Backplate for use in a turbine engine containment assembly and method of forming the same

Abstract

A backplate for use in a turbine engine fan case and a method of forming the same is disclosed. The backplate includes a first portion including a first portion first end and an opposite first portion second end. The first portion is tapered between the first portion first end and the first portion second end. The backplate further includes a second portion connected to the first portion. The second portion includes a second portion first end and an opposite second portion second end. The second portion defines a constant thickness between the second portion first end and the second portion second end.

Description

Technical Field

[0001] This disclosure generally relates to turbine engines, and more specifically to backplates for use in turbine engine assemblies and methods of forming thereof. Background Technology

[0002] At least some known gas turbine engines, such as aircraft engines, include a stator assembly extending circumferentially around a rotor assembly of the turbine engine. Known rotor assemblies include at least one row of rotor blades extending radially outward from the blade root, for example, causing the rotor blades to rotate close to the stator assembly of the turbine engine. At least some known stator assemblies include a soft-walled containment assembly that helps provide rotor containment during unlikely events such as unexpected blade shedding conditions. The soft-walled containment assembly typically includes an engine housing, a collapsible containment member connected to the engine housing, and a carbon fiber backplate extending across the collapsible containment member and a portion of the engine housing.

[0003] At least some known backplate structures typically have a constant thickness. This thickness is the minimum thickness necessary to meet the strength requirements at every point along the entire length of the backplate. However, some points along the length of the backplate have lower strength requirements than others, and therefore do not require the same backplate thickness as points with higher strength requirements. Consequently, at least some known backplates are over-designed, which increases the weight of the backplate and manufacturing costs. Summary of the Invention

[0004] In one aspect, a backplate for use in a turbine engine fan housing is provided. The backplate includes a first portion having a first end and an opposing second end. The first portion is tapered between the first end and the second end. The backplate also includes a second portion connected to the first portion. The second portion includes a second first end and an opposing second end. The second portion defines a constant thickness between the first end and the second end.

[0005] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the backplate includes a third portion connected to the second portion and including a first end of the third portion and an opposing second end of the third portion. The third portion is tapered between the first end and the second end of the third portion.

[0006] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the second part is connected between the first part and the third part.

[0007] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the second end of the first portion, the first end of the third portion, and the second portion define substantially similar thicknesses.

[0008] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the first end of the first portion and the second end of the third portion define substantially similar thicknesses.

[0009] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following instances and aspects, a first portion has a first end defining a first thickness and a second end defining a second thickness greater than the first thickness, and the second end of the first portion is connected to the second portion.

[0010] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the first and second portions are made of a plurality of laminates of composite materials.

[0011] In another aspect, a housing assembly for use in a turbine engine is provided. The housing assembly includes an engine housing comprising a shell layer and a wing member extending obliquely from the shell layer. The assembly further includes a honeycomb structure connected to the shell layer and a backplate connected to the honeycomb structure and the wing member. The backplate includes a first portion comprising a first end of the first portion and an opposing second end of the first portion, wherein the first portion is tapered between the first end and the second end of the first portion. The backplate also includes a second portion connected to the first portion. The second portion includes a first end of the second portion and an opposing second end of the second portion, wherein the second portion defines a constant thickness between the first end and the second end of the second portion.

[0012] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, a first portion extends across the wing member, and a second portion extends across the wing member and the honeycomb structure.

[0013] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, a gap is defined between the distal end of the wing member and the honeycomb structure, and a second portion spans said gap.

[0014] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the second portion includes an angled engagement member approaching the gap.

[0015] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the housing component includes a third portion connected to the second portion and extending across the honeycomb structure.

[0016] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the third portion includes a first end of the third portion and an opposing second end of the third portion. The third portion is tapered between the first end and the second end of the third portion.

[0017] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the receiving component includes a receiving material layer extending over a backplate.

[0018] In another aspect, a method is provided for forming a backplate for use in a turbine engine housing assembly. The method includes forming a first portion of the backplate, the first portion including a first end and an opposing second end, such that the first portion is tapered between the first end and the second end. The method further includes integrally forming a second portion with the first portion. Integrating the second portion includes forming a first end and an opposing second end, such that the second portion includes a constant thickness between the first end and the second end.

[0019] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the method includes integrally forming a third portion with the second portion. Integrating the third portion includes forming a first end of the third portion and an opposing second end of the third portion, such that the third portion is tapered between the first end and the second end of the third portion.

[0020] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, integrally forming the third portion includes integrally forming a first end of the third portion, a second end of the first portion, and a second portion to define substantially similar thicknesses.

[0021] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, a first portion is formed and a second portion is integrally formed. A third portion is formed by multiple layers of composite material. The first portion is formed and the second portion is integrally formed.

[0022] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, a first portion is formed at a first end with a thickness defined in the range of about 0.10 inches and about 0.25 inches.

[0023] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the first end of the first portion is formed with a thickness defined in the range of about 0.04 inches and about 0.15 inches.

[0024] In another aspect, a backplate is provided for use in a turbine engine fan housing. The backplate includes a first end, an opposing second end, and a body portion extending between the first and second ends. The body portion includes a non-uniform thickness configuration.

[0025] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the body portion defines a ring-shaped structure.

[0026] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, the body portion includes a first end portion proximate to a first end, a second end portion proximate to a second end, and a central portion positioned between the first end portion and the second end portion. At least one of the first end portion and the second end portion includes a non-uniform thickness configuration.

[0027] In one aspect of this disclosure, which may include at least a portion of any of the preceding and / or following examples and aspects, each of the first end and the second end includes a non-uniform thickness configuration, and the central portion includes a uniform thickness configuration.

[0028] Specifically, technical solution 1 of this application relates to a backplate for use in a turbine engine fan housing, the backplate comprising: a first portion including a first end of the first portion and an opposing second end of the first portion, wherein the first portion is tapered between the first end of the first portion and the second end of the first portion; and a second portion connected to the first portion and including a first end of the second portion and an opposing second end of the second portion, wherein the second portion defines a constant thickness between the first end of the second portion and the second end of the second portion.

[0029] Technical solution 2 of this application relates to the backplate according to technical solution 1, which further includes a third part, the third part being connected to the second part and including a first end of the third part and an opposite second end of the third part, the third part being tapered between the first end of the third part and the second end of the third part.

[0030] Technical solution 3 of this application relates to the backplate according to technical solution 2, wherein: the second part is connected between the first part and the third part.

[0031] Technical solution 4 of this application relates to a backplate according to technical solution 2, wherein: the second end of the first portion, the first end of the third portion, and the second portion are defined to have substantially similar thicknesses.

[0032] Technical solution 5 of this application relates to the backplate according to technical solution 2, wherein: the first end of the first portion and the second end of the third portion define substantially similar thicknesses.

[0033] Technical solution 6 of this application relates to a backplate according to technical solution 1, wherein: a first end of the first portion defines a first thickness and a second end of the first portion defines a second thickness greater than the first thickness, and the second end of the first portion is connected to the second portion.

[0034] Technical solution 7 of this application relates to a backplate according to technical solution 1, wherein: the first part and the second part are made of multiple layers of composite material.

[0035] Technical solution 8 of this application relates to a housing assembly for use in a turbine engine, the housing assembly comprising: an engine housing including: a shell layer; and a wing member extending obliquely from the shell layer; a honeycomb structure connected to the shell layer; and a backplate connected to the honeycomb structure and the wing member, wherein the backplate comprises:

[0036] A first portion includes a first end of the first portion and an opposing second end of the first portion, wherein the first portion is tapered between the first end of the first portion and the second end of the first portion; and a second portion is connected to the first portion and includes a first end of the second portion and an opposing second end of the second portion, wherein the second portion defines a constant thickness between the first end of the second portion and the second end of the second portion.

[0037] Technical solution 9 of this application relates to the housing component according to technical solution 8, wherein: the first portion extends across the wing member, and the second portion extends across the wing member and the honeycomb structure.

[0038] Technical solution 10 of this application relates to a receiving component according to technical solution 8, wherein: a gap is defined between the distal end of the wing member and the honeycomb structure, and the second portion spans the gap.

[0039] Technical solution 11 of this application relates to the receiving assembly according to technical solution 10, wherein: the second part includes an angled engagement member adjacent to the gap.

[0040] Technical solution 12 of this application relates to the housing component according to technical solution 8, which further includes a third portion connected to the second portion and extending across the honeycomb structure.

[0041] Technical solution 13 of this application relates to a receiving component according to technical solution 12, wherein: the third part includes a third part first end and an opposing third part second end, and the third part is tapered between the third part first end and the third part second end.

[0042] Technical solution 14 of this application relates to the containment assembly according to technical solution 8, which further includes a containment material layer extending above the back plate.

[0043] Technical solution 15 of this application relates to a method of forming a backplate for use in a turbine engine housing assembly, the method comprising: forming a first portion of the backplate, the first portion including a first end of the first portion and an opposing second end of the first portion, such that the first portion is tapered between the first end of the first portion and the second end of the first portion; and integrally forming a second portion with the first portion, wherein integrally forming the second portion includes forming a first end of the second portion and an opposing second end of the second portion, such that the second portion defines a constant thickness between the first end of the second portion and the second end of the second portion.

[0044] Technical solution 16 of this application relates to the method according to technical solution 15, wherein: it further includes integrally forming a third portion with the second portion, wherein integrally forming the third portion includes forming a first end of the third portion and an opposing second end of the third portion, such that the third portion is tapered between the first end of the third portion and the second end of the third portion.

[0045] Technical solution 17 of this application relates to the method according to technical solution 16, wherein: integrally forming the third portion includes integrally forming a first end of the third portion, a second end of the first portion, and a second portion to define substantially similar thicknesses.

[0046] Technical solution 18 of this application relates to the method according to technical solution 15, wherein: forming the first part and integrally forming the second part includes forming the first part and integrally forming the second part by a plurality of layers of composite material.

[0047] Technical solution 19 of this application relates to the method according to technical solution 15, wherein: forming the first portion includes forming a second end of the first portion with a thickness defined in the range of about 0.10 inches and about 0.25 inches.

[0048] Technical solution 20 of this application relates to the method according to technical solution 15, wherein: forming the first portion includes forming a first end of the first portion with a thickness defined in the range of about 0.04 inches and about 0.15 inches.

[0049] Technical solution 21 of this application relates to a backplate for use in a turbine engine fan housing, the backplate comprising: a first end; an opposing second end; and a body portion extending between the first end and the second end, wherein the body portion comprises a non-uniform thickness configuration.

[0050] Technical solution 22 of this application relates to the back plate according to technical solution 21, wherein: the main body portion defines an annular structure.

[0051] Technical solution 23 of this application relates to a backplate according to technical solution 21, wherein: the main body portion includes: a first end portion adjacent to the first end portion; a second end portion adjacent to the second end portion; and a central portion located between the first end portion and the second end portion, wherein at least one of the first end portion and the second end portion includes a non-uniform thickness configuration.

[0052] Technical solution 24 of this application relates to a backplate according to technical solution 23, wherein: each of the first end and the second end includes a non-uniform thickness configuration, and the central portion includes a uniform thickness configuration. Attached Figure Description

[0053] These and other features, aspects, and advantages of this disclosure will become better understood when the following detailed description is read in conjunction with the accompanying drawings, in which the same reference numerals denote the same parts.

[0054] Figure 1 It is a schematic illustration of a demonstrative turbine engine;

[0055] Figure 2 It is possible Figure 1 A cross-sectional illustration of an exemplary housing component used in a turbine engine, shown in the illustration;

[0056] Figure 3 It is a section taken along region 3 according to the first embodiment of this disclosure. Figure 2 A cross-sectional illustration of a portion of the housing component shown in the image;

[0057] Unless otherwise specified, the accompanying drawings provided herein are intended to illustrate features of embodiments of this disclosure. These features are considered applicable to a wide variety of systems that include one or more embodiments of this disclosure. Accordingly, the drawings are not intended to include all conventional features known to those skilled in the art for practicing the embodiments disclosed herein. Detailed Implementation

[0058] In the following specification and claims, several terms will be referenced, and these terms shall be defined to have the following meanings.

[0059] Unless the context explicitly indicates otherwise, the singular forms “a” and “the” include the plural referent.

[0060] "Optional" or "as needed" means that the events or circumstances described below may or may not occur, and the description includes both cases where the events occur and cases where they do not occur.

[0061] As used herein and throughout the specification and claims, approximate language may be applied to modify any quantitative expression that may be varied in manner without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” and “substantially” are not limited to the specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure said value. Scope limitations may be combined and / or interchanged herein and throughout the specification and claims. Unless otherwise indicated by context or wording, such scopes may be specified and include all subscopes included herein.

[0062] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends generally parallel to the centerline of the turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends generally perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the turbine engine.

[0063] Embodiments of this disclosure relate to rotor section housing assemblies having an improved load path transition between components of the assembly. More specifically, the housing assembly described herein includes an engine housing, such as a fan housing, comprising a shell and a wing member extending from the shell. The housing assembly also includes a honeycomb structure connected to the shell and a backplate connected to the honeycomb structure and the wing member. The backplate member described herein includes one or more design features that help limit damage to the backplate caused by the wing member in events that force the wing member radially outward toward the backplate, such as during unexpected blade shedding conditions. More specifically, the backplate includes tapered first and third portions, and a second portion extending therebetween with a constant thickness. During blade shedding conditions, a high-concentration load path to the backplate is located at the wing member. Thus, the second portion of the backplate has a maximum thickness to provide the backplate with the strength and stiffness necessary to withstand blade shedding conditions. Accordingly, the thickness of the backplate is adjusted along its length based on the expected load concentration, and portions of the backplate are tapered to transition from a smaller thickness to a larger thickness; that is, from a thinner section to a thicker section. This configuration contributes to a reduction in the overall weight and manufacturing cost of the backplate.

[0064] Although the following embodiments are described in the context of turbofan engines, it should be understood that the systems and methods described herein are also applicable to, for example, turboprop engines, turboshaft engines, turbojet engines, and ground turbine engines.

[0065] Figure 1 This is a schematic diagram of an exemplary turbine engine 10, which includes a fan assembly 12, a low-pressure or booster compressor assembly 14, a high-pressure compressor assembly 16, and a combustor assembly 18. The fan assembly 12, booster compressor assembly 14, high-pressure compressor assembly 16, and combustor assembly 18 are fluidly connected. The turbine engine 10 also includes a high-pressure turbine assembly 20 fluidly connected to the combustor assembly 18 and the low-pressure turbine assembly 22. The fan assembly 12 includes an array of fan blades 24 extending radially outward from a rotor disk 26. The low-pressure turbine assembly 22 is connected to the fan assembly 12 and the booster compressor assembly 14 via a first drive shaft 28, and the high-pressure turbine assembly 20 is connected to the high-pressure compressor assembly 16 via a second drive shaft 30. The turbine engine 10 has an inlet 32 ​​and an exhaust port 34. The turbine engine 10 further includes the fan assembly 12, the booster compressor assembly 14, the high-pressure compressor assembly 16, and a centerline 36 around which the turbine assemblies 20 and 22 rotate.

[0066] During operation, air entering the turbine engine 10 via intake 32 is conveyed through a channel to the supercharger assembly 14 and then through the fan assembly 12. Compressed air is discharged from the supercharger assembly 14 toward the high-pressure compressor assembly 16. Highly compressed air is conveyed from the high-pressure compressor assembly 16 toward the combustor assembly 18, mixed with fuel, and the mixture is burned within the combustor assembly 18. The high-temperature combustion gases produced by the combustor assembly 18 are conveyed through channels to the turbine assemblies 20 and 22. The combustion gases are then discharged from the turbine engine 10 via exhaust 34.

[0067] Figure 2 It can be used in turbocharged engines 10 ( Figure 1 A cross-sectional illustration of the exemplary housing assembly 100 used in the example shown in the diagram. In an exemplary embodiment, the housing assembly 100 includes an engine housing 102 (also referred to below as a "fan housing") and a honeycomb structure 108 connected to a shell 104, the engine housing 102 including the shell 104 and a wing member 106. More specifically, the wing member 106 is oriented obliquely relative to the shell 104, such that a cavity 110 is at least partially defined between the shell 104 and the wing member 106. The honeycomb structure 108 is positioned within the cavity 110 to provide noise attenuation when the turbine engine 10 is in operation.

[0068] The housing assembly 100 also includes an annular backplate 112 extending above the wing member 106 and the honeycomb structure 108. More specifically, the backplate 112 includes a first end 113, a second end 115, and a body portion 117 extending between the ends 113 and 115. In an exemplary embodiment, the body portion 117 has a non-uniform thickness configuration. More specifically, the body portion 117 has a first end portion 119 adjacent to the first end 113, an opposing second end portion 121 adjacent to the second end 115, and a central portion 123 extending between the ends 119 and 121. Figure 2 As shown, at least one of the ends 119 and 121 includes a non-uniform thickness configuration. More specifically, the first end 119 and the second end 121 each have a non-uniform thickness configuration, and the central portion 123 has a uniform thickness configuration.

[0069] Each end 119 and 121 includes a first portion 114 extending across wing member 106, a second portion 116 extending partially across wing member 106 and partially across honeycomb structure 108, and a third portion 118 extending across honeycomb structure 108. The second portion 116 is defined between the first portion 114 and the third portion 118. Additionally, the backplate 112 utilizes an adhesive material layer 120 ( Figure 3 (As shown in the image) It is connected to wing component 106.

[0070] The wing member 106 and the backplate 112 are each free to allow the housing assembly 100 to be made of any material that functions as described herein. For example, the wing member 106 is made of a metallic material such as aluminum, and the backplate 112 is made of a composite material such as carbon fiber reinforced polymer (CFRP). Thus, and as will be explained in more detail below, adjusting the thickness of the wing member 106 helps to reduce the ratio of metallic to composite material at the interface defined between the wing member 106 and the backplate 112, and thus helps to provide a smooth load path transition therebetween.

[0071] Furthermore, the backplate 112 provides a surface on which one or more subsequent material layers can be circumferentially positioned around the engine housing 102. For example, in an exemplary embodiment, the receiving assembly 100 also includes a receiving material layer 122 extending above the backplate 112. The receiving material can be any material that enables the receiving assembly 100 to function as described herein, such as (but not limited to) aramid materials (i.e., ).

[0072] In an exemplary embodiment, for example, fan blade 24 ( Figure 1 The array of rotor blades 124 (as shown in the image) extends radially inward from the engine housing 102. The array of rotor blades 124 and the housing material layer 122 are positioned relative to the centerline 36 of the turbine engine 10. Figure 1 (As shown in the image) Axial alignment. More specifically, the containment material layer 122 extends across the leading edge 126 and trailing edge 128 of the rotor blade 124. Thus, in the event of an unexpected blade detachment condition, the containment material layer 122 is positioned to prevent radial outward movement of the rotor blade 124.

[0073] Figure 3 The receiving component 100 is a section taken along region 3 according to an exemplary embodiment of this disclosure. Figure 2 A cross-sectional illustration of a portion of the image (shown in the image). Figure 3 As shown, the backplate 112 includes a first portion 114, a second portion 116, and a third portion 118, which are connected to each other in series such that the second portion is between the first portion 114 and the third portion 118. The first portion 114 includes an inner surface 130 and an outer surface 132 defining the thickness of the first portion 114 therebetween. Furthermore, the first portion 114 includes a first end 134 positioned near the shell 104 and an opposing second end 136 positioned near the second portion 116. The first end 134 and the second end 136 define a first length L1 therebetween. In one embodiment, the first length L1 is in the range of about 1.0 inch to about 2.0 inches. More specifically, the first length L1 is approximately 1.44 inches. Typically, the first length L1 is any length that facilitates the operation of the backplate 112 as described herein.

[0074] like Figure 3 As shown, a first end 134 has a first thickness T1 defined between surfaces 130 and 132, and a second end 136 has a second thickness T2 defined between surfaces 130 and 132. In an exemplary embodiment, the first thickness T1 is less than the second thickness T2, such that the first portion 114 is tapered between the first and second ends 134 and 136 and thus has a non-uniform thickness configuration. More specifically, the first end 134 has a first thickness T1 defined in the range of about 0.04 inches to about 0.15 inches. Furthermore, the second end 136 has a second thickness T2 defined in the range of about 0.10 inches to about 0.25 inches. More specifically, the first thickness T1 is approximately 0.08 inches, and the second thickness T2 is approximately 0.152 inches. Typically, the first thickness T1 and the second thickness T2 are any length that facilitates the operation of the backplate 112 as described herein.

[0075] In an exemplary embodiment, the third portion 118 includes an inner surface 138 and an outer surface 140 defining the thickness of the third portion 118 therebetween. Furthermore, the third portion 118 includes a first end 142 positioned adjacent to the second portion 116 and an opposing second end 144. The first end 134 and the second end 136 define a second length L2 therebetween. In one embodiment, the second length L2 is in the range of about 1.0 inch to 2.0 inches. More specifically, the second length L2 is approximately 1.44 inches. Typically, the second length L2 is any length that facilitates the operation of the backplate 112 as described herein.

[0076] like Figure 3 As shown, the first end 142 has a first thickness T1 defined between surfaces 138 and 140, and the second end 144 has a second thickness T2 defined between surfaces 138 and 140. In an exemplary embodiment, the first thickness T1 is thicker than the second thickness T2, such that the third portion 118 is tapered between the first end 142 and the second end 144, i.e., has a non-uniform thickness configuration. More specifically, the first end 142 has a first thickness T1 defined in the range of about 0.10 inches to about 0.25 inches. Furthermore, the second end 144 has a second thickness T2 defined in the range of about 0.04 inches to about 0.15 inches. More specifically, the first thickness T1 is approximately 0.152 inches, and the second thickness T2 is approximately 0.08 inches. Typically, the first thickness T1 and the second thickness T2 are any lengths that facilitate the operation of the backplate 112 as described herein. In an exemplary embodiment, the first end 134 of the first portion 114 and the second end 144 of the third portion 118 have substantially similar thicknesses. More specifically, the first thickness T1 of the first part 114 is generally similar to the second thickness T2 of the third part 118.

[0077] The second portion 116 connects between the first portion 114 and the third portion 118, and includes an inner surface 146 and an outer surface 148 defining the thickness of the second portion 116 therebetween. Furthermore, the second portion 116 includes a first end 150 integrally formed with a second end 136 of the first portion, and an opposing second end 152 integrally formed with a first end 142 of the second portion 116. In an exemplary embodiment, the second portion 116 has a constant thickness T3 defined between surfaces 138 and 140 and extending between the first end 150 and the second end 152. More specifically, the second portion 116 has a third thickness T3 defined in the range of about 0.10 inches to about 0.25 inches. In an exemplary embodiment, the second end 136 of the first portion 114, the first end 142 of the third portion 118, and the entire length of the second portion 116 have substantially similar thicknesses. More specifically, the third thickness T3 of the second portion 116 is substantially similar to the second thickness T2 of the first portion 114 and the first thickness T1 of the third portion 118.

[0078] In another embodiment, the second portion 116 has a non-uniform thickness configuration, wherein the second portion 116 has a minimum thickness to meet a predetermined strength requirement. More specifically, when the second portion 116 has a non-uniform thickness configuration, the minimum thickness of the second portion is substantially similar to the maximum second thickness T2 of the first portion 114 and the first thickness T1 of the third portion 118.

[0079] As described above, the backsheet 112 is made of a composite material, such as carbon fiber reinforced polymer (CFRP). More specifically, each of the first portion 114, the second portion 116, and the third portion 118 of the backsheet 112 is formed of multiple layers of composite material. In an exemplary embodiment, the thicker regions of the backsheet 112 include more layers of composite material than the regions with smaller thicknesses. For example, the second end 136 of the second portion 116, the second end 136 of the first portion 114, and the first end 142 of the third portion 118 include more layers of composite material than the first end 134 of the first portion 114 and the second end 144 of the third portion 118 to create a thickness difference.

[0080] In an exemplary embodiment, wing member 106 includes a distal end 154 spaced from honeycomb structure 108 to form a gap 156 between honeycomb structure 108 and distal end 154. Figure 3 As shown, the second portion 116 spans the gap 156 such that a portion of the second portion 116 is positioned radially outward from the gap 156. More specifically, the second portion 116 includes an angled engagement 158 ​​adjacent to and positioned radially outward from the gap 156. During blade detachment conditions, the high-concentration load path to the backplate 112 is located at the distal end 154 of the wing member 106. Thus, the second portion 116 of the backplate 112 has the maximum thickness of the backplate 112 to provide the strength and stiffness necessary for the backplate 112 to withstand blade detachment conditions. Furthermore, the first and second portions 114 and 118 of the backplate 112 are not subjected to the same high load as the second portion 116. Thus, the first and second portions 114 and 118 can be thinner than the second portion 116. Accordingly, the thickness of the backplate 112 is adapted along its length based on the expected load concentration, and portions of the backplate 112 are tapered to transition from a smaller thickness to a larger thickness. This configuration reduces the overall weight and manufacturing cost of the backplate 112.

[0081] The exemplary technical effects of the components and methods described herein include at least one of the following: (a) providing housing for the rotor assembly; (b) providing a smooth load path transition between the metal and composite components within the housing assembly; and (c) reducing the likelihood of damage to the backplate within the housing assembly in an event where the wing component is forced radially outward toward the backplate.

[0082] The foregoing describes in detail exemplary embodiments of housing components used in turbine engines and related parts. The components are not limited to the specific embodiments described herein; in fact, components of the system and / or steps of the method may be used independently and separately from other components and / or steps described herein. For example, the configuration of the components described herein may also be used in conjunction with other processes and is not limited to practice with the fan section of a turbine engine. In fact, exemplary embodiments can be implemented and utilized in conjunction with many applications requiring smooth load transitions between components.

[0083] While certain features of various embodiments of this disclosure may be shown in some drawings but not in others, this is merely for convenience. Any feature of the drawings may be referenced and / or claimed in combination with any feature of any other drawing, based on the principles of embodiments of this disclosure.

[0084] This written description discloses embodiments of the present disclosure, including the best mode, by way of example, and also enables those skilled in the art to practice the embodiments of the present disclosure, including making and using any apparatus or system and performing any incorporated methods. The patentable scope of the embodiments described herein is defined by the claims and may include other instances conceived by those skilled in the art. Such other instances are deemed to be within the scope of the claims if they have structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A backplate positioned radially outward from a turbine engine fan housing, the backplate comprising: The first part includes a first end of the first part and an opposing second end of the first part, wherein the first part is tapered between the first end of the first part and the second end of the first part; as well as The second portion is connected to the first portion and includes a first end of the second portion and a second end of the opposing second portion, wherein the second portion defines a constant thickness between the first end of the second portion and the second end of the second portion.

2. The backplate according to claim 1, further comprising a third portion connected to the second portion and including a first end of the third portion and an opposing second end of the third portion, the third portion being tapered between the first end of the third portion and the second end of the third portion.

3. The backplate according to claim 2, wherein: The second part is connected between the first part and the third part.

4. The backplate according to claim 2, wherein: The second end of the first portion, the first end of the third portion, and the second portion define similar thicknesses.

5. The backplate according to claim 2, wherein: The first end of the first portion and the second end of the third portion define similar thicknesses.

6. The backplate according to claim 1, wherein: The first portion has a first end defining a first thickness and a second end defining a second thickness greater than the first thickness, and the second end of the first portion is connected to the second portion.

7. The backplate according to claim 1, wherein: The first part and the second part are made of multiple layers of composite material.

8. A housing assembly for use in a turbine engine, the housing assembly comprising: Engine housing, comprising: Shell; and A wing component that extends obliquely from the shell; A honeycomb structure, which is connected to the shell; and Backplate, which is connected to the honeycomb structure and the wing member, wherein the backplate comprises: A first portion, comprising a first end of the first portion and an opposing second end of the first portion, wherein the first portion is tapered between the first end of the first portion and the second end of the first portion; and The second portion is connected to the first portion and includes a first end of the second portion and a second end of the opposing second portion, wherein the second portion defines a constant thickness between the first end of the second portion and the second end of the second portion.

9. The housing component according to claim 8, wherein: The first portion extends across the wing member, and the second portion extends across the wing member and the honeycomb structure.

10. The receiving component according to claim 8, wherein: The gap is defined between the distal end of the wing member and the honeycomb structure, and the second portion spans the gap.

11. The receiving component according to claim 10, wherein: The second part includes an angled engagement member adjacent to the gap.

12. The housing component of claim 8, further comprising a third portion connected to the second portion and extending across the honeycomb structure.

13. The receiving component according to claim 12, wherein: The third part includes a first end and a second end of the opposite third part, and the third part is tapered between the first end and the second end of the third part.

14. The housing assembly of claim 8, further comprising a housing material layer extending over the back plate.

15. A method of forming a backplate positioned radially outward from a turbine engine fan housing, the method comprising: A first portion forming the back plate, the first portion including a first end of the first portion and an opposing second end of the first portion, such that the first portion is tapered between the first end of the first portion and the second end of the first portion; as well as The second portion is integrally formed with the first portion, wherein integrally forming the second portion includes forming a first end of the second portion and an opposing second end of the second portion, such that the second portion defines a constant thickness between the first end of the second portion and the second end of the second portion.

16. The method of claim 15, wherein: The third portion is further integrally formed with the second portion, wherein integrally forming the third portion includes forming a first end of the third portion and an opposing second end of the third portion, such that the third portion is tapered between the first end and the second end of the third portion.

17. The method of claim 16, wherein: Integrating the third portion includes integrally forming the first end of the third portion, the second end of the first portion, and the second portion to define similar thicknesses.

18. The method of claim 15, wherein: Forming the first part and integrally forming the second part includes forming the first part and integrally forming the second part from multiple layers of composite material.

19. The method of claim 15, wherein: Forming the first portion includes forming a second end of the first portion with a thickness defined in the range of 0.10 inches and 0.25 inches.

20. The method of claim 15, wherein: Forming the first portion includes forming a first end of the first portion with a thickness defined in the range of 0.04 inches and 0.15 inches.

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