structure.

[0016] Figure 12 From Figure 10 The schematic cross-sectional view of the engine component seen through section line XII-XII further illustrates the interface between opposing parts of the cover structure. Detailed Implementation

[0017] This document discloses a turbine engine including engine components. The engine components have a composite structure and a cover structure. The cover structure includes a main body and an extension. The composite structure includes a channel. The extension is disposed within the channel. The engine components are any suitable components disposed within the turbine engine, such as, but not limited to, airfoil assemblies, casings (e.g., fan casings, engine casings, etc.).

[0018] The cover structure is used to reinforce the composite structure against external forces or forces generated during normal operation of the turbine engine. The cover structure can also be used to connect the composite structure to another structure of the turbine engine. For illustrative purposes, this disclosure will be described with respect to engine components of a turbine engine. However, it should be understood that the aspects of the disclosure described herein are not limited thereto and can have general applicability in other engines or other parts of turbine engines. For example, this disclosure can be applied to engine components in other engines or vehicles and can provide benefits in industrial, commercial, and residential applications.

[0019] As used herein, the term "composite structure" includes a bulk or component that comprises composite materials or collections of composite materials, including but not limited to polymer matrix composites (PMC), ceramic matrix composites (CMC), metal matrix composites (MMC), carbon fibers, polymer resins, thermoplastic resins, bismaleimide (BMI) materials, polyimide materials, epoxy resins, glass fibers, and silicon matrix materials. Composite segments of the bulk define the composite structure.

[0020] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, and the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "forward" or "forward" mean in front of something, and "backward" or "rearward" means behind something. For example, when used for fluid flow, forward / forward can mean upstream, and backward / rearward can mean downstream.

[0021] Furthermore, as used herein, the terms "axial" and "longitudinal" refer to directions parallel to the centerline axis of an object, while the terms "radial" or "radially" refer to directions perpendicular to the axial direction or away from a common center. For example, in the context of a turbine engine, radial refers to the direction of a ray extending between the engine's centerline longitudinal axis and the engine's outer perimeter. Additionally, as used herein, the terms "group of elements" or "a set of elements" can refer to any number of elements, including only one.

[0022] Furthermore, as used herein, the term "fluid" or its related expressions may refer to any suitable fluid within a gas turbine engine to which at least a portion of the gas turbine engine is exposed, such as, but not limited to, combustion gases, ambient air, pressurized airflow, operating airflow, or any combination thereof. It is also conceivable that the gas turbine engine may be another suitable turbine engine, such as, but not limited to, a steam turbine engine or a supercritical carbon dioxide turbine engine. As a non-limiting example, the term "fluid" may refer to steam in a steam turbine engine or carbon dioxide in a supercritical carbon dioxide turbine engine.

[0023] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, front, rear, etc.) are used for identification purposes only to aid the reader in understanding this disclosure and do not constitute a limitation, particularly regarding the location, orientation, or use of the disclosure described herein. Unless otherwise stated, connection references (e.g., attachment, joint, fixation, fastening, connection, and engagement) should be interpreted broadly and may include intermediate members between a group of elements and relative movement between elements. Therefore, a connection reference does not necessarily imply that two elements are directly connected and that there is a fixed relationship between them. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative dimensions reflected in the figures may vary.

[0024] As used herein, the term "composite material" refers to a component having two or more materials. A composite material can be a combination of at least two or more metals, nonmetals, or metal and nonmetal elements or materials. Examples of composite materials can be, but are not limited to, polymer matrix composites (PMC), ceramic matrix composites (CMC), metal matrix composites (MMC), carbon fibers, polymer resins, thermoplastic resins, bismaleimide (BMI) materials, polyimide materials, epoxy resins, glass fibers, and silicon matrix materials.

[0025] As used herein, a "composite" component refers to a structure or component comprising any suitable composite material. Composite components, such as composite airfoils, may comprise several layers or plies of composite material. The layers or plies may vary in stiffness, material, and size to achieve a desired composite component or composite portion of a component having a predetermined weight, size, stiffness, and strength.

[0026] One or more layers of adhesive can be used to form or join composite components. The adhesive may include resins and phenolic resins, and may require high-temperature curing or other hardening techniques.

[0027] As described herein, PMC refers to a class of materials. For example, a portion of PMC materials is defined by prepregs, which are reinforcing materials pre-impregnated with a polymer matrix material (e.g., a thermoplastic resin). Non-limiting examples of methods for producing thermoplastic prepregs include hot melt prepreg and powder prepreg, in which the fiber reinforcement is drawn through a resin melt pool, and in powder prepreg, the resin is electrostatically (as a non-limiting example) deposited onto the fiber reinforcement and then adhered to the fibers in an oven or with the aid of heated rollers (as a non-limiting example). The prepregs can be in the form of unidirectional tapes or woven fabrics, which are then stacked together to form the required number of layups for the part.

[0028] Multilayer prepregs are stacked to the appropriate thickness and orientation of the composite part, then cured and solidified to form a fiber-reinforced composite part. Resins used as matrix materials for PMCs are generally classified as thermosetting resins or thermoplastics. Thermoplastic resins are typically classified as polymers that, due to physical rather than chemical changes, can repeatedly soften and flow upon heating and harden upon sufficient cooling. Notable examples of thermoplastic resins include nylon, thermoplastic polyesters, polyaryletherketones (PAEKs), and polycarbonate resins. Specific examples of high-performance thermoplastic resins considered for aerospace applications include polyetheretherketone (PEEK), polyetherketoneketone (PEKK), polyetherimide (PEI), polyaryletherketone (PAEK), and polyphenylene sulfide (PPS). In contrast, thermosetting resins do not undergo significant softening upon heating once fully cured into a rigid solid, but rather thermal decomposition upon sufficient heating. Notable examples of thermosetting resins include epoxy resins, bismaleimide (BMI), and polyimide resins.

[0029] In another non-limiting example, instead of using prepreg, a thermoplastic polymer can be used, allowing for the use of woven fabrics. Woven fabrics can include, but are not limited to, dry carbon fibers woven together with thermoplastic polymer fibers or filaments. Non-prepreg braided structures can be manufactured in a similar manner. This method allows for the customization of the fiber volume of the part by specifying the relative concentrations of the thermoplastic fibers and reinforcing fibers already woven or braided together. Furthermore, different types of reinforcing fibers can be woven or braided together at different concentrations to customize the performance of the part. For example, glass fibers, carbon fibers, and thermoplastic fibers can all be woven together at different concentrations to customize the performance of the part. Carbon fibers provide the strength of the system, glass fibers can be added to enhance impact resistance—a design feature of parts located near the engine inlet—and thermoplastic fibers provide the bonding for the reinforcing fibers.

[0030] In yet another non-limiting example, resin transfer molding (RTM) can be used to form at least a portion of a composite part. Typically, RTM involves applying dry fiber or matrix material into a mold or cavity. The dry fiber or matrix material can include prepreg, woven material, fabricated material, or any combination thereof.

[0031] Resin can be pumped or otherwise supplied to a mold or cavity to impregnate dry fibers or matrix material. The impregnated fibers or matrix material, combined with the resin, is then cured and removed from the mold. Post-curing may be required when removing the composite component from the mold.

[0032] It is conceivable that RTM could be a vacuum-assisted process. That is, air in the cavity or mold can be removed and replaced with resin before heating or curing. It is also conceivable that the placement of dry fibers or matrix material can be manual or automated. As a non-limiting example, the placement of dry fibers or matrix material can be accomplished either automatically (AFP) or manually.

[0033] Dry fibers or matrix materials can be shaped to form composite components or guide resins. Optionally, additional layers or reinforcing layers of materials different from the dry fibers or matrix materials may be included or added before heating or curing.

[0034] As used herein, CMC refers to a class of materials having reinforcing fibers within a ceramic matrix. Typically, the reinforcing fibers provide structural integrity to the ceramic matrix. Some examples of reinforcing fibers may include, but are not limited to, non-oxide silicon-based materials (e.g., silicon carbide, silicon nitride, or mixtures thereof), non-oxide carbon-based materials (e.g., carbon), oxide ceramics (e.g., silicon carbide, silicon oxynitride, alumina (Al₂O₃), silicon dioxide (SiO₂), aluminosilicates such as mullite, or mixtures thereof), or mixtures thereof.

[0035] Examples of ceramic matrix materials may include, but are not limited to, non-oxide silicon-based materials (e.g., silicon carbide, silicon nitride, or mixtures thereof), oxide ceramics (e.g., silicon oxycarbide, silicon oxynitride, alumina (Al₂O₃), silicon dioxide (SiO₂), aluminosilicates, or mixtures thereof), or mixtures thereof. Optionally, ceramic particles (e.g., oxides of Si, Al, Zr, Y, and combinations thereof) and inorganic fillers (e.g., pyrophyllite, wollastonite, mica, talc, kyanite, and montmorillonite) may also be included in the ceramic matrix.

[0036] Typically, a particular CMC can be referred to as a combination of its fiber type / matrix type. For example, C / SiC is used for carbon fiber reinforced silicon carbide; SiC / SiC is used for silicon carbide fiber reinforced silicon carbide; SiC / SiN is used for silicon carbide fiber reinforced silicon nitride; SiC / SiC-SiN is used for silicon carbide fiber reinforced silicon carbide / silicon nitride matrix mixtures, etc. In other examples, a CMC can consist of a matrix and reinforcing fibers, with the reinforcing fibers including oxide-based materials such as alumina (Al₂O₃), silicon dioxide (SiO₂), aluminosilicates, and mixtures thereof. Aluminosilicates can include crystalline materials such as mullite (3Al₂O₃·2SiO₂), as well as glassy aluminosilicates.

[0037] In some non-limiting examples, reinforcing fibers may be bundled and / or coated before being incorporated into the matrix. For example, fiber bundles may form reinforcing tapes, such as unidirectional reinforcing tapes. Multiple tapes may be stacked together to form a preformed part. Fiber bundles may be impregnated with a slurry composition before or after the formation of the preform. The preform may then undergo heat treatment and subsequent chemical treatment to obtain a part formed from a CMC material having the desired chemical composition. For example, the preform may undergo curing or burn-out to produce a high-carbon residue in the preform, followed by melt infiltration with silicon, or curing or pyrolysis to produce a silicon carbide matrix in the preform, followed by chemical vapor infiltration with silicon carbide. Additional steps may be taken before or after chemical vapor infiltration to enhance the densification of the preform by injecting it with a liquid resin or polymer followed by a heat treatment step to fill the voids with silicon carbide. The CMC material used herein may be formed using any known or developed methods, including but not limited to melt infiltration, chemical vapor infiltration, polymer impregnation pyrolysis (PIP), or any combination thereof.

[0038] This material, along with certain monolithic ceramics (i.e., ceramic materials without reinforcement), is particularly well-suited for high-temperature applications. Furthermore, these ceramic materials are lighter than superalloys, yet still provide strength and durability for components made from them. Therefore, the use of this material in many gas turbine components used in the high-temperature sections of gas turbine engines, such as airfoils (e.g., turbines and blades), combustors, shields, and other similar parts, is currently under consideration. These components would benefit from the lighter weight and higher temperature performance that these materials can offer.

[0039] As used herein, the term "metal" refers to materials that include metals, such as, but not limited to, titanium, iron, aluminum, stainless steel, and nickel alloys. A metallic material or alloy can be a combination of at least two or more elements or materials, at least one of which is a metal.

[0040] Figure 1 This is a schematic cross-sectional view of a turbine engine 10 for an aircraft. The turbine engine 10 has a generally longitudinally extending axis or centerline 12 extending from the front 14 to the rear 16. The turbine engine 10 includes a fan section 18, a compressor section 22, a combustion section 28, a turbine section 32, and an exhaust section 38 in a downstream serial flow relationship. The fan section 18 includes a fan 20, the compressor section 22 includes a supercharger or low-pressure (LP) compressor 24 and a high-pressure (HP) compressor 26, the combustion section 28 includes a combustor 30, and the turbine section 32 includes an HP turbine 34 and an LP turbine 36.

[0041] Fan section 18 includes a fan housing 40 surrounding fan 20. Fan 20 includes a set of fan blades 42 arranged radially about engine centerline 12. HP compressor 26, combustor 30 and HP turbine 34 form engine core 44 of turbine engine 10, which produces combustion gases. Engine core 44 is surrounded by engine housing 46, which can be coupled to fan housing 40.

[0042] HP shaft 48 is coaxially arranged around the engine centerline 12 of turbine engine 10 and drives HP turbine 34 to HP compressor 26. LP shaft 50 is coaxially arranged within the larger diameter annular HP shaft 48 around the engine centerline 12 of turbine engine 10 and drives LP turbine 36 to LP compressor 24 and fan 20. Shafts 48 and 50 are rotatable around the engine centerline 12 and are connected to multiple rotatable elements that collectively define rotor 51.

[0043] LP compressor 24 and HP compressor 26 each include multiple compressor stages 52 and 54, in which a set of compressor blades 56 and 58 rotate relative to a corresponding set of static compressor blades 60 and 62 to compress or pressurize the fluid flow through that stage. In a single compressor stage 52 or 54, the set of compressor blades 56 and 58 can be arranged in a ring and can extend radially outward from the blade platform to the tip relative to the engine centerline 12, while the corresponding static compressor blades 60 and 62 are positioned upstream of and adjacent to this set of compressor blades 56 and 58. It should be noted that... Figure 1 The number of blades, impellers, and compressor stages shown is chosen for illustrative purposes only; other numbers are also possible.

[0044] A set of compressor blades 56, 58 for compressor stages 24 and 26 can be mounted to (or integrated into) disc 61, which is mounted to one of the corresponding HP and LP shafts 48, 50. Static compressor impeller blades 60, 62 for compressor stages 24 and 26 can be mounted to the engine housing 46 in a circumferential arrangement.

[0045] HP turbine 34 and LP turbine 36 each comprise multiple turbine stages 64 and 66, in which a set of turbine blades 68 and 70 rotates relative to a corresponding set of turbine blades 72 and 74 (also referred to as nozzles) to extract energy from the fluid flow passing through the stage. In a single turbine stage 64 or 66, the set of turbine blades 68 and 70 may be arranged in a ring and may extend radially outward relative to the engine centerline 12, while the corresponding set of turbine blades 72 and 74 is positioned upstream of and adjacent to the set of turbine blades 68 and 70. It should be noted that... Figure 1 The number of blades, impellers, and turbine stages shown is chosen for illustrative purposes only; other numbers are also possible.

[0046] A set of turbine blades 68, 70 for the turbine stage can be mounted to a disc 71, which is mounted to one of the corresponding HP and LP shafts 48, 50. A set of turbine blades 72, 74 for the compressor stage can be mounted to the engine housing 46 in a circumferential arrangement.

[0047] Complementing the rotor section, the stationary parts of the turbine engine 10, such as the static compressor blades 60, 62 in the compressor section 22 and the turbine section 32, or a group of turbine blades 72, 74, are also referred to individually or collectively as the stator 63. Therefore, the stator 63 can refer to the combination of non-rotating elements in the entire turbine engine 10.

[0048] It should be understood that the turbine engine 10 can be divided into at least two separate parts: a rotor part and a stator part. The rotor part can be defined as any part of the turbine engine 10 that rotates about a corresponding axis of rotation. The stator part can be defined by a combination of non-rotating elements disposed within the turbine engine 10. As a non-limiting example, the rotor part may include one or more of a set of fan blades 42, a set of compressor blades 56, 58, or a set of turbine blades 68, 70. As a non-limiting example, the stator part may include one or more of a set of airfoil guide vanes 82 (described below), static compressor vanes 60, 62, or a set of turbine vanes 72, 74.

[0049] In operation, the airflow leaving fan section 18 is split, with a portion directed to LP compressor 24. LP compressor 24 then supplies pressurized airflow 76 to HP compressor 26, which further pressurizes the air. The pressurized airflow 76 from HP compressor 26 mixes with fuel in combustor 30 and is ignited, producing combustion gases. Some work is extracted from these gases by HP turbine 34, which drives HP compressor 26. The combustion gases are discharged into LP turbine 36, which extracts additional work to drive LP compressor 24. The exhaust gases are finally discharged from turbine engine 10 through exhaust section 38. The drive of LP turbine 36 drives LP shaft 50 to rotate fan 20 and LP compressor 24.

[0050] A portion of the pressurized gas flow 76 can be extracted from the compressor section 22 as bleed air 77. Bleed air 77 can be extracted from the pressurized gas flow 76 and supplied to engine components for cooling. The temperature of the pressurized gas flow 76 entering the combustor 30 is significantly higher than the bleed air temperature. Bleed air 77 can be used to reduce the temperature of core components downstream of the combustor 30. Bleed air 77 can also be utilized by other systems.

[0051] Some of the air supplied by fan 20 can bypass engine core 44 to cool portions of turbine engine 10, particularly hot sections, and / or to cool or power other aspects of the aircraft. In the context of a turbine engine, the hot sections are typically located downstream of combustor 30, particularly turbine section 32, with HP turbine 34 being the hottest section as it is directly downstream of combustion section 28. Other sources of cooling fluid may be, but are not limited to, fluid discharged from LP compressor 24 or HP compressor 26.

[0052] The remaining portion of the airflow exiting fan section 18, referred to as bypass airflow 78, bypasses the LP compressor 24 and engine core 44, and exits the turbine engine 10 via a stationary blade array at the fan exhaust side 84, more specifically, an outlet guide vane assembly 80 comprising a set of airfoil guide vanes 82. More specifically, adjacent to fan section 18, radially extending airfoil guide vanes 82 in a circumferential array are used to exert at least some directional control on the bypass airflow 78.

[0053] As shown in the figure, turbine engine 10 is a turbofan engine. However, it should be understood that turbine engine 10 can be any suitable engine, such as, but not limited to, a turboprop engine, a turboshaft engine, a ducted turbofan engine, a non-ducted engine, or an open rotor turbine engine. As a non-limiting example, turbine engine 10 can be a non-ducted turbine engine. A non-ducted turbine engine includes a set of external fan blades and external fan wheel blades that extend radially outward from the nacelle or outer casing housing the engine core. The external fan blades and external fan wheel blades are functionally similar to a set of fan blades 42 and a set of airfoil guide vanes 82 of turbine engine 10, respectively. It should be understood that at least a portion of the external fan blades or external fan wheel blades may define radial limits in a non-ducted turbine engine (e.g., the portion radially furthest from the engine centerline 12). In other words, in a non-ducted turbine engine, no part of the turbine engine is located radially outside the external fan blades or external fan wheel blades.

[0054] Figure 2 It is applicable Figure 1 An exploded view of engine component 100 within a turbine engine 10. The engine component includes a composite structure 102 and a cover structure 104. For illustrative purposes, the cover structure 104 is exploded from the composite structure 102. The composite structure 102 may include an airfoil portion 106 such that the engine component 100 is an airfoil assembly suitable for use as a blade, impeller, airfoil, or other component in any turbine engine, such as, but not limited to, a gas turbine engine, a turboprop engine, a turboshaft engine, a tubular turbofan engine, and the turbine engine 10. Figure 1( ) or non-ducted turbine engine. Airfoil section 106 is any suitable airfoil element of turbine engine 10, such as, but not limited to, a set of fan blades 42 ( Figure 1 ), a set of airfoil guide vanes 82 ( Figure 1 ), a set of compressor blades 56, 58 ( Figure 1 ), a set of compressor impellers 60, 62 ( Figure 1 ), a set of turbine blades 68, 70 ( Figure 1 ) or a set of turbine blades 72, 74 ( Figure 1 ).

[0055] The airfoil portion 106 includes a composite structure outer wall 108. The composite structure outer wall 108 extends between the leading edge 114 and the trailing edge 116 of the composite structure to define the chord direction (Cd). The composite structure outer wall 108 extends between the root 110 and the tip 112 of the composite structure to define the spanwise direction (Sd). The composite structure outer wall 108 defines a pressure side 120 and an intake side 118.

[0056] The composite structure 102 includes a channel 122. As a non-limiting example, the channel 122 extends along the edge of the airfoil portion 106. As another non-limiting example, the channel 122 extends along at least one of the composite structure leading edge 114, composite structure tip 112, composite structure trailing edge 116, composite structure root 110, or combinations thereof. In the illustrated example, the channel 122 extends along the composite structure leading edge 114 in the spanwise direction (Sd). It should be understood that the channel 122 can be segmented or continuous. The channel 122 can extend along the entire corresponding edge of the airfoil portion 106 or less than the entire corresponding edge. As a non-limiting example, the channel 122 extends along the entire span of the composite structure leading edge 114 between the composite structure root 110 and the composite structure tip 112 (e.g., an extension in the spanwise direction (Sd)).

[0057] At least a portion of the composite structure 102 comprises a composite material. As a non-limiting example, the outer wall 108 of the composite structure may comprise a composite material. As a non-limiting example, the outer wall 108 of the composite structure may comprise at least a PMC portion, a polymer portion, or both. The PMC portion may include, but is not limited to, a thermosetting (epoxy resin, phenolic resin) or thermoplastic (polycarbonate, polyvinyl chloride, nylon, acrylic resin) matrix and embedded glass, carbon, steel, or combinations thereof.

[0058] The cover structure 104 includes a body 124 and an extension 126 extending from the body 124. The body 124 defines the outer portion of the cover structure 104. The body 124 and the extension 126 are integrally formed or connected to each other.

[0059] The cover structure 104 includes a cover structure edge 162, a set of main body distal ends 164, and an extension distal end 166. As shown in the figure, the cover structure edge 162 is the foremost part of the cover structure 104 in the chord direction (Cd).

[0060] The total distance that the extension 126 extends in the spanwise direction (Sd) can be equal to the total distance that the main body 124 extends in the spanwise direction (Sd). The total distance that the extension 126 extends in the spanwise direction (Sd) can be different from the total distance that the main body 124 extends in the spanwise direction (Sd). As a non-limiting example, the extension 126 can extend within 75% of the leading edge 114 of the composite structure in the spanwise direction (Sd), while the main body 124 can extend within more than 75% of the leading edge 114 of the composite structure in the spanwise direction (Sd).

[0061] The cover structure 104 includes at least one of a metallic material, a plastic material, or a combination thereof. The material of the cover structure 104 may be, but is not limited to, titanium, aluminum, polyurethane, etc. As a non-limiting example, the cover structure 104 may include a metallic material, such that the cover structure 104 is defined as a metallic cover structure.

[0062] The cover structure 104 is attached to the composite structure 102 by any suitable connection method, such as, but not limited to, welding, adhesion, bonding, fastening, friction fit, etc. The extension 126 is sized to fit within the channel 122. When the cover structure 104 is attached to the composite structure 102, the extension 126 is received within the channel 122. When attached to the composite structure 102, the cover structure 104 covers the corresponding portion of the composite structure 102. In other words, the cover structure 104 covers the corresponding portion of the composite structure 102.

[0063] After assembling or forming the composite structure 102, the composite structure 102 and the cover structure 104 can be connected to each other. As a non-limiting example, the composite structure 102 and the cover structure 104 can be connected to each other after the composite structure 102 has been cured. The composite structure 102 and the cover structure 104 can be integrally formed together. As a non-limiting example, the cover structure 104 can be positioned along the uncured version of the composite structure 102. The cover structure 104 and the composite structure 102 can then be co-cured, such that the cover structure 104 is integrally formed with the composite structure 102 and becomes a whole. As a non-limiting example, the cover structure 104 and the composite structure 102 can be integrally formed by any suitable method, such as, but not limited to, electroforming, 3D printing, etc.

[0064] The cover structure edge 162 defines the leading edge of the engine component for the engine component 100. However, it should be understood that the cover structure edge 162 varies based on the location of the cover structure 104. As a non-limiting example, the cover structure 104 may be positioned along the trailing edge 116 of the composite structure to define at least a portion of the trailing edge of the engine component. As a non-limiting example, the cover structure may be positioned along the tip 112 of the composite structure to define at least a portion of the tip of the engine component. As a non-limiting example, the cover structure may be positioned along the root 110 of the composite structure to define at least a portion of the root of the engine component. As a non-limiting example, the cover structure may be positioned along the outer wall 108 of the composite structure to define at least a portion of the outer wall of the engine component. It should be understood that the engine component 100 includes any number or more cover structures 104 positioned along any suitable portion of the composite structure 102.

[0065] It should be understood that engine component 100 is any suitable engine component 100. As a non-limiting example, engine component 100 may be an airfoil assembly comprising an airfoil portion having a dovetail tenon extending radially inward from a root (e.g., composite structure root 110). In this case, cover structure 104 may extend above or terminate before the dovetail tenon portion. Other non-limiting examples of engine component 100 include, but are not limited to, housings (e.g., fan housings, burner bushings, engine housings, etc.), airfoil portions including shields (e.g., mid-span shields, tip shields, outer platforms, inner platforms, etc.), airfoil portions extending from an inner band coupled to a root, airfoil assemblies including spars extending from the root of the airfoil portion and coupled to trunnions (e.g., variable pitch airfoil assemblies), coupled to discs (e.g., Figure 1 The airfoil section of the disk (61, 71), etc.

[0066] During operation, engine component 100 is subjected to force (F). Force (F) is present in a turbine engine (e.g., Figure 1 The turbine engine 100 may experience any force during operation. As a non-limiting example, the force (F) can be, but is not limited to, the airflow passing through the engine component 100 (e.g., airflow through the turbine engine 100). Figure 1 The force (F) is the force of the pressurized airflow 76, the rotational force exerted on the engine component 100 due to its rotation, the external force exerted on the engine component 100 (e.g., bird strike), or a combination thereof. The force (F) is shown in the chordal direction (Cd). The force (F) can be in any suitable direction.

[0067] The cover structure 104 is used to reinforce certain portions of the composite structure 102 (e.g., the leading edge 114 of the composite structure) to ensure that the engine component 100 can withstand the force (F). It is conceivable that without the cover structure 104, the force (F) might damage certain portions of the composite structure 102.

[0068] Figure 3 It is along Figure 2 A schematic cross-sectional view of engine component 100 taken by section line III-III. Section line III-III is perpendicular to the wingspan direction (Sd). Although section line III-III is shown as approximately halfway between the composite structure root 110 and the composite structure tip 112, it can be located at any suitable portion of the composite structure leading edge 114, including the endpoints (e.g., the composite structure tip 112 and the composite structure root 110).

[0069] The corresponding portions of the main body 124 and the airfoil portion 106 meet at the joint 128. The joint 128 is configured such that when the cover structure 104 is attached to the composite structure 102, the outer portion of the main body 124 extends continuously from the outer wall 108 of the composite structure. In other words, the joint 128 may be configured such that the outer surface of the cover structure 104 abuts flush with the outer wall 108 of the composite structure. Alternatively, the joint 128 may be configured such that the outer surface of the cover structure 104 is recessed relative to the position of the outer wall 108 of the composite structure at the distal end 164 of the main body (e.g., radially closer to the centerline (C1)). The joint 128 is any suitable joint, such as, but not limited to, interlocking joints, butt joints, lap joints, etc.

[0070] The extension 126 and the main body 124 meet at the transition 130 shown by the dashed line. When viewed along section line III-III, the extension 126 includes any suitable cross-sectional area.

[0071] Engine component 100 includes a cover structure edge 162 and a composite structure trailing edge 116. Figure 2 The centerline (Cl) extends between the opposite edges of the engine component 100, which is an airfoil assembly. For the engine component 100 as an airfoil assembly, the centerline (Cl) is a mid-curve. However, it should be understood that the centerline (Cl) is any suitable centerline extending between the opposite edges of the engine component 100 and equidistant between the opposite surfaces of the composite structure outer wall 108.

[0072] When viewed along a plane extending along the centerline (Cl) (e.g., section line III-III), extension 126 has a cross-sectional area. As shown, the cross-sectional area is rectangular. However, it should be understood that the cross-sectional area can be any suitable shape, such as, but not limited to, circular, oval, triangular, rectangular, hexagonal, etc. As a non-limiting example, the cross-sectional area can be defined by a wavy (wave-like) cross-section. Extension 126 can be symmetrical about the centerline (Cl). Extension 126 can be asymmetrical about the centerline (Cl).

[0073] The cross-sectional area of ​​the extension 126 can be constant or vary along the range of the channel 122. As a non-limiting example, the cross-sectional area of ​​the extension 126 can vary in the spanwise direction (Sd). As a non-limiting example, the root 110 of the composite structure (… Figure 2 The cross-sectional area of ​​the extension 126 at the point can be triangular, and the root 110 and tip 112 of the composite structure ( Figure 2 The cross-sectional area of ​​the extension 126 between the two can be rectangular, while the cross-sectional area of ​​the extension 126 at the tip 112 of the composite structure can be oval.

[0074] The variation in the cross-sectional area of ​​extension 126 is based on the cross-sectional area of ​​composite structure 102, wherein cap structure 104 covers composite structure 102 (e.g., along composite structure leading edge 114). As a non-limiting example, composite structure 102 may sweep along composite structure leading edge 114 or include a non-constant cross-sectional area in the spanwise direction (Sd). These variations in the cross-sectional area of ​​composite structure 102 affect the formation of extension 126. As a non-limiting example, a smaller cross-sectional area of ​​composite structure 102, in turn, means that the size of extension 126 must be smaller than the area of ​​composite structure with a larger cross-sectional area. Furthermore, it is conceivable that certain shapes of extension 126 affect certain forces (e.g., Figure 3 The force (F) has better resistance. As a non-limiting example, if the force (F) is an external force (e.g., a bird strike), then in the spanwise direction (Sd), the force (F) has a greater impact closer to the tip 112 of the composite structure compared to the root 110. Therefore, the cap structure 104, especially the extension 126, has a more robust design (e.g., a larger cross-sectional area with a larger extension 126) closer to the tip 112 of the composite structure compared to the root 110.

[0075] The most downstream or axially displaced distal end of a set of main bodies 164 is provided with a first centerline length (Cl1) of the main body 124 at a distance of 130 from the transition portion. The main body 124 may be symmetrical about the centerline (Cl). The main body 124 may be asymmetrical about the centerline (Cl).

[0076] The extension 126 extends a second centerline length (Cl2) in the chordal direction (Cd) between the transition 130 and the distal end 166 of the extension. The first centerline length (Cl1) is greater than or equal to the second centerline length (Cl2). As a non-limiting example, the second centerline length (Cl2) is greater than or equal to 10% of the first centerline length (Cl1) and less than or equal to 100% of the first centerline length (Cl1). The distal end 166 of the extension is axially coincident with or axially offset from at least one of the distal ends 164 of the main body relative to the centerline (Cl).

[0077] It is conceivable that the selection of the second centerline length (Cl2) is for manufacturing and assembly purposes. Specifically, the shorter the second centerline length (Cl2), the easier it is to insert the extension 126 into the channel 122. Conversely, a longer second centerline length (Cl2) makes it more difficult to insert the extension 126 into the channel 122. However, the shorter the second centerline length (Cl2), the smaller the mating area between the cover structure 104 and the composite structure 102. Conversely, the longer the second centerline length (Cl2), the larger the mating area between the cover structure 104 and the composite structure 102, because the extension 126 is longer. As used herein, "mating area" is defined as the available surface area between the first structure (e.g., cover structure 104) and the second structure (e.g., composite structure 102) that can be used to join the two structures together. For example, when the composite structure 102 and the cover structure 104 are joined using an adhesive, the total available mating area is the total surface area of ​​the cover structure 104 in direct contact with the composite structure 102. A larger mating area means a stronger bond between the cover structure 104 and the composite structure 102. The above range (0.10Cl1≤Cl2≤Cl1) is chosen to ensure a sufficient balance between ease of manufacture and mating area.

[0078] Figure 4 It is applicable Figure 2 A schematic cross-sectional view of engine component 200 of engine component 100. Engine component 200 is similar to engine component 100; therefore, similar components will be identified by similar numbers increasing to the 200 series, and it should be understood that, unless otherwise stated, the description of engine component 100 applies to engine component 200.

[0079] Engine component 200 includes a composite structure 202 and a cover structure 204. Engine component 200 includes a centerline (C1). Composite structure 202 includes a composite structure outer wall 208 and a composite structure edge 268. Composite structure edge 268 can be any suitable edge of composite structure 202. As a non-limiting example, composite structure edge 268 can be, but is not limited to, a composite structure tip (e.g., ...). Figure 2The composite structure tip 112), the composite structure root (e.g. Figure 2 The root 110 of the composite structure), the leading edge of the composite structure (e.g. Figure 2 The leading edge 114 of the composite structure and the trailing edge of the composite structure (e.g.) Figure 2 The composite structure trailing edge 116, etc. Channel 222 is formed along the edge 268 of the composite structure. The composite structure 202 is any suitable composite structure, such as, but not limited to, airfoil portions (e.g., Figure 2 The airfoil portion 106), the fan housing (e.g. Figure 1 The fan housing 40), shroud, etc. The cover structure 204 includes a main body 224 and an extension 226. The extension 226 intersects with the main body 224 at a transition 230 (shown by dashed lines). The cover structure 204 includes a cover structure edge 262, a set of main body distal ends 264, and extension distal ends 266. The cover structure 204 and the composite structure 202 intersect at a joint 228.

[0080] The engine component 200 is similar to the engine component 100 in that a cover structure 204 is coupled to the composite structure 202. The cover structure 204 is disposed along the edge 268 of the composite structure and covers at least a portion of the outer wall 208 of the composite structure. However, the engine component 200 also includes a set of alignment channels 232 and a set of aligners 234. As shown, each aligner in the set of aligners 234 is sized to fit within a corresponding aligner channel of the set of alignment channels 232. The set of aligners 234 and the set of alignment channels 232 are used to align or otherwise engage the cover structure 204 to the composite structure 202 in a desired manner or position. The set of aligners 234 and the set of alignment channels 232 also function as a lock. In other words, once the set of aligners 234 is positioned within the set of alignment channels 232, the cover structure 204 is locked or otherwise engaged to the composite structure 202. The extension 226, the set of aligners 234, and the set of alignment channels 232 together engage the cover structure 204 to the composite structure 202.

[0081] A set of aligners 234 is disposed on one of the cover structure 204 or the composite structure 202, while a set of alignment channels 232 is disposed on the other of the cover structure 204 or the composite structure 202. As a non-limiting example, the set of aligners 234 is disposed along the body 224, and the set of alignment channels 232 is disposed along the outer wall 208 of the composite structure. However, it should be understood that each of the cover structure 204 and the composite structure 202 may include one or more corresponding aligners from the set of aligners 234 and one or more corresponding alignment channels from the set of alignment channels 232.

[0082] Each of the aligners in the set 234 includes a corresponding cross-sectional area. The corresponding cross-sectional area of ​​each aligner in the set 234 can be any suitable shape, such as, but not limited to, rectangular, circular, oval, triangular, barbed, etc.

[0083] Figure 5 It is applicable Figure 2 A schematic cross-sectional view of engine component 100 and engine component 300. Engine component 300 is similar to engine components 100 and 200. Figure 4 Therefore, similar parts will be identified by similar numbers added to the 300 series, and it should be understood that, unless otherwise stated, the descriptions of engine parts 100 and 200 apply to engine part 300.

[0084] Engine component 300 includes a composite structure 302 and a cover structure 304. Engine component 300 includes a centerline (C1). Composite structure 302 includes a composite structure outer wall 308 and a composite structure edge 368. Composite structure edge 368 can be any suitable edge of composite structure 302. As a non-limiting example, composite structure edge 368 can be, but is not limited to, the tip of composite structure (e.g., ...). Figure 2 The composite structure tip 112), the composite structure root (e.g. Figure 2 The root 110 of the composite structure), the leading edge of the composite structure (e.g. Figure 2 The leading edge 114 of the composite structure and the trailing edge of the composite structure (e.g.) Figure 2 The composite structure trailing edge 116, etc. Channel 322 is formed along the edge 368 of the composite structure. The composite structure 302 is any suitable composite structure, such as, but not limited to, airfoil portions (e.g., Figure 2 The airfoil portion 106), the fan housing (e.g. Figure 1 The fan housing 40), shroud, etc. The cover structure 304 includes a main body 324 and an extension 326. The extension 326 intersects with the main body 324 at a transition 330 (shown by dashed lines). The cover structure 304 includes a cover structure edge 362, a set of main body distal ends 364, and extension distal ends 366. The cover structure 304 and the composite structure 302 intersect at a joint 328.

[0085] Engine component 300 is similar to engine components 100 and 200 in that a cover structure 304 is connected to the composite structure 302. The cover structure 304 is disposed along the edge 368 of the composite structure and covers at least a portion of the outer wall 308 of the composite structure. However, the extension 326 includes a triangular cross-sectional area. The connector 328 is a butt joint, not like connector 128. Figure 3 Such a splicing joint. The dimensions of the joint 328 allow the main body 324 and the outer wall 308 of the composite structure to form a continuous surface, as shown in the figure.

[0086] Figure 6 It is applicable Figure 2 A schematic cross-sectional view of engine component 400 of engine component 100. Engine component 400 is similar to engine components 100 and 200. Figure 4 ), 300 Figure 5 Therefore, similar parts will be identified by similar numbers increasing to the 400 series, and it should be understood that, unless otherwise stated, the descriptions of engine parts 100, 200, and 300 apply to engine part 400.

[0087] Engine component 400 includes a composite structure 402 and a cover structure 404. Engine component 400 includes a centerline (C1). Composite structure 402 includes a composite structure outer wall 408 and a composite structure edge 468. Composite structure edge 468 can be any suitable edge of composite structure 402. As a non-limiting example, composite structure edge 468 can be, but is not limited to, a composite structure tip (e.g., ...). Figure 2 The composite structure tip 112), the composite structure root (e.g. Figure 2 The root 110 of the composite structure), the leading edge of the composite structure (e.g. Figure 2 The leading edge 114 of the composite structure and the trailing edge of the composite structure (e.g.) Figure 2 The composite structure trailing edge 116, etc. Channel 422 is formed along the edge 468 of the composite structure. The composite structure 402 is any suitable composite structure, such as, but not limited to, airfoil portions (e.g., Figure 2 The airfoil portion 106), the fan housing (e.g. Figure 1 The fan housing 404, shroud, etc. The cover structure 404 includes a main body 424 and an extension 426. The extension 426 intersects with the main body 424 at a transition 430 (shown by dashed lines). The cover structure 404 includes a cover structure edge 462, a set of main body distal ends 464, and extension distal ends 466. The cover structure 404 and the composite structure 402 intersect at a joint 428.

[0088] The engine component 400 is similar to engine components 100, 200, and 300 in that a cover structure 404 is connected to the composite structure 402. The cover structure 404 is disposed along the edge 468 of the composite structure and covers at least a portion of the outer wall 408 of the composite structure. However, the extension 426 includes forks, such that the extension 426 includes two or more branches 436 terminating at the distal end 466 of the respective extension. Each of the two or more branches 436 has a corresponding cross-sectional area, which is any suitable shape, such as, but not limited to, triangular, rectangular, oval, trapezoidal, barbed, etc. The cross-sectional areas of at least two of the two or more branches 436 may be identical. The cross-sections of at least two of the two or more branches 436 may be different. The two or more branches 436 may be symmetrical about a centerline (C1). The two or more branches 436 may be asymmetrical about a centerline (C1). The two or more branches 436 may include any number of multiple branches. As shown in the figure, the dimensions of the joint 428 cause a discontinuity between the main body 424 and the outer wall 408 of the composite structure. In other words, a step is formed between the outer wall 408 of the composite structure and the main body 424. Therefore, the joint 428 is defined as a stepped joint. As a non-limiting example, the outer surface or outer wall of the cover structure is arranged radially outward from the outer wall 408 at the distal end 464 of the main body relative to the centerline (C1).

[0089] Figure 7 It is applicable Figure 2 A schematic cross-sectional view of engine component 500. Engine component 500 is similar to engine components 100 and 200. Figure 4 ), 300 Figure 5 ), 400 Figure 6 Therefore, similar parts will be identified by similar numbers increasing to the 500 series, and it should be understood that, unless otherwise stated, the descriptions of engine parts 100, 200, 300, and 400 apply to engine part 500.

[0090] Engine component 500 includes a composite structure 502 and a cover structure 504. Engine component 500 includes a centerline (C1). Composite structure 502 includes a composite structure outer wall 508 and a composite structure edge 568. Composite structure edge 568 can be any suitable edge of composite structure 502. As a non-limiting example, composite structure edge 568 can be, but is not limited to, the tip of composite structure (e.g., ...). Figure 2 The composite structure tip 112), the composite structure root (e.g. Figure 2 The root 110 of the composite structure), the leading edge of the composite structure (e.g. Figure 2 The leading edge 114 of the composite structure and the trailing edge of the composite structure (e.g.) Figure 2The composite structure trailing edge 116, etc. Channel 522 is formed along the edge 568 of the composite structure. The composite structure 502 is any suitable composite structure, such as, but not limited to, airfoil portions (e.g., Figure 2 The airfoil portion 106), the fan housing (e.g. Figure 1 The fan housing 40), shroud, etc. The cover structure 504 includes a main body 524 and an extension 526. The extension 526 intersects with the main body 524 at a transition 530 (shown by dashed lines). The cover structure 504 includes a cover structure edge 562, a set of main body distal ends 564, and extension distal ends 566. The cover structure 504 and the composite structure 502 intersect at a joint 528.

[0091] The engine component 500 is similar to engine components 100, 200, 300, and 400 in that a cover structure 504 is coupled to the composite structure 502. The cover structure 504 is disposed along the edge 568 of the composite structure and covers at least a portion of the outer wall 508 of the composite structure. However, the extension 526 includes a set of barbs 538 disposed along the extension 526. The set of barbs 538 extends into the composite structure 502. It is conceivable that the set of barbs 538 is used to reinforce the connection between the cover structure 504 and the composite structure 502. The set of barbs 538 is used to anchor or otherwise secure the cover structure 504 within the channel 522. The set of barbs 538 includes any number of one or more barbs. The set of barbs 538 further increases the mating area between the cover structure 504 and the composite structure 502 without increasing the length of the extension 526 (e.g., Figure 3 The second centerline length (Cl2). The extension 526 and a set of barbs 538 may be symmetrical about the centerline (Cl). The extension 526 and a set of barbs 538 may be asymmetrical about the centerline (Cl).

[0092] See Figure 2-7 It should be understood that cover structures 104, 204, 304, 404, and 504 may include any aspect or combination of aspects of cover structures 104, 204, 304, 404, and 504. As a non-limiting example, the cover structure may include elements along the cover structure (e.g., in...). Figure 2 The extensions having different cross-sectional areas in the wingspan direction (Sd) are such that the cover structure includes a rectangular cross-sectional area of ​​the extension 126, a set of alignment channels 232 of the engine component 200, a set of aligners 234 of the engine component 200, a triangular cross-sectional area of ​​the extension 326, two or more branches 436 of the extension 426, at least two of a set of barbs 538 of the extension 526, or any combination thereof.

[0093] Figure 8 It is applicable Figure 2A schematic cross-sectional view of engine component 100 and engine component 600. Engine component 600 is similar to engine components 100 and 200. Figure 4 ), 300 Figure 5 ), 400 Figure 6 ), 500 Figure 7 Therefore, similar parts will be identified by similar numbers increasing to the 600 series, and it should be understood that, unless otherwise stated, the descriptions of engine parts 100, 200, 300, 400, and 500 apply to engine part 600.

[0094] Engine component 600 includes a composite structure 602 and a cover structure 604. The composite structure 602 includes a composite structure outer wall 608 extending between a leading edge 614 and a trailing edge 616 of the composite structure. The composite structure 602 includes a channel 622. The channel 622 may be formed along the trailing edge 616 of the composite structure. The cover structure 604 includes a body 624 and an extension 626. The cover structure 604 includes a cover structure edge 662, a set of distal ends 664 of the body, and distal ends 666 of the extension. The extension 626 is disposed within the channel 622.

[0095] The engine component 600 is similar to engine components 100, 200, 300, 400, and 500 in that a cover structure 604 is connected to the composite structure 602. The cover structure 604 is disposed along the edge of the composite structure (e.g., the trailing edge 616 of the composite structure) and covers at least a portion of the outer wall 608 of the composite structure. However, as shown, the cover structure 604 is disposed along the trailing edge 616 of the composite structure instead of the leading edge 614 of the composite structure.

[0096] However, engine component 600 is the housing of turbine engine 682. Turbine engine 682 has an engine centerline 656 and a set of fan blades 640 (e.g., Figure 1 A set of fan blades 42) and a set of fan wheel blades 642 (e.g. Figure 1 A set of airfoil guide vanes 82), which are housed in the fan housing (e.g., Figure 1 The fan housing 40) is located within the engine component 600. As described herein, the engine component 600 is the fan housing. A set of fan blades 640 and a set of fan impeller blades 642 are functionally similar to a set of fan blades 42 ( Figure 1 ) and a set of airfoil guide vanes 82 ( Figure 1 As a non-limiting example, turbine engine 682 is a turbofan engine. Turbine engine 682 includes an engine housing 644. Engine housing 644 is any suitable housing separate from the fan housing (e.g., engine component 600). As a non-limiting example, engine housing 644 may be engine housing 46 (…). Figure 1 ), cabin, etc.

[0097] The cover structure 604 may extend circumferentially around the entire engine centerline 656. The cover structure 604 may also extend circumferentially around a portion smaller than the entire engine centerline 656. The cover structure 604 may be a single, integral unit. As a non-limiting example, the cover structure 604 may be formed as a continuous ring forming a circumferential loop around the engine centerline 656. The cover structure 604 may also be a plurality of segmented bodies circumferentially spaced around the engine centerline 656.

[0098] The cover structure 604 can operatively connect the composite structure 602 to the engine housing 644. As a non-limiting example, the cover structure 604 can be integrally formed with the engine housing 644 or connected to the engine housing 644 by any suitable method, such as, but not limited to, adhesive bonding, fastening, etc. Therefore, the cover structure 604 can define the connection between the fan housing (e.g., engine component 600) and the engine housing 644.

[0099] It is conceivable that directly mounting the composite structure 602 onto the engine housing 644 could damage the composite structure 602. As a non-limiting example, during operation of the turbine engine 682, engine components 600 can move axially, radially, or circumferentially relative to the engine centerline 656. Such movement would damage the composite structure 602 if it were allowed to move freely against or otherwise grind against another structure (e.g., the engine housing 644). However, the cover structure 604 is more resistant to damage caused by movement. Therefore, providing the cover structure 604 along the edge of the composite structure 602 protects it from damage that would otherwise come into contact with other parts of the turbine engine 682. Furthermore, mounting the composite structure 602 onto the engine housing 644 via the cover structure 604 effectively stabilizes the composite structure 602, thereby reducing movement of the engine components 600.

[0100] It should be understood that the cover structure 604 is disposed along any suitable edge of the composite structure 602, such as, but not limited to, the leading edge 614, the trailing edge 616, or any other suitable portion of the outer wall 608 of the composite structure. As a non-limiting example, the engine component 600 may include two cover structures 604; one disposed along the leading edge 614 of the composite structure and the other along the trailing edge 616. The cover structure 604 disposed along the leading edge 614 of the composite structure is particularly advantageous along the leading edge of the fan housing to prevent the entry of debris (e.g., birds).

[0101] Figure 9 It is applicable Figure 2 A schematic cross-sectional view of engine component 700. Engine component 700 is similar to engine components 100 and 200. Figure 4 ), 300 Figure 5 ), 400 Figure 6 ), 500 Figure 7 ), 600 Figure 8 Therefore, similar parts will be identified by similar numbers increasing to the 700 series, and it should be understood that, unless otherwise stated, the descriptions of engine parts 100, 200, 300, 400, 500, and 600 apply to engine part 700.

[0102] Engine component 700 includes a composite structure 702 and a cover structure 704. The composite structure 702 includes a composite structure outer wall 708 extending between a leading edge 714 and a trailing edge 716 of the composite structure. The composite structure 702 includes a channel 722. The channel 722 may be formed along the trailing edge 716 of the composite structure. The cover structure 704 includes a body 724 and an extension 726. The cover structure 704 includes a cover structure edge 762, a set of distal ends 764 of the body, and distal ends 766 of the extension. The extension 726 is disposed within the channel 722.

[0103] Engine component 700 is similar to engine components 100, 200, 300, 400, 500, and 600 because cover structure 704 is connected to composite structure 702. Cover structure 704 is disposed along the edge of composite structure (e.g., the trailing edge 716 of composite structure) and covers at least a portion of the outer wall 708 of composite structure.

[0104] Engine component 700, like engine component 600, is disposed within a turbine engine 782 having an engine centerline 756, and includes, for example, a set of fan blades 740, a set of fan impeller blades 742, and an engine housing 744. Engine component 700 is a fan housing that houses the set of fan blades 740 and the set of fan impeller blades 742. Cover structure 704 connects composite structure 702 to engine housing 744. However, cover structure 704 is mechanically connected to composite structure 702 by using fasteners 746 in conjunction with extension 726. The combined use of fasteners 746 and extension 726 provides additional support between the composite structure 702 and cover structure 704.

[0105] Fastener 746 may be formed as a bolt extending through corresponding portions of composite structure 702 and cover structure 704. Fastener 746 may also be formed as a bolt extending through corresponding portions of extension 726.

[0106] Figure 10 It is applicable Figure 2 A schematic diagram of engine component 800. Engine component 800 is similar to engine components 100 and 200. Figure 4 ), 300 Figure 5 ), 400 Figure 6), 500 Figure 7 ), 600 Figure 8 ), 700 Figure 9 Therefore, similar parts will be identified by similar numbers increasing to the 800 series, and it should be understood that, unless otherwise stated, the descriptions of engine parts 100, 200, 300, 400, 500, 600, and 700 apply to engine part 800.

[0107] Engine component 800 includes a composite structure 802 and a cover structure 804. Composite structure 802 includes a composite structure outer wall 808 extending between a leading edge 814 and a trailing edge 816 of the composite structure. Cover structure 804 includes a body 824. Engine component 800 is disposed within a turbine engine 882 having an engine centerline 856.

[0108] Engine component 800, like engine component 100, is an airfoil assembly 870. However, airfoil assembly 870 includes two adjacent airfoil portions 806 circumferentially spaced apart along platform 858 relative to engine centerline 856. It should be understood, however, that airfoil assembly 870 may include any number of two or more airfoil portions 806. Each of the two adjacent airfoil portions 806 includes an outer wall 872. Each outer wall 872 extends between a root 874 and a tip 876. Each outer wall 872 extends between a leading edge 878 and a trailing edge 880. Each outer wall 872 defines an intake side 884 and a pressure side 886.

[0109] The engine component 800 is similar to engine components 100, 200, 300, 400, 500, 600, and 700 in that a cover structure 804 is connected to the composite structure 802. The cover structure 804 is disposed along the edge of the composite structure and covers at least a portion of the outer wall 808 of the composite structure. However, the composite structure 802 is a mid-span shield. The mid-span shield (e.g., composite structure 802) is disposed between the root 874 and tip 876 of two adjacent airfoil portions 806. The mid-span shield (e.g., composite structure 802) extends from the intake side 884 of one of the two adjacent airfoil portions 806 to the pressure side 886 of the adjacent airfoil portion 806. The mid-span shield (e.g., composite structure 802) extends discontinuously between the two adjacent airfoil portions 806, such that the mid-span shield includes opposing mid-span distal ends 854. The corresponding portions of the leading edge 814 and trailing edge 816 of the composite structure are interconnected at the opposite mid-span distal end 854. However, it should be understood that the mid-span shield (e.g., composite structure 802) may extend continuously over the entire circumference between two adjacent airfoil portions 806.

[0110] As shown in the figure, the cover structure 804 includes two bodies disposed between two adjacent airfoil portions 806: a first body 888 and a second body 890. The first body 888 is disposed on a first portion of the composite structure 802. The second body 890 is disposed on a second portion of the composite structure 802. Although the first body 888 and the second body 890 are shown as separate, it should be understood that they may be integrally formed or otherwise formed as a whole. As a non-limiting example, a single body may extend between opposite mid-span distal ends 854. As a non-limiting example, a mid-span shield (e.g., composite structure 802) may be continuously formed between two adjacent airfoil portions 806, and the cover structure 804 may extend continuously as a single body along the mid-span shield (e.g., composite structure 802).

[0111] It should be understood that one or more airfoil portions 806, or any other airfoil portion, may define a corresponding portion of the composite structure 802, or a separate composite structure. Therefore, one or more airfoil portions may include elements similar to airfoil portion 106. Figure 2 The structure allows the cover structure 804, or the cover structure 804 alone, to be combined with the cover structure 804 provided along the composite structure 802 that defines the mid-span shroud, and attached to any corresponding edge of any airfoil portion.

[0112] Figure 11 From Figure 10 The schematic cross-sectional view of engine component 800 is shown along section line XI-XI. Cover structure 804 includes an extension 826 and a centerline (C1). Extension 826 extends from body 824 at transition 830, shown by dashed lines. Extension 826 includes any suitable cross-sectional area. Composite structure includes channel 822. The dimensions of channel 822 and extension 826 are such that extension 826 fits within channel 822. Cover structure 804 and composite structure 802 meet at joint 828.

[0113] Figure 12 From Figure 10 The schematic cross-sectional view of engine component 800 is shown along section line XII-XII. First body 888 and second body 890 meet at interface 860. Although shown as first body 888 and second body 890, it should be understood that cover structure 804 may include a single body interconnecting opposing mid-rear ends 854.

[0114] The separation of the mid-span shield (e.g., composite structure 802) and cover structure 804 between the first body 888 and the second body 890 allows the engine component 800 to move during operation. This movement of the engine component 800 ensures that stresses arising from excessive rigidity when the engine component 800 cannot move are not generated.

[0115] However, if two or more composite segments of the composite structure 802 come into contact with each other and move in opposite directions, the movement of the engine component 800 may damage it. As a non-limiting example, if the opposing distal mid-spans 854 are in direct contact with each other, abrasion will occur between the opposing distal mid-spans 854, thereby damaging them. It is conceivable that some materials (e.g., metals or plastics) are more resistant to abrasion than composite materials. Therefore, the use of the cover structure 804 ensures that abrasion will not damage the engine component 800.

[0116] Compared to conventional engine components with conventional cover structures, the advantages of this disclosure include a cover structure that provides a stronger bond to the corresponding portion of the engine component to which it is attached. For example, conventional cover structures are attached to the corresponding portion of conventional engine components using conventional methods such as welding, adhesion, gluing, friction, and fastening.

[0117] When a conventional cover structure is attached to the rest of a conventional engine component using fasteners or other external parts, additional components are required on the conventional engine component; this increases the complexity, size, weight, and manufacturing burden of the conventional engine component. The increased weight of the conventional engine component ultimately reduces the efficiency of the turbine engine. As described herein, the cover structure uses extensions to effectively attach the cover structure to the composite structure, thereby eliminating the need for a complex fastening system to connect the two; thus improving the overall efficiency of the turbine engine. However, in some cases, simple fasteners (e.g., Figure 9 Fasteners 746 are used to provide additional support and stability between the composite structure and the cover structure. In some cases, a set of aligners and a set of alignment channels are used to lock, align, and attach the cover structure to the composite structure by combining the extension of the cover structure.

[0118] When relying on welding, adhesion, friction, or gluing, the mating area determines the strength of the connection. As described in this article, the cover structure supports a larger mating area than a conventional cover structure because the cover structure includes extensions, while a conventional cover structure does not. Therefore, the cover structure provides a stronger bond with composite structures compared to a conventional cover structure.

[0119] Compared to conventional engine components, the stronger bond between the cover structure and the composite structure further ensures better resilience of the engine component to forces (such as operating forces, external forces, etc.). When forces are applied to conventional engine components, if the conventional cover structure is not adequately connected to the corresponding part of the conventional engine component, the cover structure may shift, be damaged, or fail to absorb the force as intended. However, as mentioned earlier, sufficient connection can be ensured by using fasteners, which increases the complexity, weight, and manufacturing burden of conventional engine components. When using other connection methods (such as welding, adhesion, friction, adhesive bonding, etc.), the ability of the cover structure to withstand higher forces depends on a good fit between the cover structure and the corresponding part of the engine component. As mentioned earlier, the cover structure has a larger mating area than the conventional cover structure. Therefore, when using welding, adhesion, friction, or adhesive bonding as connection methods, the cover structure described herein has a higher resilience to forces.

[0120] Within the scope not described herein, various features and structures of the various embodiments may be combined or substituted for each other as needed. All combinations or arrangements of the features described herein are covered by this disclosure.

[0121] This written description uses examples to illustrate various aspects of the disclosure described herein, including best practices, and to enable any person skilled in the art to practice various aspects of this disclosure, including making and using any device or system and performing any combined methods. The patentable scope of various aspects of this disclosure is defined by the claims and may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially indistinguishable from the literal language of the claims.

[0122] Further details are provided by the following topics:

[0123] An engine component for a turbine engine, the engine component comprising: a composite structure having a composite structure outer wall, a composite structure edge, and a channel disposed along the composite structure edge; and a cover structure surrounding at least a portion of the composite structure outer wall, the cover structure including a body and an extension, the body extending along the at least a portion of the composite structure outer wall, the extension being received within the channel.

[0124] The engine component according to any one of the preceding clauses, wherein when viewed along a plane partially perpendicular to the edge of the composite structure and intersecting the cover structure, the cover structure includes a non-constant cross-sectional area along the edge of the composite structure.

[0125] The engine component according to any one of the preceding clauses, wherein the cover structure extends axially along the entire edge of the composite structure.

[0126] The engine component according to any one of the preceding clauses, wherein the composite structure includes an airfoil portion having an outer wall defining an outer wall of the composite structure.

[0127] The engine component according to any one of the preceding clauses, wherein the outer wall extends between the root and tip of the composite structure and between the leading edge and trailing edge of the composite structure, wherein the edge of the composite structure is at least one of the tip of the composite structure, the leading edge of the composite structure, or the trailing edge of the composite structure.

[0128] In any of the preceding clauses, the edge of the composite structure is the leading edge of the composite structure.

[0129] An engine component according to any one of the preceding clauses, wherein the engine component is an airfoil assembly having an airfoil portion and a mid-span shield, the airfoil portion extending between a root and a tip, the mid-span shield extending from the airfoil assembly, the mid-span shield being the composite structure.

[0130] The engine component according to any one of the preceding clauses, wherein the cover structure covers at least a portion of the leading edge of the composite structure.

[0131] The engine component according to any one of the preceding clauses, wherein the outer wall of the composite structure extends between the leading edge and the trailing edge of the composite structure, the mid-span cover includes a mid-span distal end that interconnects the trailing edge and the leading edge of the composite structure, and the cover structure covers at least a portion of the mid-span distal end.

[0132] The engine component according to any one of the preceding clauses, wherein the turbine engine has an engine centerline; the airfoil assembly includes two adjacent airfoil portions circumferentially spaced relative to the engine centerline; the mid-span shroud extends discontinuously between the composite structures to define circumferentially opposite mid-span distal ends; and the cover structure is disposed along the opposite mid-span distal ends.

[0133] The engine component according to any one of the preceding clauses, wherein the turbine engine includes a fan section, and the composite structure is the fan housing of the fan section.

[0134] The engine component according to any one of the preceding clauses, wherein the cover structure is disposed along the rear edge of the composite structure.

[0135] The engine component according to any one of the preceding clauses, wherein the turbine engine includes an engine housing, and wherein the cover structure operatively connects the fan housing to the engine housing.

[0136] The engine component according to any one of the preceding clauses, wherein the composite structure includes an alignment channel disposed along the outer wall of the composite structure, and the cover structure includes an aligner disposed along the body, the aligner being received within the alignment channel.

[0137] The engine component according to any one of the preceding clauses, wherein the composite structure includes a centerline extending from the edge of the composite structure; the body extends axially with respect to the centerline by a first centerline length; and the extension extends axially with respect to the centerline by a second centerline length, the second centerline length being greater than or equal to 10% and less than or equal to 100% of the first centerline length.

[0138] The engine component according to any one of the preceding clauses, wherein the extension includes a set of barbs extending into the composite structure.

[0139] The engine component according to any one of the preceding clauses, wherein when viewed along a plane that is partially perpendicular to the edge of the composite structure and intersects the extension, the extension comprises a triangular shape.

[0140] In any of the preceding clauses, at least a portion of the extension is bifurcated.

[0141] The engine component according to any one of the preceding clauses, wherein the extension comprises a rectangular shape when viewed along a plane that is partially perpendicular to the edge of the composite structure and intersects with the extension.

[0142] The engine component according to any one of the preceding clauses, wherein the cover structure comprises at least one of a metallic material or a plastic material.

[0143] The engine component according to any one of the preceding clauses, wherein the cover structure comprises at least one of titanium, aluminum, or polyurethane.

[0144] The engine component according to any one of the preceding clauses, wherein the composite structure comprises a composite material, the composite material comprising at least one of a polymer matrix composite, a ceramic matrix composite, a metal matrix composite, carbon fiber, a polymer resin, a thermoplastic, bismaleimide, polyimide, epoxy resin, glass fiber, or a silicon matrix.

[0145] The engine component according to any one of the preceding clauses further includes fasteners that operatively connect the cover structure to the composite structure.

[0146] An engine component according to any one of the preceding clauses, wherein the fastener extends through corresponding portions of the composite structure and the cover structure.

[0147] The engine component according to any one of the preceding clauses, wherein the fastener extends through a corresponding portion of the extension.

[0148] An engine component according to any one of the preceding clauses, wherein when the cover structure is attached to the composite structure, the cover structure extends continuously from the outer wall of the composite structure.

[0149] The engine component according to any one of the preceding clauses, wherein the outer surface of the cover structure abuts flush with the outer wall at the distal end of the body relative to the outer wall.

[0150] The engine component according to any one of the preceding clauses, wherein the outer surface of the cover structure is recessed relative to the outer wall at the distal end of the body.

[0151] The engine component according to any one of the preceding clauses, wherein the outer surface of the cover structure is disposed radially outward relative to the outer wall at the distal end of the body to form a stepped joint.

[0152] The engine component according to any one of the preceding clauses, wherein the cover structure is pre-cured or co-molded with the composite structure.

[0153] The engine component according to any one of the preceding clauses, wherein a joint is formed between the cover structure and the composite structure, the joint being at least one of a butt joint, an lap joint, an interlocking joint, or a stepped joint.

[0154] A turbofan engine includes: an engine core having a compressor section, a combustion section, and a turbine section arranged in a series flow configuration, the engine core defining a rotor and a stator; an engine housing surrounding at least a portion of the engine core; a fan section coupled to the rotor, the fan section including a fan housing, the fan housing including a composite structure having an outer wall, an edge of the composite structure, and a channel disposed along the edge of the composite structure; and a cover structure surrounding at least a portion of the outer wall, the cover structure coupling the fan housing to the engine housing.

[0155] The turbine engine according to any one of the preceding clauses, wherein when viewed along a plane that is partially perpendicular to the edge of the composite structure and intersects the cover structure, the cover structure includes a non-constant cross-sectional region along the edge of the composite structure.

[0156] The turbine engine according to any one of the preceding clauses, wherein the cover structure extends axially along the entire edge of the composite structure.

[0157] The turbine engine according to any one of the preceding clauses, wherein the composite structure includes an airfoil portion having an outer wall defining the outer wall of the composite structure.

[0158] The turbine engine according to any one of the preceding clauses, wherein the outer wall extends between the root and tip of the composite structure and between the leading edge and trailing edge of the composite structure, wherein the edge of the composite structure is at least one of the tip of the composite structure, the leading edge of the composite structure, or the trailing edge of the composite structure.

[0159] In the turbine engine according to any one of the preceding clauses, the edge of the composite structure is the leading edge of the composite structure.

[0160] The turbine engine according to any one of the preceding clauses, wherein the engine component is an airfoil assembly having an airfoil portion and a mid-span shield, the airfoil portion extending between a root and a tip, the mid-span shield extending from the airfoil assembly, the mid-span shield being the composite structure.

[0161] The turbine engine according to any one of the preceding clauses, wherein the composite structure covers at least a portion of the leading edge of the composite structure.

[0162] The turbine engine according to any one of the preceding clauses, wherein the outer wall of the composite structure extends between the leading edge and the trailing edge of the composite structure, the mid-span shroud includes a mid-span distal end that interconnects the trailing edge and the leading edge of the composite structure, and the cover structure covers at least a portion of the mid-span distal end.

[0163] The turbine engine according to any one of the preceding clauses, wherein the turbine engine has an engine centerline; the airfoil assembly includes two adjacent airfoil portions circumferentially spaced apart relative to the engine centerline; the mid-span shroud extends discontinuously between the composite structures to define circumferentially opposite mid-span distal ends; and the cover structure is disposed along the opposite mid-span distal ends.

[0164] The turbine engine according to any one of the preceding clauses, wherein the turbine engine includes a fan section, and the composite structure is the fan housing of the fan section.

[0165] The turbine engine according to any one of the preceding clauses, wherein the cover structure is disposed along the trailing edge of the composite structure.

[0166] The turbine engine according to any one of the preceding clauses, wherein the turbine engine includes an engine housing, and wherein the cover structure operatively connects the fan housing to the engine housing.

[0167] The turbine engine according to any one of the preceding clauses, wherein the composite structure includes an alignment channel disposed along the outer wall of the composite structure, and the cover structure includes an aligner disposed along the body, the aligner being received within the alignment channel.

[0168] The turbine engine according to any one of the preceding clauses, wherein the composite structure includes a centerline extending from the edge of the composite structure; the body extends axially with respect to the centerline by a first centerline length; and the extension extends axially with respect to the centerline by a second centerline length, the second centerline length being greater than or equal to 10% and less than or equal to 100% of the first centerline length.

[0169] The turbine engine according to any one of the preceding clauses, wherein the extension includes a set of barbs extending into the composite structure.

[0170] The turbine engine according to any one of the preceding clauses, wherein when viewed along a plane that is partially perpendicular to the edge of the composite structure and intersects the extension, the extension comprises a triangular shape.

[0171] In any of the preceding clauses, at least a portion of the extension is bifurcated in the turbine engine.

[0172] The turbine engine according to any one of the preceding clauses, wherein when viewed along a plane that is partially perpendicular to the edge of the composite structure and intersects the extension, the extension comprises a rectangular shape.

[0173] According to the turbine engine described in the foregoing clause, the cover structure comprises at least one of a metallic material or a plastic material.

[0174] According to the turbine engine described in the foregoing clause, the cover structure includes at least one of titanium, aluminum, or polyurethane.

[0175] The turbine engine according to any one of the preceding clauses, wherein the composite structure comprises a composite material, the composite material comprising at least one of a polymer matrix composite, a ceramic matrix composite, a metal matrix composite, carbon fiber, a polymer resin, a thermoplastic, bismaleimide, polyimide, epoxy resin, glass fiber, or a silicon matrix.

[0176] The turbine engine according to any one of the preceding clauses, wherein the engine component further includes fasteners operatively connecting the cover structure to the composite structure.

[0177] The turbine engine according to any one of the preceding clauses, wherein the fastener extends through corresponding portions of the composite structure and the cover structure.

[0178] The turbine engine according to any one of the foregoing clauses, wherein the fastener extends through a corresponding portion of the extension.

[0179] The turbine engine according to any one of the preceding clauses, wherein when the cover structure is attached to the composite structure, the cover structure extends continuously from the outer wall of the composite structure.

[0180] The turbine engine according to any one of the preceding clauses, wherein the outer surface of the cover structure abuts flush with the outer wall at the distal end of the body relative to the outer wall.

[0181] The turbine engine according to any one of the preceding clauses, wherein the outer surface of the cover structure is recessed relative to the outer wall at the distal end of the body.

[0182] According to any one of the preceding clauses, in the turbine engine, the outer surface of the cover structure is radially outward relative to the outer wall at the distal end of the body to form a stepped joint.

[0183] According to the turbine engine described in the foregoing clauses, the cover structure is pre-cured or co-molded with the composite structure.

[0184] The turbine engine according to any one of the preceding clauses, wherein a joint is formed between the cover structure and the composite structure, the joint being at least one of a butt joint, an lap joint, an interlocking joint, or a stepped joint.

Claims

1. An engine component for a turbine engine, characterized in that, The engine components include: A composite structure having an outer wall, an edge, and a channel along the edge, the composite structure having a centerline extending from the edge; and A cover structure that surrounds at least a portion of the outer wall of the composite structure, the cover structure including a body and an extension, the body extending integrally along at least a portion of the outer wall of the composite structure axially spaced behind the edge of the composite structure at the center line relative to the center line, the extension being received within the channel, the junction of the extension and the body coinciding with the edge of the composite structure at the center line.

2. The engine component according to claim 1, characterized in that, in: The composite structure includes an airfoil portion having an outer wall defining the outer wall of the composite structure; and The outer wall of the composite structure extends between the root and tip of the composite structure and between the leading and trailing edges of the composite structure, wherein the edge of the composite structure is at least one of the tip, the leading edge, or the trailing edge of the composite structure.

3. The engine component according to claim 1, characterized in that, The engine component therein is an airfoil assembly having an airfoil portion and a mid-span shield, the airfoil portion extending between a root and a tip, and the mid-span shield extending from the airfoil assembly, the mid-span shield being the composite structure.

4. The engine component according to claim 3, characterized in that, The outer wall of the composite structure extends between the front edge and the rear edge of the composite structure, the mid-span cover includes a mid-span distal end that interconnects the rear edge and the front edge of the composite structure, and the cover structure covers at least a portion of the mid-span distal end.

5. The engine component according to claim 3, characterized in that, in: The turbine engine has an engine centerline; The airfoil assembly includes two adjacent airfoil portions that are circumferentially spaced apart relative to the engine centerline; The mid-span shroud extends discontinuously between the two adjacent airfoil portions to define circumferentially opposite mid-span distal ends; and The cover structure is positioned along the distal end of the opposite mid-span.

6. The engine component according to claim 1, characterized in that, The turbine engine includes a fan section, and the composite structure is the fan housing of the fan section.

7. The engine component according to claim 6, characterized in that, The cover structure is disposed along the rear edge of the composite structure.

8. The engine component according to claim 7, characterized in that, The turbine engine includes an engine housing, and the cover structure connects the fan housing to the engine housing.

9. The engine component according to claim 1, characterized in that, The composite structure includes an alignment channel disposed along the outer wall of the composite structure, and the cover structure includes an aligner disposed along the body, the aligner being received within the alignment channel.

10. The engine component according to claim 1, characterized in that, in: The main body extends axially relative to the centerline by a first centerline length; and The extension extends axially relative to the center line by a second center line length, the second center line length being greater than or equal to 10% of the first center line length and less than or equal to 100% of the first center line length.

11. The engine component according to claim 1, characterized in that, The extension includes a set of barbs extending into the composite structure.

12. The engine component according to claim 1, characterized in that, When viewed along a plane that is partially perpendicular to the edge of the composite structure and intersects with the extension, the extension comprises a triangular shape.

13. The engine component according to claim 1, characterized in that, At least a portion of the extension is bifurcated.

14. The engine component according to claim 1, characterized in that, When viewed along a plane that is partially perpendicular to the edge of the composite structure and intersects with the extension, the extension has a rectangular shape.

15. The engine component according to claim 1, characterized in that, The cover structure comprises at least one of a metallic material or a plastic material.

16. The engine component according to claim 1, characterized in that, The main body and the extension are integrally formed.

17. The engine component according to claim 1, characterized in that, The extension extends continuously relative to the edge of the composite structure by a distance greater than or equal to 75% and less than or equal to 100% of the total range of the edge of the composite structure.

18. The engine component according to claim 1, characterized in that, The channel extends into the composite structure in a first direction relative to the centerline; and When viewed along a plane extending along the centerline and intersecting the cover structure, the extension has a cross-sectional area that is not constant within the channel in a second direction transverse to the first direction.

19. The engine component according to claim 18, characterized in that, The engine component is an airfoil, the first direction is the chord direction of the airfoil, and the second direction is the span direction of the airfoil.

20. An engine component for a turbine engine, characterized in that, The engine components include: A composite structure having an outer wall, an edge, and a channel along the edge, the composite structure having a centerline extending from the edge; and A cover structure that surrounds at least a portion of the outer wall of the composite structure, the cover structure including a body and an extension, the body extending along at least a portion of the outer wall of the composite structure, the extension being received within the channel; in: The main body terminates at its distal end, and the distal end of the main body is axially spaced backward from the centerline and the edge of the composite structure by a first centerline length; and The extension terminates at its distal end, which is axially spaced from the centerline and the edge of the composite structure by a second centerline length. The length of the second centerline is greater than or equal to 10% of the length of the first centerline and less than or equal to the length of the first centerline.

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