Engine mounting joint accessory

Abstract

The invention relates to an engine mounting section accessory. Accessory for mounting an engine to an aircraft wing. The fitting includes a body having a first end and a second end. A first pocket is located at the first end, wherein the first pocket is sized to receive a front engine mount assembly. A second pocket is located at the second end, wherein the second pocket is sized to receive a strut of an aircraft wing. The body includes a first section and a second section connected together.

Description

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS

[0002] This application claims priority to U.S. Provisional Patent Application Serial No. 63 / 540,434, filed on September 26, 2023, which is incorporated herein by reference in its entirety. Technical Field

[0003] The present disclosure relates generally to the field of aircraft engine mounts and, more particularly, to an engine mount constructed from multiple sections to facilitate attachment of an engine to an aircraft wing. Background Art

[0004] Certain aircraft include wings with structural members that support the engines. The structural members are designed to support the engines and securely connect them to the aircraft. Due to the position of the structural members relative to the engines, the structural members affect the airflow, thereby affecting the operation of the engines. The aerodynamics of the structural members have a greater impact in aircraft with certain engines, such as those that include exposed blades. One type is an unducted turbofan engine that includes exposed fan blades combined with a gas turbine engine. Fan aerodynamics become highly sensitive to the shape and size of the structural members.

[0005] The design aspects of the structural members are usually a compromise between aerodynamic and structural requirements. Aerodynamic requirements prefer that the structural members be small and unobtrusive to reduce aerodynamic drag. Structural requirements require that the structural members be of sufficient size and dimensions to support the engine.

[0006] Therefore, there is a need for a structural member that effectively mounts an engine to an aircraft and also includes an efficient aerodynamic design. Summary of the invention

[0007] One aspect relates to an accessory for mounting an engine to a wing of an aircraft. The accessory includes a body having a first end and a second end. A first pocket is located at the first end, wherein the first pocket is sized to receive a front engine mounting section accessory. A second pocket is located at the second end, wherein the second pocket is sized to receive a strut box of the aircraft wing. The body includes a first section and a second section connected together.

[0008] In another aspect, the first section and the second section are abutted together at a joint extending along the length of the body.

[0009] In another aspect, the body includes a tapered shape that increases from the first end to the second end.

[0010] In another aspect, the taper is consistent along the length from the first end to the second end.

[0011] In another aspect, the first segment is a mirror image of the second segment.

[0012] In another aspect, the first end is open to receive the front engine mounting bracket and the second end is open to receive the strut box.

[0013] In another aspect, a flange extends along a first side of the body and an opposing second side of the body, wherein the flange includes a central flange section and transversely extending reinforcements spaced along the length of the central flange section.

[0014] In another aspect, a first portion of the flange is mounted to the first segment and a second portion of the flange is mounted to the second segment.

[0015] In another aspect, a container is positioned along a side of the body, wherein the container includes opposing transverse walls extending outwardly from the side of the body and one or more ribs extending between the transverse walls.

[0016] In another aspect, the ribs extend outwardly from the inner sides of the first segment and the second segment, wherein the ribs abut together when the first segment and the second segment are connected together.

[0017] In another aspect, the body includes two or more planar sides.

[0018] One aspect relates to a fitting for mounting an engine to a wing of an aircraft. The fitting includes a first section and a second section, each section including: a lateral side; a top side; a bottom side; and an inner side. The first section and the second section are configured to be connected together along the inner side to form a body, wherein the body includes: a first side formed by the lateral side of the first section; a second side formed by the lateral side of the second section; a third side formed by the top side of the first section and the second section; and a fourth side formed by the bottom side of the first section and the second section.

[0019] In another aspect, an interior space is within the body, wherein the interior space includes a first pocket at a first end of the body to receive a forward engine mount accessory and a second pocket at a second end of the body to receive a strut box of the wing.

[0020] In another aspect, the first pocket and the second pocket are both surrounded by the first section and the second section.

[0021] In another aspect, the first segment is a mirror image of the second segment.

[0022] In another aspect, the ribs extend outwardly from inner surfaces of lateral sides of the first segment and the second segment, wherein the ribs have exposed ends that abut together when the first segment and the second segment are connected together.

[0023] In another aspect, the lateral sides are flat to connect with brackets of the rear engine mounting fitting.

[0024] In another aspect, a flange extends outwardly from the body and includes a flange segment and a transverse stiffener, wherein the flange is configured to form a structural interface that is subjected to both shear and tension.

[0025] In another aspect, the fastener extends through the first section and connects it to the second section.

[0026] In another aspect, the first section and the second section are abutted together at a joint extending longitudinally through the body.

[0027] One aspect relates to a method of attaching an engine to a wing of an aircraft. The method includes: attaching a first fitting to a first section of a rear engine mounting node fitting of a back fitting; attaching a second fitting to a second section of the rear engine mounting node fitting of the back fitting and connecting the first section and the second section of the back fitting together; attaching a front engine mounting node fitting to the back fitting; attaching the back fitting to a strut box on the wing of the aircraft; and attaching an engine to the front engine mounting node fitting and the first fitting and the second fitting of the rear engine mounting node fitting, thereby attaching the engine to the wing of the aircraft.

[0028] In another aspect, the method further includes positioning a front engine mounting node assembly at first ends of the first section and the second section, and then coupling the first section and the second section of the back assembly together and coupling the front engine mounting node assembly to the back assembly.

[0029] In another aspect, the method further includes aligning a first section of the flange on the first segment with a second section of the flange on the second segment and connecting the first segment and the second segment together and forming a single flange extending along the length of the spine fitting.

[0030] The features, functions, and advantages that have been discussed may be achieved independently in various aspects or may be combined in yet other aspects, further details of which may be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 is an isometric view of an aircraft equipped with the fittings for mounting the engines to the wings.

[0032] Figure 2 is a side view of a spine fitting located at the end of a strut box and configured to mount an engine to an aircraft wing.

[0033] Figure 3 is an isometric view of a spine assembly connected to a front engine mounting node assembly and a rear engine mounting node assembly.

[0034] Figure 4 yes Figure 3 Side view of the back accessory.

[0035] Figure 5 is a side view of the inner surface of the first section of the spinal fitting.

[0036] Figure 6 is a schematic cross-sectional view of a front engine mounting section assembly connected to the end of a spine assembly, wherein the view is along Figure 4 The VI-VI line is intercepted.

[0037] Figure 7 is a bottom view of an example of a spine accessory.

[0038] Figure 8 is a bottom view of another example of a spine accessory.

[0039] Fig. 9 A method of attaching an engine to an aircraft wing is shown. DETAILED DESCRIPTION

[0040] Figure 1 An aircraft 100 is shown that includes a fuselage 101 and wings 102. An engine 103 is mounted to each of the wings 102. Although the number and positioning of the engines 103 along the wings 102 can vary, this particular aircraft 100 includes an engine 103 mounted to each of the wings 102. The engines 103 are mounted to aerodynamic strut boxes 104 below the wings 102. Various types of engines 103 can be used in the aircraft 100. In some examples, the engines 103 include exposed fan blades. One specific example is an unducted turbofan engine with an exposed fan 105.

[0041] Figure 2 A side view of an engine 103 mounted to a strut box 104 of a wing 102 is shown. The strut box 104 includes a back assembly 20. The back assembly 20 is connected to the front end of the strut box 104. The back assembly 20 is connected to the engine 103 through a front engine mounting node assembly 30 and a rear engine mounting node assembly 40. In the embodiment of the present invention, the engine 103 is an unducted turbofan engine. Figure 2 In the example of the front engine mounting node assembly 30 and the rear engine mounting node assembly 40 are both connected to the engine fan bracket 106 on the front of the engine 103. In one example, the front engine mounting node assembly 30 and the rear engine mounting node assembly 40 are spaced about 30 inches apart along the engine 103.

[0042] The fan 105 of the engine 103 is located in front of the back assembly 20. The air flowing through the fan 105 passes through the back assembly 20, which is covered by an aerodynamic forward pylon fairing (not shown). The shape of the back assembly 20 is designed to reduce the impact of the airflow on the fan 105. In some examples, the back assembly 20 is directly behind the center of the fan 105.

[0043] Figure 3 The back assembly 20 is shown attached to the front engine mounting section assembly 30 and the rear engine mounting section assembly 40. The back assembly 20 includes a body 21 having an elongated shape, wherein the body has a front end 22 and a rear end 23. In some examples, the body 21 has a substantially rectangular cross-sectional shape including four sides. The body 21 includes opposing top and bottom sides 24, 25 and opposing lateral sides 26, 27. Figure 3 As shown, one or more sides may be substantially flat. This shape facilitates attachment of the rear mounting section 40 and airflow. In some examples, one or more sides are open or have openings.

[0044] In some examples, the body 21 has a tapered shape with a smaller cross-sectional area at the front end 22 and a larger cross-sectional area at the rear end 23. This tapered shape provides a transition between the strut box connected to the rear end 23 and the front engine mounting node 30 connected to the front end 22. The tapered shape also helps airflow. In some examples, the taper is consistent along the length from the front end 22 to the rear end 23.

[0045] The body 21 is formed of two sections 51, 52 that abut together and form a joint 53. In some examples, the two sections 51, 52 have a clamshell design that aligns together. The two sections 51, 52 include exposed edges along the inside that abut together to form the joint 53. In some examples, each of the sections 51, 52 is substantially equal and forms half of the back accessory 20. In one specific example, the sections 51, 52 are mirror images. In some examples, the sections 51, 52 have different shapes and / or sizes, wherein one of the sections 51, 52 is larger than the other.

[0046] An advantage of forming the body 21 from two sections 51, 52 is that the inside can be accessed before they are connected together. This provides access to the fasteners 110 used to connect one or more of the front engine mounting node assembly 30 and the rear engine mounting node assembly 40. This overcomes the current problem of not being able to access these fasteners (commonly referred to as "blind fasteners") within the closed interior of the strut box.

[0047] In such Figure 3 In some examples shown, each segment 51, 52 includes a respective lateral side 26, 27 and a portion of the top side 24 and the bottom side 25. Figure 3 In one example shown, each segment 51, 52 forms half of the top side 24 and the bottom side 25. The two segments 51, 52 are abutted together along a joint 53 extending longitudinally through the body 21. When connected, the exposed edges of the segments 51, 52 abut together. In some examples, the edges are flat and aligned to abut together in a non-overlapping configuration. In some examples, the edges are configured to overlap when abutting together. A specific example includes exposed edges configured to form a lap joint.

[0048] The flange 60 extends along one or more sides of the body 21. The flange 60 is configured to form a structural interface that withstands both shear and tensile loads across the joint 53. The flange 60 is located along one or more sides of the spine fitting 20. In some examples, the flange 60 is located along the top side 24 and the bottom side 25. In some examples, the spine fitting 20 does not include the flange 60.

[0049] The flange 60 includes a central flange section 61 and reinforcements 62 spaced apart along the flange section 61. The reinforcements 62 extend laterally outward from the flange section 61 and have a gradually decreasing height that decreases as it moves away from the flange section. The reinforcements 62 structurally support the flange section 61. The flange section 61 includes a front end and a rear end that are tapered to improve structural load distribution. In instances where the flange 60 is provided on two or more sides of the back accessory 20, the flange 60 may have the same or different configurations. In some instances, the flange 60 is symmetrical about a centerline extending along the flange section 61.

[0050] In some examples, the flange 60 is divided between the first section 51 and the second section 52. Each of the sections 51, 52 includes a portion of the flange section 61 and a set of reinforcements 62. When the sections 51, 52 are abutted together, the opposing flange sections abut together and form a single flange section 61.

[0051] The two sections 51, 52 are connected together by a fastener 110. The fastener 110 extends through the two sections 51, 52 and bridges the joint 53. Figure 3 and Figure 4 In one example shown, each of the segments 51, 52 includes a portion of the flange segment 61. The fastener 110 extends through the flange segment 61 and connects the segments 51, 52 together. In this configuration, the fastener 110 is aligned perpendicular to the joint 53.

[0052] An internal space 29 is formed within the spine accessory 20. The two sections 51, 52 can be designed with various numbers and arrangements of ribs and pocket configurations. The sections 51, 52 are designed to optimize the load distribution in the spine accessory 20 itself when reacting to the engine mounting interface loads between the engine 103 and the strut box 104.

[0053] Figure 5 and Figure 6 Aspects of the interior space 29 are shown. The interior space 29 includes a pocket area 28 at the front end 22 that is open to receive a front engine mounting node 30. Figure 5 and Figure 6 An example of a pocket 28 located at the front end 22 and sized to receive a front engine mounting joint accessory 30 is shown. The pocket 28 has a width W measured between opposing sides. In some examples, the width W decreases toward the front end 22. In some examples, the front engine mounting joint accessory 30 includes a tapered shape corresponding to the tapered width W of the pocket 28. These corresponding shapes maintain the front engine mounting joint accessory 30 attached to the spine accessory 20 and prevent unintentional separation from the front end 22. In some examples, the thickness of the flanges 33a, 33b is different, so that the width W of the pocket 28 is constant and the front engine mounting joint accessory 30 is not captive when the two halves are joined together. Additionally or alternatively, one or more fasteners 110 connect the front engine mounting joint accessory 30 to the spine accessory 20.

[0054] One or more ribs 70 extend outwardly from the opposite sides and through the interior space 29. The ribs 70 provide strength and rigidity to the back accessory 20. In some examples, the ribs 70 extend between the opposite lateral sides 26, 27. The ribs 70 are formed from different segments extending outwardly from the sides of different segments 51, 52. When the segments 51, 52 are connected together, the ribs 70 on each of the segments are aligned and abut together.

[0055] Figure 5 The inside of the segment 51 is shown. The ribs 70 are positioned in different orientations, extending outwardly from the inner surface of the lateral side 26. The pockets 54 are formed at the ribs 70. The second segment 52 (not shown) will include ribs with a similar arrangement so that the ribs abut together when the segments 51, 52 are connected together. The configuration of the ribs 70 can be varied to accommodate different engine mounting configurations and can be optimized.

[0056] The interior space 29 also includes a pocket 89 at the rear end 23. The pocket 89 is sized to receive the strut box 104. In some examples, one or more fasteners 110 connect the strut box 104 to the pocket 89 of the spine accessory 20.

[0057] The back fitting 20 is configured to be connected to the rear engine mounting node fitting 40, which in turn is connected to the engine 103. The rear engine mounting node fitting 40 includes fittings 41 mounted to the lateral sides 26, 27 of the back fitting 20. Fasteners 110 connect the fittings 41 to the back fitting 20.

[0058] Figure 7 A bottom view of one example of a back accessory 20 is shown. Accessories 41a, 41b are attached to opposing lateral sides 26, 27, respectively. Fasteners 110 extend through accessories 41a, 41b and lateral sides 26, 27 and into interior space 29 within back accessory 20.

[0059] Figure 8 A bottom view of another example of a back fitting 20 is shown. The bottom side 25 includes a container 80 positioned to receive a fastener 110 connecting the fittings 41a, 41b. The container 80 includes a transverse wall 81 extending along the length of the fittings 41a, 41b connection. The container 80 is designed to allow the fastener 110 interface between the fittings 41a, 41b and the transverse sides 26, 27 to extend below the bottom side 25. The container 80 also includes a central rib 82 spanning the gap between the transverse walls 81. A gap 83 is formed between the transverse wall 81 and the rib 82. In some examples, the container 80 is a separate fitting that engages with the first and second sections 51, 52 and spans between the two fittings 41a, 41b. In other examples, the container 80 is an integral part of the first and second sections 51, 52. The fastener 110 extends through the transverse sides 26, 27 and the transverse wall 81 and into the gap 83. In one example, the fastener 110 includes a shear pin.

[0060] Fig. 9 A method of attaching an engine 103 to a wing 102 of an aircraft 100 is shown. A first fitting 41a of a rear engine mounting node fitting 40 is attached to a first section 51 of a back fitting 20 (block 300). A second fitting 41b is attached to a second section 52 of the back fitting 20 (block 302). The first section 51 and the second section 52 are connected to a front engine mounting node fitting 30 (block 304). In some examples, the front engine mounting node fitting 30 is located between two separate sections 51, 52. The sections 51, 52 are then connected together, thereby attaching the front engine mounting node fitting 30 to the back fitting 20. The back fitting 20 is attached to a strut box 104 (block 306). The strut box 104 including the back fitting 20 is mounted on the wing 102 (block 308). The engine 103 is attached to the wing 102 by attaching to the front mounting node fitting 30 and the rear engine mounting node fitting 40 (block 310).

[0061] The back fitting 20 can be used to connect various engines 103 to the wing 102 of the aircraft 100. In some examples, the engine 103 has exposed fan blades. A specific example is a non-ducted turbofan engine. In other examples, the engine 103 includes a ducted fan.

[0062] Various types of fasteners 110 are used to connect the segments 51, 52 and to connect the front engine mounting node assembly 30 and / or the rear engine mounting node assembly 40. Examples include, but are not limited to, rivets, pins, nuts / bolts, and studs.

[0063] With respect to quantities or measurements, the term "substantially" means that the characteristic, parameter or value described need not be achieved precisely. Rather, deviations or changes, including, for example, tolerances, measurement errors, measurement precision limitations and other factors known to those skilled in the art, may occur in amounts that do not eliminate the effect that the characteristic is intended to provide.

[0064] Without departing from the essential characteristics of the invention, the present disclosure may be carried out in other ways than those specifically set forth herein. The present embodiments should be considered in all respects as illustrative and not restrictive, and all changes within the meaning and equivalent range of the appended claims are intended to be embraced therein.

[0065] Parts List

[0066] 20 Back Accessories

[0067] 21 Subject

[0068] 22 Frontend

[0069] 23 Backend

[0070] 24 Top side

[0071] 25 bottom side

[0072] 26 lateral side

[0073] 27 lateral side

[0074] 28 pockets

[0075] 29 Interior Space

[0076] 30 Front mounting section accessories

[0077] 31 Center Arm

[0078] 32 Back member

[0079] 33 Transverse Wing

[0080] 40 rear installation section accessories

[0081] 41 Bracket

[0082] 51 First Segment

[0083] 52 Second Segment

[0084] 53 Connector

[0085] 54 Open side

[0086] 60 Flange

[0087] 61 Flange section

[0088] 62 reinforcement

[0089] 70 ribs

[0090] 75 Piano Hinge

[0091] 76 pieces (Leaf)

[0092] 77 pieces

[0093] 78 Knuckle

[0094] 79 Pin

[0095] 80 Containers

[0096] 81 lateral wall

[0097] 82 Ribs

[0098] 83 Gap

[0099] 89 Pocket Zone

[0100] 100 Aircraft

[0101] 101 Body

[0102] 102 Wing

[0103] 103 Engine

[0104] 104 Pillar Box

[0105] 105 Fan

[0106] 106 Engine Mount

[0107] 107 Turbine Frame

[0108] 108 Pillars

[0109] 110 Fasteners

Claims

1. An accessory for mounting an engine 103 to a wing 102 of an aircraft, the accessory comprising: a body 21 having a first end 22 and a second end 23; a first pocket 28 at the first end 22 sized to receive a front engine mounting joint fitting 30 ; a second pocket 89 at the second end 23, the second pocket 89 being sized to receive a strut box of the wing 102 of the aircraft; and The main body 21 includes a first section 51 and a second section 52 connected together. 2 . The fitting of claim 1 , wherein the first section 51 and the second section 52 abut together at a joint 53 extending along the length of the body 21 . 3 . The accessory of claim 1 , wherein the body 21 comprises a tapered shape that increases from the first end 22 to the second end 23 . 4 . The fitting of claim 3 , wherein the taper is uniform along the length from the first end 22 to the second end 23 . 5 . The accessory of claim 1 , wherein the first section 51 is a mirror image of the second section 52 . 6 . The fitting of claim 1 , wherein the first end 22 is open to receive the front engine mounting node fitting 30 , and the second end 23 is open to receive the strut box 104 .

7. The fitting of claim 1 further comprising a flange 60 extending along a first side of the body 21 and an opposing second side of the body 21, the flange 60 comprising a central flange section 61 and transversely extending reinforcements 62 spaced apart along the length of the central flange section 61. 8 . The fitting according to claim 7 , wherein a first portion of the flange 60 is mounted to the first section 51 , and a second portion of the flange 60 is mounted to the second section 52 . 9 . The accessory of claim 1 , further comprising a container 80 positioned along a side of the body 21 , the container 80 comprising opposing transverse walls 81 extending outwardly from the sides of the body 21 and one or more ribs 82 extending between the transverse walls 81 .

10. The accessory of claim 1, further comprising a rib 70 extending outwardly from an inner side of the first section 51 and the second section 52, wherein the rib 70 abuts together when the first section 51 and the second section 52 are connected together.

11. The accessory of claim 9, wherein the body 21 comprises two or more flat sides.

12. An accessory for mounting an engine 103 to a wing 102 of an aircraft, the accessory comprising: The first section 51 and the second section 52 each include: lateral side; Top side; bottom side; medial side; The first section 51 and the second section 52 are configured to be connected together along the inner side to form a main body 21, wherein the main body 21 includes: a first side formed by said lateral sides of said first section 51; a second side formed by said lateral side of said second section 52; a third side formed by the top sides of the first section 51 and the second section 52; and A fourth side is formed by the bottom sides of the first section 51 and the second section 52 .

13. The accessory according to claim 12 further includes an internal space 29 located within the body 21, the internal space including a first pocket area 28 located at a first end of the body 21 to receive a front engine mounting node accessory 30 and a second pocket area 89 located at a second end of the body 21 to receive a strut box 104 of the wing 102. 14 . The accessory of claim 13 , wherein the first pocket 28 and the second pocket 89 are each surrounded by the first section 51 and the second section 52 . 15 . The accessory of claim 12 , wherein the first section 51 is a mirror image of the second section 52 .

16. The accessory of claim 12, further comprising a rib 70 extending outwardly from the inner surface of the lateral sides of the first section 51 and the second section 52, the rib 70 having exposed ends that abut together when the first section 51 and the second section 52 are connected together.

17. The fitting of claim 12, further comprising a flange 60 extending outwardly from the body 21 and comprising a flange segment 61 and a transverse reinforcement 62, the flange 60 being configured to form a structural interface subject to both shear and tension. 18 . The accessory of claim 12 , further comprising a joint 53 wherein the first section 51 and the second section 52 abut together, wherein the joint 53 extends longitudinally through the body 21 .

19. A method of attaching an engine 103 to a wing 102 of an aircraft, the method comprising: Attaching the first fitting 41a to the first section 51 of the rear engine mounting node fitting 40 of the spine fitting 20; Attaching a second fitting 41b to the second section 52 of the rear engine mounting joint fitting 40 of the back fitting 20 and connecting the first section 51 and the second section 52 of the back fitting 20 together; Attaching the front engine mounting node fitting 30 to the back fitting 20; attaching the spine assembly to a strut box 104 on a wing 102 of an aircraft; and The engine 103 is attached to the first fitting 41 a and the second fitting 41 b of the front engine mounting node fitting 30 and the rear engine mounting node fitting 40 , thereby attaching the engine 103 to the wing 102 of the aircraft.

20. The method according to claim 19 further includes positioning the front engine mounting joint accessory 30 at the first end of the first section 51 and the second section 52, and then connecting the first section 51 and the second section 52 of the spine accessory 20 together, and connecting the front engine mounting joint accessory 30 to the spine accessory 20.

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