Acoustic turbofan airfoil apparatus

Abstract

An acoustic turbine fan airfoil apparatus is disclosed. An example apparatus includes a platform of a turbofan engine, the platform including a perforation to receive an acoustic wave; an acoustic cavity protruding from a first side of the platform, the acoustic cavity aligned with the perforation in a radial direction defined by the turbofan engine, the acoustic cavity to attenuate the acoustic wave; and an airfoil protruding from a second side of the platform opposite the first side of the platform.

Description

Technical Field

[0001] This disclosure generally relates to turbofans, and more specifically, to acoustic turbofan airfoil platforms and related equipment. Background Technology

[0002] Generally, aircraft engines are the primary source of noise in aircraft, especially during takeoff and climb. Due to their rotating mechanical components and the aerodynamic airflow passing through them, aircraft engines typically generate significant mechanical noise. For example, the airfoil components of an aircraft engine produce narrow bands of high-intensity peaks corresponding to their rotational speed. Attached Figure Description

[0003] Figure 1 shows a schematic cross-sectional view of a prior art example of a turbofan engine.

[0004] Figure 2 shows a prior art example of an acoustic panel for a turbofan engine.

[0005] Figure 3 An example turbofan engine with an example acoustic turbofan airfoil device according to the teachings disclosed herein is shown.

[0006] Figure 4A It shows Figure 3 A detached stereoscopic view of an example acoustic turbine fan airfoil device.

[0007] Figure 4B It shows Figure 4A A cross-sectional view of an example acoustic turbine fan airfoil device.

[0008] Figure 5 A separate stereoscopic view of another example acoustic turbine fan airfoil device is shown, based on the teachings disclosed herein.

[0009] These figures are not drawn to scale. Generally, the same reference numerals will be used throughout the figures and the accompanying written description to refer to the same or similar parts. As used herein, unless otherwise stated, a connection reference (e.g., attachment, coupling, joining, and joining) may include intermediate members between the elements referred to by the connection reference and / or relative movement between these elements. Therefore, a connection reference does not necessarily imply that two elements are directly connected and / or have a fixed relationship with each other. As used herein, stating that any part is in “contact” with another part is defined as meaning that there is no intermediate part between the two parts.

[0010] Unless otherwise expressly stated, descriptors such as “first,” “second,” and “third” are used herein not to imply or otherwise indicate any meaning of priority, physical order, arrangement in a list, and / or any sorting, but merely as labels and / or arbitrary names to distinguish elements for ease of understanding of the disclosed examples. In some examples, the descriptor “first” may be used to refer to an element in the detailed description, while different descriptors (e.g., “second” or “third”) may be used in the claims to refer to the same element. In such cases, it should be understood that such descriptors are only used to clearly identify those elements that may, for example, otherwise share the same name.

[0011] The approximate language used throughout this specification and claims is applied to modify any quantitative expression that may allow for variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” and “substantially” are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of ten percent.

[0012] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0013] The terms "upstream" and "downstream" refer to the relative directions of flow along a path. For example, in fluid flow, "upstream" refers to the direction from which the fluid flows, while "downstream" refers to the direction in which the fluid flows. Detailed Implementation

[0014] The Federal Aviation Administration (FAA) specifies the maximum noise level that a single civil aircraft can emit, as defined in Chapter 14, Part 36 of the Common Regulations of the United States (CFR). However, the noise produced by a turbofan engine is directly proportional to its operating speed. Therefore, the speed of an aircraft may be limited by the noise level it produces.

[0015] To meet regulatory requirements, aircraft typically include noise attenuation structures in their associated turbofan engines. In some embodiments, the turbofan engine includes a honeycomb core attached to the inner wall of the inlet duct to attenuate sound waves impacting the turbofan engine surface. Furthermore, the surfaces of the flow path of the turbofan engine may include perforations for receiving sound waves. In some embodiments, the honeycomb core and / or the perforated surfaces are positioned between the mounting surfaces of the stationary guide vanes of the turbofan engine (e.g., inlet guide vanes, outlet guide vanes).

[0016] However, incorporating perforated surfaces and / or honeycomb cores between and / or around the mounting surfaces of stationary guide vanes involves additional structure, thus increasing the vehicle's weight. Furthermore, adapting perforated surfaces and / or honeycomb cores between the mounting surfaces of the vanes reduces the area of ​​the flow path and limits the proximity at which the noise attenuation structure can be positioned relative to the vane. In turn, this noise attenuation structure increases fuel consumption for propulsion while reducing the vehicle's maximum speed. Moreover, this noise attenuation structure is limited by the percentage of surface area of ​​the flow path that contributes to noise attenuation.

[0017] The examples disclosed herein provide an acoustic turbofan airfoil device for attenuating sound waves in a turbofan engine. In some examples, the turbofan engine (e.g., an aircraft engine) includes a platform positioned along the boundary of a flow path. In some examples, the turbofan engine platform includes openings (e.g., holes, orifices, perforations, etc.) for receiving sound waves. In some examples, an acoustic cavity is coupled to and / or protrudes from a first side of the turbofan engine platform opposite the flow path. In some examples, the airfoil protrudes from a second side of the platform's surface defining the flow path. That is, the airfoil is integral with the platform.

[0018] In some examples, the platform defines the inner surface of the flow path of the turbine engine because a first radial end of the airfoil extends from it. Additionally or alternatively, the platform may define the outer surface of the flow path of the turbofan engine because a second radial end of the airfoil opposite the first radial end extends from it. In some examples, the platform defines the surface of the turbofan engine nacelle (e.g., the inner radial surface of the nacelle). In some examples, the platform defines the surface of the turbofan engine casing (e.g., the inner radial surface of the casing, the outer radial surface of the casing). In some examples, the platform defines the surface of the turbofan engine shaft (e.g., a rotating surface, a non-rotating surface). Therefore, the airfoil can be implemented as an inlet guide vane, an outlet guide vane, a fan blade, a rotor blade, a stator blade, and / or any other airfoil in a turbofan engine. In some examples, the platform may rotate relative to the surface of the turbofan engine to which the platform is attached, thus enabling the airfoil to be used as a variable-pitch airfoil.

[0019] In some examples, the acoustic cavity is aligned with one or more openings in the platform. In other examples, the openings in the platform receive sound waves and subsequently scatter or disperse them into the acoustic cavity. Furthermore, the existing air within the acoustic cavity provides a buffer that allows the cavity to suppress sound waves. Therefore, the acoustic cavity can receive and attenuate sound waves encountered by the inner and / or outer radial surfaces of the turbine engine's flow path.

[0020] In some examples, the size, shape, orientation, and / or distribution of the openings are based on the position of some openings relative to the airfoil and / or within the associated flow path. Similarly, the size and / or shape of the acoustic cavity may be based on the position of the acoustic cavity relative to the airfoil and / or the openings. In some examples, the openings are unevenly distributed along the platform. For example, a larger portion of the openings may be located near the leading edge of the airfoil compared to the trailing edge. Additionally or alternatively, the distribution of the openings may be directly related to the proximity of the openings relative to the airfoil. In some examples, the openings include a first opening having a first size and / or shape and a second opening having a second size and / or shape different from the first size and / or shape. In some examples, the openings include a first opening having a first angular orientation relative to the platform and a second opening having a second angular orientation relative to the platform.

[0021] In some examples, the platform, acoustic cavity, and airfoil are manufactured using additive manufacturing. In some examples, the airfoil is integrally formed with the platform, and the acoustic cavity is attached to the platform by adhesives (e.g., epoxy adhesives) and / or brazing. In some examples, the platform is attached to the surface of the turbofan engine by dovetail joints and / or by mechanical fasteners (e.g., nuts, bolts, screws, etc.). In some examples, the acoustic cavity may be constructed by... Cellular, aluminum cellular, additive metal alloy, and / or additive polymer formations are used. In some examples, the platform and airfoil may be made of metal, polymer, and / or ceramic materials.

[0022] Referring now to the accompanying drawings, FIG1 is a schematic cross-sectional view of a prior art example of a turbofan engine 100, which can be combined with various examples disclosed herein. As shown in FIG1, the turbofan engine 100 defines a longitudinal or axial central axis 102 extending therethrough for reference. Typically, the turbofan engine 100 may include a core turbine or core turbine engine 104 disposed downstream of a fan section 106.

[0023] The core turbine engine 104 typically includes a generally tubular outer casing 108 defining an annular inlet 110. The casing 108 may be formed of multiple segments. The casing 108 surrounds a compressor segment having a supercharger or low-pressure compressor 112 (“LP compressor 112”) and a high-pressure compressor 114 (“HP compressor 114”) in a series flow relationship; a combustion segment 116; a turbine segment having a high-pressure turbine 118 (“HP turbine 118”) and a low-pressure turbine 120 (“LP turbine 120”); and an exhaust segment 122. A high-pressure shaft or spool 124 (“HP shaft 124”) drivesably connects the HP turbine 118 and the HP compressor 114. A low-pressure shaft or spool 126 (“LP shaft 126”) drivesably connects the LP turbine 120 and the LP compressor 112. The LP shaft 126 may also be connected to a fan shaft or spool 128 of the fan segment 106. In some examples, the LP shaft 126 can be directly coupled to the fan shaft 128 (i.e., a direct drive configuration). In alternative configurations, the LP shaft 126 can be coupled to the fan shaft 128 via a reduction gearbox 130 (i.e., an indirect drive or gear-driven configuration).

[0024] As shown in Figure 1, fan section 106 includes a plurality of fan blades 132 (“fan” 132) coupled to and extending radially outward from fan shaft 128. An annular fan housing or nacelle 134 circumferentially surrounds at least a portion of fan section 106 and / or core turbine engine 104. Nacelle 134 may be supported relative to core turbine engine 104 by a forward mounting member 136. Furthermore, a downstream section 138 of nacelle 134 may surround an external portion of core turbine engine 104 to define a bypass airflow passage 140 therebetween.

[0025] As shown in Figure 1, air 142 enters the intake or inlet portion 144 of the turbofan engine 100 during operation. A first portion 146 of the air 142 flows into a bypass airflow passage 140, while a second portion 148 of the air 142 flows into the inlet 110 of the LP compressor 112. One or more sequential stages of the LP compressor stator blades 150 and rotor blades 152, coupled to the LP shaft 126, progressively compress the second portion 148 of the air 142 flowing through the LP compressor 112 and directed into the HP compressor 114. Next, one or more sequential stages of the HP compressor stator blades 154 and rotor blades 156, coupled to the HP shaft 124, further compress the second portion 148 of the air 142 flowing through the HP compressor 114. This provides compressed air 158 to the combustion section 116, where the compressed air 158 is mixed with fuel and burned to provide combustion gases 160.

[0026] Combustion gas 160 flows through HP turbine 118, where one or more sequential stages of HP turbine stator blades 162 and HP turbine rotor blades 164, coupled to HP shaft 124, extract a first portion of kinetic and / or thermal energy. This energy extraction supports the operation of HP compressor 114. Combustion gas 160 then flows through LP turbine 120, where one or more sequential stages of LP turbine stator blades 166 and LP turbine rotor blades 168, coupled to LP shaft 126, extract a second portion of thermal and / or kinetic energy. This energy extraction causes LP shaft 126 to rotate, thereby supporting the operation of LP compressor 112 and / or rotation of fan shaft 128. Combustion gas 160 then exits core turbine 104 through exhaust section 122 of core turbine 104.

[0027] Together with the turbofan engine 100, the core turbine 104 serves a similar purpose and experiences a similar environment in land-based turbines and turbojet engines, where the ratio of the first portion 146 of air 142 to the second portion 148 of air 142 is less than that in turbofan and ductless fan engines (where fan section 106 lacks nacelle 134). In each of the turbofan, turbojet, and ductless engines, a reduction gear (e.g., reduction gearbox 130) may be included between any shaft and spool. For example, reduction gearbox 130 may be disposed between LP shaft 126 and fan shaft 128 of fan section 106.

[0028] As depicted therein, the turbofan engine 100 defines an axial direction A, a radial direction R, and a circumferential direction C. Generally, the axial direction A extends approximately parallel to the axial centerline axis 102, the radial direction R extends perpendicularly outward from the axial centerline axis 102, and the circumferential direction C extends concentrically around the axial centerline axis 102.

[0029] Figure 2 shows an enlarged view of the fan section 106 of the turbofan engine 100 of Figure 1. In the example shown in Figure 2, the fan section 106 includes an example prior art acoustic panel 200. The prior art acoustic panel 200 is coupled to the nacelle 134. The prior art acoustic panel 200 includes a honeycomb structure 202 positioned between a backplate 204 and perforated plates 206 facing the axial centerline 102. The perforated plates 206 include perforations evenly distributed and oriented perpendicular to the axial centerline 102. Therefore, the prior art acoustic panel 200 attenuates some sound waves encountered through the inlet 144 of the bypass airflow passage 140 and / or some sound waves generated by the fan blades 132. However, because the prior art acoustic panel 200 is spaced apart from, for example, airfoil elements (fan blades 132) that generate and / or disperse sound waves, the prior art acoustic panel 200 cannot absorb some sound waves generated by the fan blades 132. Therefore, some sound waves will be deflected from surfaces that do not provide sound attenuation, such as the fan blades 132 from the surfaces they extend from (e.g., the outer radial surface of the fan shaft 128 in FIG1), which further disperses and / or amplifies the sound waves, increasing the overall noise generated by the turbofan engine 100.

[0030] Figure 3 A cross-sectional view of an example turbofan engine 300 including an example acoustic device 302 according to the teachings disclosed herein is shown. Specifically, the cross-sectional view of the example shown represents an example fan segment 304 of the turbofan engine 300 (e.g., fan segment 106 of Figures 1 and 2).

[0031] exist Figure 3 In this acoustic device 302, an example platform (e.g., a panel, plate, etc.) 306, a first side (e.g., an outer radial surface) 310 coupled to and / or extending therefrom of the platform 306, and an airfoil 312 projecting from a second side (e.g., an inner radial surface) 314 of the platform 306. Specifically, the outer radial end 316 of the airfoil 312 projectes from the second side 314 of the platform 306 (e.g., integral with and formed as part of the second side 314 of the platform 306).

[0032] exist Figure 3 In the example shown, platform 306 is connected to the nacelle 318 of turbofan engine 300 via mechanical fasteners 320. In some examples, the sidewall 322 of acoustic device 302 extending from platform 306 is connected to nacelle 318 via dovetail joints. In the example shown, acoustic device 302 is positioned in the axial direction A between inlet 324 (e.g., inlet 144 of Figures 1 and 2) and fan 326 (e.g., fan 132 of Figures 1 and 2) of turbofan engine 300. Therefore, Figure 3The airfoil element 312 in the example shown is an inlet guide vane 312. Therefore, the inlet guide vane 312 extends radially away from the nacelle 318 toward the axial centerline axis of the turbofan engine 300 (e.g., axial centerline axis 102 of FIG. 1). Specifically, the inlet guide vane 312 is a partial-span inlet guide vane 312, as described in U.S. Patent No. 10,711,797B2, which is incorporated herein by reference in its entirety.

[0033] exist Figure 3 In the illustrated example, platform 306 includes holes (e.g., orifices, perforations, openings, etc.) to receive acoustic waves encountered and / or generated by inlet 324, inlet guide vane 312, and / or fan 326. In some examples, the holes are formed by drilling or laser drilling, which allows for defining specific shapes (e.g., circular, elliptical, etc.), orientations (e.g., perpendicular or non-perpendicular relative to platform 306), distributions, or sizes for each hole. For example, the shape, orientation, and / or size of the holes can be based on the position of each hole in the turbofan engine 300, the position or spatial relationship of each hole relative to other holes in the platform, the position or spatial relationship of each hole relative to airfoil 312, and / or the position or spatial relationship of each hole relative to other airfoils such as the blades of fan 326. Thus, the shape, orientation, distribution, and / or size of the holes can be constructed based on the aerodynamic characteristics associated with the position of each hole in the turbofan engine 300, which allows the holes to receive an additional portion of the acoustic waves within the turbofan engine 300 compared to perforations in the perforated sheet 206 of the prior art acoustic panel 200.

[0034] In some examples, the airfoil 312 encounters and / or generates sound waves while producing aerodynamics, which affects the propagation of the sound waves within the turbofan engine 300. Therefore, the shape, orientation, distribution, and / or size of the apertures in the platform 306 can be based on the aerodynamic characteristics associated with the airfoil 312 and / or other airfoils (e.g., the blades of the fan 326) in the turbofan engine 300 to maximize or otherwise increase the reception of sound waves. For example, apertures in the platform 306 located near the leading edge 328 of the airfoil 312 can be oriented at least partially toward the inlet 324 of the turbofan engine 300, allowing the increased area of ​​the apertures to be positioned along the travel paths 330a, 330b, 330c, 330d, 330e, and 330f of the sound waves generated and / or encountered by the airfoil 312, inlet 324, and / or fan 326.

[0035] Furthermore, since the holes are formed in the inlet guide vane 312 from its protruding platform 306, the placement of the individual holes in the platform offers increased flexibility compared to the perforations in the perforated plate 206 of the prior art acoustic panel 200. For example, the hole in the platform 306 near the side 327 of the airfoil 312 can be formed in a rectangular shape, with its longer portion spanning in the axial direction A to receive an increased portion of the sound waves propagating along the side edge 327 of the airfoil 312. Additionally, a portion of the hole in the platform 306 can be positioned near the leading edge 328, trailing edge 332, and / or any other location in the platform 306 to receive the sound waves generated by the inlet guide vane 312, which would otherwise prevent the acoustic panel (e.g., the prior art acoustic panel 200) from being separated from and / or spaced apart from the airfoil 312.

[0036] In some examples, the holes in platform 306 have a denser distribution in certain areas of turbofan engine 300 and a looser distribution in other areas of turbofan engine 300. For example, when the acoustic device 302 is implemented in an area of ​​turbofan engine 300 associated with highly variable and / or unpredictable sound wave propagation, the holes located in that area may include a denser distribution and various shapes, sizes, and / or orientations to accommodate different sound wave propagations. Furthermore, when the acoustic device 302 is implemented in an area of ​​turbofan engine 300 associated with substantially uniform sound wave propagation, the holes located in that area may include a uniform shape, size, and / or orientation based on the encountered sound waves, thereby maximizing or otherwise increasing the portion of the sound waves received. In some examples, the holes in platform 306 have increasing spacing between each other in areas of turbofan engine 300 associated with substantially uniform sound wave propagation and / or in other areas encountering sound waves with decreasing frequencies. Therefore, the holes can be unevenly distributed along platform 306 to maximize or otherwise increase the percentage of sound waves passing through the holes while also providing structural support.

[0037] exist Figure 3 In the example shown, one or more holes in platform 306 are aligned with corresponding acoustic cavities 308 in the radial direction R. For example, the peripheries of two or more holes in platform 306 may be aligned within the periphery of an acoustic cavity 308 in the radial direction R. Therefore, acoustic cavity 308 can absorb and / or attenuate sound waves passing through the holes in platform 306. Specifically, the air within acoustic cavity 308 dampens the sound waves, enabling acoustic cavity 308 to provide sound attenuation. In some examples, the size and / or shape of the holes in acoustic cavity 308 and / or platform 306 are based on the volume of air to be positioned within the corresponding acoustic cavity 308 to attenuate sound waves.

[0038] In some examples, the size and / or shape of the corresponding acoustic cavity 308 is based on the amplitude and / or path 330a, 330b, 330c, 330d, 330e, 330f of the sound wave as it travels through the holes in the platform 306 according to the paths 330a, 330b, 330c, 330d, 330e, 330f to maximize or otherwise increase the attenuation of the sound wave. Therefore, the size and / or shape of the acoustic cavity 308 can be based on the size, shape, distribution, and / or orientation of the holes in the platform 306 aligned with the corresponding acoustic cavity 308 in the radial direction R. As a result, the acoustic cavity 308 can optimize or otherwise improve the attenuation of the sound wave compared to the uniform distribution of the honeycomb structure 202 in the prior art acoustic panel 200.

[0039] In some examples, the first acoustic cavity 308 includes a first size and / or a first shape, and the second acoustic cavity 308 includes a second size and / or a second shape different from the first size and / or different from the first shape. Therefore, some acoustic cavities 308 can be configured to increase sound attenuation, while others can be configured to provide increased structural support in addition to sound attenuation. In some examples, the size and / or shape of the acoustic cavity 308 are based on the position of the respective acoustic cavity 308 within the turbofan engine 300, the positional or spatial relationship of the respective acoustic cavity 308 relative to the airfoil 312, and / or the positional or spatial relationship of the respective acoustic cavity 308 relative to other airfoils such as the blades of the fan 326. Because the airfoil 312 is integral with the platform 306, the acoustic cavity 308 can be positioned closer to the airfoil 312 than the honeycomb structure 202 of the prior art acoustic panel 200. Therefore, compared to the honeycomb structure 202 of the prior art acoustic panel 200, the acoustic cavity 308 can provide acoustic attenuation in a region of the turbofan engine 300 closer to the sound source, which prevents or otherwise reduces the deflection and / or propagation of sound waves.

[0040] exist Figure 3 In the example shown, platform 306 and airfoil 312 (e.g., inlet guide vane 312) can be formed of metallic, polymeric, or ceramic materials. Figure 3 In the middle, the acoustic cavity 308 can be made of Cellular, aluminum cell, additive metal alloy, and / or additive polymer units are formed. Figure 3 In this configuration, platform 306, acoustic cavity 308, and airfoil 312 are integrally formed by additive manufacturing. In some examples, platform 306 and airfoil 312 are formed by additive manufacturing, and acoustic cavity 308 is bonded to the first side 310 of platform 306 by adhesive.

[0041] Figure 4A It shows Figure 3 Separated stereo view 400 of example acoustic device 302. Figure 4B It shows Figure 4A The cross section AA of the example acoustic device 302.

[0042] exist Figure 4A In the example shown, platform 306 includes an example aperture (e.g., perforation, pore, orifice, etc.) 402 defined therein. Aperture 402 extends through a first side 310 and a second side 314 of platform 306 to define a flow path through which sound waves can enter acoustic cavity 308. Figure 4A In this configuration, at least two holes 402 are aligned with each acoustic cavity 308. Figure 4A In this embodiment, the aperture 402 includes various sizes, shapes, angular orientations, and density distributions. In some examples, the size, shape, angular orientation, and density distribution of the aperture 402 are based on the airflow pressure associated with the location where the acoustic device 302 is implemented in the turbofan engine 300. For example, in response to a corresponding location in the turbofan engine 300 being associated with a higher pressure airflow, the aperture 402 may include a higher density distribution and / or a larger size. In the illustrated example, the aperture 402 is positioned in the platform 306 from its protruding area around the airfoil 312. In the illustrated example, the aperture 402 includes a non-uniform distribution 404. Therefore, the aperture 402 can receive sound waves generated and / or deflected by the airfoil 312. Because the sound waves are received by the airfoil 312 from its protruding platform 306, the acoustic device 302 minimizes or otherwise reduces the weight of the turbofan engine 300, which would otherwise be increased by an acoustic panel (e.g., prior art acoustic panel 200) separated from the airfoil 312.

[0043] exist Figure 4AIn the illustrated examples, the size, shape, angular orientation, and / or non-uniform distribution 404 of each aperture 402 may be based on the acoustic waves encountered by the platform 306 and the paths of their travel 330a, 330b, 330c, 330d, 330e, 330f. In some examples, one or more apertures 402 minimize or otherwise reduce the surface area of ​​the platform 306, where acoustic waves can be deflected and contact the airfoil 312. In some examples, one or more apertures 402 maximize or otherwise increase the reception of acoustic waves generated and / or encountered by the airfoil 312. For example, one or more apertures 402 may include an angular orientation at least partially facing the same direction as the leading edge 328 of the airfoil 312 to receive acoustic waves generated by the airfoil 312 and / or in front of the airfoil 312 in the axial direction A. Furthermore, one or more apertures 402 may include an angular orientation at least partially facing in the same direction as the trailing edge 332 of the airfoil 312 to receive sound waves generated by other airfoils (e.g., fan blades 326) disposed behind the airfoil 312 in the axial direction A. Additionally, one or more apertures 402 may be at least partially facing towards the side surface 327 of the airfoil 312 to receive sound waves generated and / or deflected by the side surface 327. Additionally or alternatively, one or more apertures 402 may be at least partially facing away from the side surface 327 to receive sound waves generated by other airfoils, which also minimizes or otherwise reduces sound waves deflected by the airfoil 312. In some examples, one or more apertures 402 are vertically positioned in the platform 306. Furthermore, the size, shape, and / or non-uniform distribution 404 of the individual apertures 402 may be based on the orientation of the apertures 402 and / or the possible paths of the sound waves received by the apertures 402.

[0044] In some examples, the size and / or shape of each orifice 402 is based on the air volume to be positioned within its associated acoustic cavity 308. For example, to provide maximum or otherwise increased acoustic attenuation, the size of each orifice 402 may be large enough to receive as many sound waves as possible, while also being small enough to maintain at least a portion of the air volume within the acoustic cavity 308 and the structural integrity of the platform 306. In some examples, the size and / or shape of the acoustic cavity 308 and / or the orifices 402 aligned therewith are based on parameters that determine the air volume to be positioned within the acoustic cavity 308, such as the amplitude or amplitude range and / or frequency or frequency range of the sound waves typically entering the acoustic cavity 308. Therefore, the size, shape, orientation, and / or non-uniform distribution 404 of the orifices 402, and the size and / or shape of the acoustic cavity 308, may be determined based on the location of the individual orifices 402 and the acoustic cavity 308 within the turbofan engine 300. As a result, the size, shape, angular orientation, and / or non-uniform distribution 404 of the orifice 402 and the size and / or shape of the acoustic cavity 308 can maximize or otherwise increase the attenuation of sound waves encountered by the platform 306, so as to minimize or otherwise reduce sound waves via the flow path defined by the acoustic cavity 308, and, therefore, minimize or otherwise reduce the overall sound distribution of the turbofan engine 300.

[0045] exist Figure 4A In the example shown in -B, the acoustic device 302 includes a slot 406 through which mechanical fasteners 320 are inserted to attach the acoustic device 302 to the nacelle 318. In some examples, the hole 402 and / or the acoustic cavity 308 are positioned based on the location of the slot 406 and / or the size and / or shape of the mechanical fasteners 320 inserted therethrough. Furthermore, because the acoustic device 302 includes an airfoil 312 instead of a separate panel, such as the prior art acoustic panel 200, the acoustic device 302 can reduce the number of mechanical fasteners 320 used in the turbofan engine 300, thereby reducing the weight of the turbofan engine 300 compared to the prior art turbofan engine 100. Moreover, because the acoustic device 302 enables the turbofan engine 300 to use fewer mechanical fasteners 320, the acoustic device 302 can include fewer slots 406 compared to prior art turbofan engines. Therefore, compared to the perforations in the honeycomb structure 202 and perforated sheet 206 of the prior art acoustic panel 200, the acoustic cavity 308 and the hole 402 can span an increased area of ​​the turbofan engine 300. Thus, the acoustic device 302 maximizes or otherwise increases the surface area of ​​the turbofan engine 300 associated with sound attenuation, while also minimizing or otherwise reducing the weight of the turbofan engine 300.

[0046] Figure 5 A separate stereo view of another example acoustic device 500 according to the teachings of this disclosure is shown. Figure 5In the example shown, the acoustic device 500 includes a platform 502 (e.g., Figure 3 and 4A -B platform 306), acoustic cavity 504 (e.g., Figure 3 and 4A -B's acoustic cavity 308) and airfoil 506. Similar to Figure 3 and 4A The acoustic device 302 of the -B has a acoustic cavity 504 connected to and / or protruding from the first side 508 of the platform 502, and an airfoil 506 protruding from the second side of the platform 510. In the example shown, the first end 512 of the airfoil 506 protrudes from the platform 502.

[0047] In some examples, the acoustic device 500 includes a second platform (e.g., platform 502, platform 306) from which a second end 514 of the airfoil 506 protrudes. Thus, a second set of acoustic cavities (e.g., cavity 504, cavity 308) may be coupled to and / or extend from the second platform opposite to the second end 514 of the airfoil 506.

[0048] exist Figure 5 In this embodiment, platform 502 includes a perforation 516 (e.g., hole 402) aligned with acoustic cavity 504. In the illustrated example, perforation 516 is positioned within platform 502 around a first end 512 of airfoil 506. Figure 5 In this context, the shape, size, and / or angular orientation of the perforation 516 are constructible. In the illustrated example, the perforation 516 includes various shapes, sizes, and / or angular orientations. In some other examples, the perforation 516 in platform 502 includes substantially the same or similar construction, which may be constructed based on the implementation area of ​​acoustic device 500. Figure 5 In this context, the acoustic cavity 504 includes various sizes and / or shapes. In some other examples, the acoustic cavity 504 includes substantially the same size and / or shape, which may be constructed based on the implementation area of ​​the acoustic device 500. In the illustrated example, the perforation 516 receives the sound waves encountered by the platform 502. In turn, the air contained in the acoustic cavity 504 attenuates the sound waves to minimize or otherwise reduce the associated turbofan engine (e.g., turbofan engine 100 of Figures 1 and 2). Figure 3 The sound distribution of turbofan engines (such as the 300).

[0049] exist Figure 5 In the example shown, the acoustic device 500 includes sidewalls 518 extending from a first side 508 of the platform 502. Therefore, a acoustic cavity 504 is positioned between the respective sidewalls 518. In some examples, the sidewalls 518 are coupled to an associated turbofan engine via dovetail joints and / or via mechanical fasteners (e.g., mechanical fastener 320) to mount the acoustic device 500.

[0050] exist Figure 5 In the example shown, airfoil 506 is a full-span airfoil 506, and... Figure 3 and 4A -B's partial span airfoil 312 is the opposite. That is, the sidewall 518 is connected to the turbofan engine (e.g., the turbofan engine 100 in Figure 1) along the inner diameter of the flow path (e.g., the bypass airflow passage 140 in Figures 1 and 2). Figure 3 The acoustic device 500 is connected to the turbofan engine 300, and the second end 514 of the airfoil 506 is coupled to the turbofan engine along the outer diameter of the flow path opposite to the first side. In some examples, the second end 514 of the airfoil 506 extends to the outer diameter of the flow path without being coupled to it. In some examples, the sidewall 518 is coupled to the outer diameter of the flow path. Therefore, the platform 502 and the acoustic cavity 504 can be positioned along the inner and / or outer diameter of the flow path of the turbofan engine. Furthermore, in response to the decoupling of the sidewall 518 from the turbofan engine, the acoustic device 500 can be separated from the turbofan engine. Therefore, the acoustic device 500 can be removed to improve accessibility for servicing other components of the turbofan engine. Additionally or alternatively, the acoustic device 500 can be implemented and used in more than one turbofan engine.

[0051] exist Figure 5 In the example shown, airfoil 506 can be implemented as a static airfoil, a rotating airfoil, and / or a variable pitch airfoil at various locations throughout the turbofan engine. For example, airfoil 506 can be implemented as a fan blade (e.g., fan blade 132 of Figures 1 and 2). Figure 3 and 4A -B fan blades 326), stator blades (e.g., LP compressor stator blades 150, HP compressor stator blades 154, HP turbine stator blades 162 and / or LP turbine stator blades 166 of Figure 1), rotor blades (e.g., LP compressor rotor blades 152, HP compressor rotor blades 156, HP turbine rotor blades 164 and / or LP turbine rotor blades 168), inlet guide vanes (e.g., full-span inlet guide vanes) and / or outlet guide vanes. In some examples, sidewalls 518 may be connected to a nacelle (e.g., nacelle 134 of Figures 1 and 2). Figure 3 and 4A-B's nacelle 318), outer shell (e.g., outer shell 108 of FIG. 1), high-pressure shaft (e.g., HP shaft 124 of FIG. 1), low-pressure shaft (e.g., LP shaft 126 of FIG. 1), and / or fan shaft (e.g., fan shaft 128 of FIG. 1). In some examples, platform 306 defines the surfaces of the nacelle, outer shell, high-pressure shaft, low-pressure shaft, and / or fan shaft, enabling acoustic attenuation to be provided on these surfaces. Furthermore, when airfoil 506 is implemented as a variable-pitch airfoil, the sidewall 518 of platform 502 is coupled to the surface of a bushing, rotatable column, or shaft via a rotatable trunnion that rotates to adjust the pitch of airfoil 506. Thus, the associated bushing, column, or shaft is coupled to the nacelle, outer shell, high-pressure shaft, low-pressure shaft, and / or fan shaft. Therefore, platform 502 is coupled to rotatable surfaces to enable adjustment of the airfoil's pitch.

[0052] Although the examples disclosed herein describe acoustic devices 302, 500 as having individual airfoils 312, 506, acoustic devices 302, 500 may include multiple airfoils 312, 506 extending from platforms 306, 502 to provide sectors for associated turbofan engines (e.g., turbofan engine 300). That is, platforms 306, 502 may form a ring from which multiple airfoils 312, 506 project. Furthermore, acoustic cavities 308, 504 may form rings corresponding to and / or extending from platforms 306, 502, opposite to the multiple airfoils 312, 506. Conversely, sidewalls 322, 518 may form rings corresponding to the nacelle, outer shell, high-pressure shaft, low-pressure shaft, and / or fan shaft. Therefore, acoustic devices 302, 500 can form components or rings of fans, and / or inlet guide vanes, outlet guide vanes, stator vanes, and / or rotor blades. Furthermore, for example, acoustic devices (e.g., first acoustic devices) 302, 500 defining stator vanes or stator vane rings can extend to another (e.g., second acoustic device) defining rotor vanes or rotor vane rings. As a result, acoustic devices 302, 500 allow a significant portion of the surfaces of the nacelle, housing, high-pressure shaft, low-pressure shaft, and / or fan shaft to be correlated with sound attenuation. Therefore, acoustic devices 302, 500 can optimize or otherwise improve the sound distribution of the associated turbofan.

[0053] While each example acoustic device disclosed above has certain features, it should be understood that a particular feature of one example acoustic device is not necessarily specific to that example. Rather, any feature described above and / or depicted in the accompanying drawings may be combined with any example as a complement or alternative to any other feature of those examples. A feature of one example is not mutually exclusive with a feature of another example. Rather, the scope of this disclosure includes any combination of any features.

[0054] In some examples, acoustic devices 302, 500 include means for receiving sound waves defined in the surface of an aircraft engine, such as a turbofan engine 300. For example, the means for receiving sound waves can be implemented via a hole 402 and / or a perforation 516. In some examples, acoustic devices 302, 500 include means for attenuating sound waves extending from a first side of the means for receiving sound waves. In such examples, the means for attenuation is aligned with the means for receiving sound waves in a radial direction defined by the aircraft engine. For example, the means for attenuation can be implemented by acoustic cavities 308 and / or 504. In some examples, acoustic devices 302, 500 include means for generating aerodynamic forces protruding from a second side of the means for receiving sound waves opposite the first side. For example, the means for generating aerodynamic forces can be implemented by airfoil elements 312, 506.

[0055] "Comprising" and "including" (and all their forms and tenses) are used herein as open-ended terms. Therefore, whenever a claim uses any form of "comprising" or "including" (e.g., including, comprising, having, etc.) in a preamble or in any type of claim statement, it should be understood that additional elements, terms, etc., may be present without exceeding the scope of the corresponding claim or statement. As used herein, when the phrase "at least" is used as a transitional term, for example, in the preamble of a claim, it is open-ended in the same way as the terms "comprising" and "including". The term "and / or" when used, for example, in the form of A, B, and / or C, refers to any combination or subset of A, B, and C, such as (1) A alone, (2) B alone, (3) C alone, (4) A and B, (5) A and C, (6) B and C, and (7) A and B and C. As used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A and B" is intended to refer to an implementation comprising (1) at least one A, (2) at least one B, and (3) any one of at least one A and at least one B. Similarly, as used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A or B" is intended to refer to an implementation comprising (1) at least one A, (2) at least one B, and (3) any one of at least one A and at least one B. As used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A and B" is intended to refer to an implementation comprising (1) at least one A, (2) at least one B, and (3) any one of at least one A and at least one B. Similarly, as used herein in the context of describing the performance or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A or B" is intended to refer to an implementation comprising (1) at least one A, (2) at least one B, and (3) any one of at least one A and at least one B.

[0056] As used herein, singular references (e.g., “a,” “an,” “first,” “second,” etc.) do not exclude plurals. As used herein, the term “a” or “an” refers to one or more of that entity. The terms “a” (or “an”), “one or more,” and “at least one” are used interchangeably herein. Furthermore, although listed separately, multiple means, elements, or method actions can be implemented, for example, by a single unit or processor. Moreover, while individual features may be included in different examples or claims, these may be combined, and inclusion in different examples or claims does not imply that combination of features is impractical and / or advantageous.

[0057] From the above, it will be understood that an example acoustic turbofan airfoil device has been disclosed that provides acoustic attenuation within a turbofan engine without requiring a panel separate from the airfoil. Therefore, the example acoustic device disclosed herein eliminates the need for such a panel specifically integrated for acoustic attenuation. Consequently, the example acoustic device disclosed herein reduces the weight of the turbofan engine, which would otherwise derive from a panel dedicated to acoustic attenuation. Furthermore, the example acoustic device disclosed herein maximizes or otherwise increases the area of ​​one or more flow paths within the associated turbofan engine, which can improve the associated efficiency.

[0058] Although certain example methods, apparatuses, and articles of manufacture have been disclosed herein, the scope of this patent is not limited thereto. Rather, this patent covers all methods, apparatuses, and articles of manufacture that fall fully within the scope of the claims of this patent.

[0059] The following claims are incorporated herein by reference, each of which exists independently as a separate embodiment of this disclosure.

[0060] Further aspects of this disclosure are provided by the subject matter of the following clauses:

[0061] 1. An apparatus comprising: a platform for a turbofan engine, the platform including a perforation for receiving sound waves; a acoustic cavity projecting from a first side of the platform, the acoustic cavity being aligned with the perforation in a radial direction defined by the turbofan engine, the acoustic cavity being used to attenuate the sound waves; and an airfoil projecting from a second side of the platform opposite to the first side of the platform.

[0062] 2. The device according to any of the preceding clauses, wherein the airfoil is an inlet guide vane.

[0063] 3. The device according to any of the preceding clauses, wherein the platform defines the inner diameter of the flow path of the turbofan engine.

[0064] 4. The device according to any of the preceding clauses, wherein the platform defines the outer diameter of the flow path of the turbofan engine.

[0065] 5. The device according to any of the preceding clauses, wherein the platform defines the inner surface of the nacelle of the turbofan engine.

[0066] 6. The device according to any of the preceding clauses, wherein the platform defines the surface of the outer casing of the turbofan engine.

[0067] 7. The device according to any of the preceding clauses, wherein the platform defines the surface of the shaft of the turbofan engine.

[0068] 8. The device according to any of the preceding clauses, wherein the platform is coupled to a rotatable surface to enable adjustment of the pitch of the airfoil.

[0069] 9. The device according to any of the preceding clauses, wherein the distribution of the perforations is based on the position of a plurality of perforations relative to the airfoil.

[0070] 10. The device according to any of the preceding clauses, wherein the perforations are unevenly distributed along the platform.

[0071] 11. The device according to any of the preceding clauses, wherein the perforation includes at least a first perforation and a second perforation, the first perforation including a first size or shape, and the second perforation including a second size or shape different from the first size or shape.

[0072] 12. The device according to any of the preceding clauses, wherein the perforation includes at least a first perforation and a second perforation, the first perforation including a first angular orientation relative to the platform, and the second perforation including a second angular orientation relative to the platform.

[0073] 13. The device according to any of the preceding clauses, wherein the platform, the acoustic cavity, and the airfoil are manufactured by additive manufacturing.

[0074] 14. A turbofan engine, comprising: a facet including holes, the facet defining a surface of the turbofan engine; a acoustic cavity extending from a first side of the facet; and an airfoil integral with a second side of the facet, the second side being opposite to the first side.

[0075] 15. The turbofan engine according to any of the preceding clauses, wherein the facet and the airfoil are formed by additive manufacturing.

[0076] 16. The turbofan engine according to any of the preceding clauses, wherein the acoustic cavity is attached to the first side of the faceplate by an adhesive.

[0077] 17. The turbofan engine according to any of the preceding clauses, wherein the hole is formed in the facet via laser drilling.

[0078] 18. An apparatus comprising: means for receiving sound waves on the surface of an aircraft engine; means for attenuating the sound waves extending from a first side of the means for receiving, the means for attenuation being aligned with the means for receiving in a radial direction defined by the aircraft engine; and means for generating aerodynamics protruding from a second side of the means for receiving opposite to the first side.

[0079] 19. The device according to any of the preceding clauses, wherein the means for receiving comprises a first means for receiving and a second means for receiving, the first means for receiving comprising at least one of a first size or a first shape, and the second means for receiving comprising at least one of a second size or a second shape, the second size being different from the first size and the second shape being different from the first shape.

[0080] 20. The device according to any of the preceding clauses, wherein the means for attenuation includes a first means for attenuation and a second means for attenuation, the first means for attenuation including at least one of a first size or a first shape, and the second means for attenuation including at least one of a second size or a second shape, the second size being different from the first size and the second shape being different from the first shape.

Claims

1. A device, characterized in that, include: A first platform for a turbofan engine, the first platform including a first perforation and a second perforation, the first perforation for receiving sound waves, and the second perforation for receiving mechanical fasteners that connect the first platform to the nacelle of the turbofan engine. A first acoustic cavity, which is integral with and protrudes from a first side of the first platform, is aligned with the first perforation in a radial direction defined by the turbofan engine, and is used to attenuate the sound waves. The second platform includes a third perforation for receiving a second acoustic wave. The second acoustic cavity is integral with and protrudes from the first side of the second platform. The second acoustic cavity is aligned with the third perforation in the radial direction. The second acoustic cavity is used to attenuate the second sound wave. and An airfoil, wherein a first end of the airfoil is integral with and protrudes from a second side of a first platform, the second side of the first platform being opposite to the first side of the first platform, and wherein a second end of the airfoil is integral with and protrudes from a second side of a second platform, the second side of the second platform being opposite to the first side of the second platform, wherein the second end of the airfoil is opposite to the first end of the airfoil.

2. The device according to claim 1, characterized in that, The airfoil is an inlet guide vane.

3. The device according to claim 1, characterized in that, The first platform defines the outer diameter of the flow path of the turbofan engine.

4. The device according to claim 1, characterized in that, The first platform defines the inner surface of the nacelle of the turbofan engine.

5. The device according to claim 1, characterized in that, The first platform defines the surface of the outer casing of the turbofan engine.

6. The device according to claim 1, characterized in that, The second platform defines a surface of the rotatable shaft of the turbofan engine, the surface being capable of adjusting the pitch of the airfoil, and wherein the surface defines the inner diameter of the flow path of the turbofan engine.

7. The device according to claim 1, characterized in that, in, The first perforation is located in a first region of the first platform with a first distribution and in a second region of the first platform that is different from the first region with a second distribution, and the first perforation in the first distribution is more densely packed than the first perforation in the second distribution.

8. The device according to claim 1, characterized in that, The first perforation includes at least a first portion and a second portion, the first portion including a first angular orientation relative to the first platform, and the second portion including a second angular orientation relative to the first platform.

9. The device according to claim 1, characterized in that, The first platform, the first acoustic cavity, and the airfoil are manufactured via additive manufacturing.

10. The device according to claim 1, characterized in that, The first acoustic cavity is aligned with the mechanical fastener in the circumferential direction defined by the turbofan engine.

11. The device according to claim 1, characterized in that, The distribution of the first perforations on the first platform is non-uniform, and the distribution of the first perforations is based on the position of the first perforations relative to the airfoil to receive the sound waves generated by or affected by the airfoil.

12. A turbofan engine having the device according to claim 1, characterized in that, The first platform defines the surface of the turbofan engine, and the first perforation includes a first portion and a second portion.

13. The turbofan engine according to claim 12, characterized in that, The first platform and the airfoil are formed by additive manufacturing.

14. The turbofan engine according to claim 12, characterized in that, The first perforation is formed in the first platform via laser drilling in multiple orientations.

15. The turbofan engine according to claim 12, characterized in that, It further includes a sidewall projecting from the first side of the first platform and surrounding the first acoustic cavity, wherein the sidewall is connected to the nacelle of the turbofan engine via a dovetail joint.

16. The turbofan engine according to claim 12, characterized in that, The first acoustic cavity is aligned with the first perforation.

17. A device, characterized in that, include: A device for receiving sound waves on a first surface of an aircraft engine, the device for receiving sound waves including a first device for receiving sound waves, a second device for receiving sound waves and a third device, the first device for receiving sound waves including a circular cross-sectional area, the second device for receiving sound waves including a rectangular cross-sectional area, and the third device for receiving a fastening device for connecting the device for receiving sound waves to the nacelle of the aircraft engine. The first device for attenuating the sound wave is integral with and extends from the first side of the device for receiving the sound wave in the first surface of the aircraft engine. The first device for attenuating the sound wave is aligned with the first device and the second device for receiving the sound wave in the radial direction defined by the aircraft engine. Device for receiving sound waves in the second surface of the aircraft engine; The second device for attenuating the sound wave is integral with and extends from the first side of the device for receiving the sound wave in the second surface of the aircraft engine. The second device for attenuating the sound wave is aligned with the perforation of the device for receiving the sound wave in the second surface of the aircraft engine in the radial direction. and A device for generating aerodynamics, wherein the device for generating aerodynamics includes a first end integral with and protruding from a second side of a device for receiving sound waves on a first surface of an aircraft engine, the second side being opposite to the first side; the rectangular cross-sectional region includes a longitudinal portion in the same direction as the side span of the device for generating aerodynamics; wherein the device for generating aerodynamics includes a second end integral with and protruding from a second side of a device for receiving sound waves on a second surface of an aircraft engine, the second side of the device for receiving sound waves on a second surface of an aircraft engine being opposite to the first side of the device for receiving sound waves on a second surface of an aircraft engine.

18. The device according to claim 17, characterized in that, The first device for attenuating sound waves includes at least one of a first size or a first shape and at least one of a second size or a second shape, the second size being different from the first size and the second shape being different from the first shape. The first device for attenuating sound waves having the first size or the first shape is positioned closer to the device for generating the aerodynamics than the first device for attenuating sound waves having the second size or the second shape. The first size or the first shape is configured to increase structural support relative to the second size or the second shape, and the second size or the second shape is configured to increase acoustic attenuation relative to the first size or the first shape.

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