Sealing systems for use with aircraft

Abstract

The present invention relates to a sealing system for use with an aircraft. A sealing system for an aircraft is disclosed. An exemplary sealing system includes a first seal coupled to a first thrust reverser portion, the first seal having a first cross-sectional shape. A second seal coupled to a second thrust reverser portion opposite the first seal. The second seal has a second cross-sectional shape different from the first cross-sectional shape. The second seal receives at least a portion of the first seal in response to the first seal engaging the second seal.

Description

Technical Field

[0001] The present disclosure relates generally to aircraft and, more particularly, to sealing systems for use with aircraft. Background Art

[0002] Aircraft engines employ thrust reversers that are movable between an open position and a closed position for maintenance and inspection. A gap that is typically formed between the thrust reversers when the thrust reversers are in the closed position can result in engine bypass air leakage. In order to seal the gap and prevent bypass air leakage, aircraft engines typically employ a bulb seal. For example, the bulb seal is typically coupled to a first thrust reverser plate and engages or contacts a second thrust reverser plate when the thrust reversers are in the closed position. Summary of the invention

[0003] An exemplary sealing system includes a first seal coupled to a first thrust reverser portion, the first seal having a first cross-sectional shape. A second seal is coupled to a second thrust reverser portion opposite the first seal. The second seal has a second cross-sectional shape different from the first cross-sectional shape. The second seal receives at least a portion of the first seal in response to the first seal engaging the second seal.

[0004] An exemplary sealing system includes a first seal having a first sealing body and a second seal having a second sealing body. At least a portion of the second sealing body deforms and wraps around at least a portion of the first sealing body in response to the first seal engaging the second seal.

[0005] An exemplary sealing system includes a first sealing device, wherein the first sealing device has a first cross-sectional shape. The system includes a second sealing device, wherein the second sealing device has a second cross-sectional shape different from the first cross-sectional shape. The second sealing device receives at least a portion of the first sealing device in response to the first sealing device engaging the second sealing device.

[0006] Furthermore, the present disclosure includes embodiments according to the following clauses:

[0007] Clause 1: A sealing system comprising a first seal coupled to a first thrust reverser portion and a second seal coupled to a second thrust reverser portion opposite the first seal, the first seal having a first cross-sectional shape, the second seal having a second cross-sectional shape different from the first cross-sectional shape, the second seal receiving at least a portion of the first seal in response to the first seal engaging the second seal.

[0008] Clause 2: The sealing system of clause 1, wherein the first seal has a circular cross-sectional shape when the first seal is in an uncompressed state.

[0009] Clause 3: The sealing system of any of the preceding clauses, wherein the second seal has a rectangular cross-sectional shape.

[0010] Clause 4: The sealing system of any of the preceding clauses, wherein the second seal is rotatable about a first pivot and a second pivot to enable a first portion of the second seal to sealingly engage a section of the first seal.

[0011] Clause 5: A sealing system according to any of the preceding clauses, wherein the second seal at least partially collapses in response to the first seal engaging the second seal so that at least a portion of the outer surface of the second seal can be wrapped around at least a portion of the outer surface of the first seal.

[0012] Clause 6: A sealing system according to any of the preceding clauses, wherein the first seal includes a first leg connecting the first seal to the first thrust reverser portion, and the second seal includes a second leg connecting the second seal to the second thrust reverser portion, and the first seal engages the second seal when the first thrust reverser portion and the second thrust reverser portion are in a closed position.

[0013] Clause 7: The sealing system of any of the preceding clauses, wherein the first seal and the second seal are comprised of the same material.

[0014] Clause 8: The sealing system of any of the preceding clauses, wherein the first seal and the second seal are comprised of different materials.

[0015] Clause 9: An aircraft comprising an engine having a thrust reverser portion and a sealing system according to any of the preceding clauses.

[0016] Clause 10: A sealing system comprising a first seal having a first sealing body and a second seal having a second sealing body, at least a portion of the second sealing body deforming and wrapping around at least a portion of the first sealing body in response to the first seal engaging the second seal.

[0017] Clause 11: A sealing system according to any of the preceding clauses, wherein when the first sealing body is in an uncompressed state, the first sealing body has a circular cross-sectional shape, and when the second sealing body is in an uncompressed state, the second sealing body has a rectangular cross-sectional shape.

[0018] Clause 12: The sealing system of any of the preceding clauses, wherein the second sealing body is configured to partially collapse in response to the first seal member engaging the second seal member.

[0019] Clause 13: The sealing system of any of the preceding clauses, wherein in response to collapse of the second seal, the second sealing body forms a pocket to receive the at least a portion of the first sealing body.

[0020] Clause 14: The sealing system of any of the preceding clauses, wherein in response to the first seal engaging the second seal, an outer surface of the second seal body defining the pocket conforms to a shape complementary to a shape of the first seal body engaging the outer surface of the second seal body.

[0021] Clause 15: The sealing system of any of the preceding clauses, wherein when the first seal engages the second seal, at least a portion of the second seal body has a cross-sectional shape that is complementary to a cross-sectional shape of the at least a portion of the first seal body.

[0022] Clause 16: The sealing system of any of the preceding clauses, wherein the first seal comprises a first standoff attaching the first seal body to a first structure, the first standoff being received by a channel of the first structure.

[0023] Clause 17: The sealing system of any of the preceding clauses, wherein the second seal comprises a second standoff attaching the second seal body to a second structure, the second standoff being received by a channel of the second structure.

[0024] Clause 18: A sealing system according to any of the preceding clauses, wherein the distance between the first transition portion and the second transition portion of the second seal when the sealing system is in an uncompressed state is greater than the distance between the first transition portion and the second transition portion when the sealing system is in a compressed state.

[0025] Item 19: A sealing system comprising a first sealing device and a second sealing device, wherein the first sealing device has a first cross-sectional shape, the second sealing device has a second cross-sectional shape different from the first cross-sectional shape, and the second sealing device receives at least a portion of the first sealing device in response to the first sealing device engaging the second sealing device.

[0026] Clause 20: The sealing system of any of the preceding clauses, wherein the first sealing means comprises first means for attaching the first sealing means to a first portion of a first structure.

[0027] Clause 21: A sealing system according to any of the preceding clauses, wherein the second sealing means comprises second means for attaching the second sealing means to a second portion of a second structure.

[0028] Clause 22: A method comprising engaging a first seal having a first sealing body with a second seal having a second sealing body such that in response to the first seal engaging the second seal, at least a portion of the second sealing body deforms and wraps around at least a portion of the first sealing body.

[0029] Clause 23: The method of any preceding clause, further comprising: partially collapsing the second seal in response to the first seal engaging the second seal.

[0030] Clause 24: The method of any of the preceding clauses, further comprising: the second sealing body forming a pocket to receive the at least a portion of the first sealing body in response to the second sealing body partially collapsing. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 An exemplary aircraft having an exemplary sealing system in accordance with the teachings of the present disclosure is shown.

[0032] Figure 2 yes Figure 1 A partially exploded view of an exemplary aircraft engine.

[0033] Figure 3 yes Figure 1-2 A perspective cutaway view of an exemplary aircraft engine of an exemplary aircraft.

[0034] Figure 4 is in the closed position Figure 1-3 A schematic front view of an exemplary aircraft engine.

[0035] Figure 5 is in the open position Figure 1-4 A schematic front view of an exemplary aircraft engine.

[0036] Figure 6 is a partial cross-sectional view of an exemplary sealing system disclosed herein shown in an uncompressed state.

[0037] Figure 7 Shown in compressed state Figure 6 A partial cross-sectional view of an exemplary sealing system.

[0038] Figure 8 yes Figure 6 and Figure 7 A partial cross-sectional view of an exemplary second seal of an exemplary sealing system, showing the exemplary second seal in phantom when the exemplary sealing system is in an exemplary uncompressed state, and showing the exemplary second seal in solid lines when the exemplary sealing system is in an exemplary compressed state.

[0039] Certain examples are shown in the figures identified above and described in detail below. In describing these examples, similar or identical reference numerals are used to identify the same or similar elements. The figures are not necessarily drawn to scale, and certain features and certain views of the figures may be shown exaggerated in scale or in schematic diagrams for clarity and / or conciseness. As used in this patent, stating that any part is positioned (e.g., located, set, formed, connected, etc.) on another part in any way means that the mentioned part is in contact with the other part, or the mentioned part is spaced apart from the other part with one or more intermediate parts in between. Stating that any part is in contact with another part means that there are no intermediate parts between the two parts. DETAILED DESCRIPTION

[0040] Known aircraft engines employ seals or sealing systems to seal gaps at interfaces between two aircraft structures (e.g., engine thrust reversers, doors, frames, etc.) to reduce air leakage and / or contain fires. During flight, pressure fluctuations may cause one or more structures employing seals to shift, bend, deflect, or otherwise move relative to seals and / or other structures of the aircraft. In some examples, the displacement of one or more structures may cause the seal to become over-compressed and / or under-compressed. For example, a bulb-shaped seal works best when compressed to 20% to 40% of its uncompressed diameter. Over-compression of a bulb-shaped seal (e.g., compression greater than 40% of the uncompressed diameter) may cause indentation and / or wear of the bulb-shaped seal, and under-compression of a bulb-shaped seal (e.g., compression less than 20% of the uncompressed diameter) may cause air leakage and / or seal fatigue, thereby causing premature failure of the seal and / or shortening the working life of the seal. In some cases, excessive compression of the bulb-shaped seal (e.g., compression greater than 50% of the uncompressed diameter) can result in permanent deformation of the seal, thereby rendering the seal ineffective. Additionally, a leaking seal can reduce aircraft engine efficiency and can affect fire detection, containment, and / or extinguishing. Furthermore, such known seals typically seal along contact points having a relatively small contact surface area. As a result, any defects or notches that may be formed on the outer surface of the seal can affect (e.g., reduce) the sealing ability of the seal.

[0041] In some cases, the high-speed air impact caused by the leakage may also cause damage to adjacent components (e.g., firewall blankets) downstream of the seal. For example, an aircraft engine using a thrust reverser has a seal between the inner walls of the thrust reverser halves of the nacelle. For example, the first part or first half of the thrust reverser may be opened relative to the second part or second half of the thrust reverser to provide access to the aircraft engine. When the thrust reverser is in a closed position, the seal of the aircraft engine seals the periphery of the first half and the second half of the thrust reverser. Some exemplary seals include a bulb-shaped seal (e.g., an Ω-shaped seal) on the first thrust reverser half, which compresses and seals the metal seal down-pressing surface located on the second thrust reverser half. However, due to the displacement of the aircraft structure (e.g., the first thrust reverser half and the second thrust reverser half) (which causes the bulb-shaped seal to become over-compressed or under-compressed), such a bulb-shaped seal may not provide a sufficiently tight seal during aircraft operation (e.g., flight). In some cases, this effect of aircraft structural shifting may cause the seal to fail prematurely and / or may not provide a sufficiently tight seal.

[0042] Compared to known seals or sealing systems, the example sealing systems disclosed herein significantly increase the useful life of the seals while providing a more effective seal (e.g., increased sealing force). For example, the example sealing systems disclosed herein can seal over a wider range of relative displacements of the aircraft structure during aircraft operation without being over-compressed by excessive compressive forces (e.g., greater than 50% of the uncompressed dimensional characteristic (e.g., diameter, width, etc.). In addition, the example sealing systems disclosed herein can surround or enclose a fire zone of an aircraft engine and provide a tortuous path that prevents or limits fire from leaving a designated fire zone of the aircraft engine.

[0043] The exemplary sealing system disclosed herein provides sealing at the interface between the first aircraft structure and the second aircraft structure. For example, the sealing system disclosed herein can seal the interface between the thrust reverser and the aircraft's pylon, the interface between the thrust reverser and the engine core, the interface between the first thrust reverser part and the second thrust reverser part, and / or any other interface of the aircraft. In some examples, the sealing system disclosed herein can prevent high-pressure air from leaking from the engine bypass to the fireproof compartment of the aircraft engine and / or prevent or extinguish fire from entering the engine bypass. Each exemplary sealing system disclosed herein includes a first seal and a second seal. In some examples, the first seal is a bulb-style seal, and the second seal is a cup seal. In some examples, the cup seal replaces the standard flat metal seal down pressure surface of the traditional or known cabin.

[0044] The first seal of the exemplary sealing system disclosed herein interacts or engages with the second seal to provide a tight seal. Specifically, the second seal is configured to partially collapse relative to the first seal to form a capsule to receive at least a portion of the first seal. For example, the concave or cup-shaped segment of the second seal is wrapped around at least a portion of the first seal (e.g., a portion of the circumference of the first seal) to form a tight seal (e.g., a tight aerodynamic seal). In this way, compared with known seals, the first seal engages the second seal on a larger amount of contact surface area. This increase in contact surface area provides greater friction between the first and second seals, thereby improving the sealing force of the sealing system. In addition, this increase in contact surface area reduces or eliminates the reduction in sealing effect caused by notches, flaws and / or permanent deformation that may be formed on the first seal and / or the second seal. In other words, the first seal and the second seal can provide a relatively tight seal, regardless of the notches, flaws and / or permanent deformation of the first seal and / or the second seal.

[0045] Figure 1 An exemplary aircraft 100 embodying aspects of the teachings of the present disclosure is shown. Figure 1 The aircraft 100 of the illustrated example includes wings 102 (e.g., right and left wings) extending laterally outward from a fuselage 104. Each of the wings 102 of the illustrated example supports an aircraft engine 106 via a pylon 108. Each aircraft engine 106 of the illustrated example is a gas turbine (e.g., a turbofan engine) that may embody aspects of the teachings of the present disclosure.

[0046] The exemplary teachings of the present disclosure are not limited to Figure 1 Aircraft 100. For example, the example sealing systems disclosed herein can be implemented with other types of aircraft, for example, other types of aircraft such as vertical take-off and landing aircraft, military aircraft, helicopters, drones and / or any other type of aircraft. In some examples, the seals disclosed herein can be implemented with other types of vehicles, other types of vehicles include but are not limited to ships, submarines, ground vehicles (e.g., racing cars, trains, cars, buses, etc.) and / or (one or more) any other vehicles or aerodynamic surfaces. The exemplary sealing systems disclosed herein can be used with aircraft engines, aircraft structures (e.g., fuselages) and / or any other aircraft structures that may need to be sealed. In some examples, the sealing systems disclosed herein can be used with buildings (e.g., garage doors, appliance doors, etc.) and / or other structures that may employ sealing.

[0047] Figure 2 is a sealing system 200 disclosed herein Figure 11. The exploded view of the aircraft engine 106 of the illustrated example. The aircraft engine 106 of the illustrated example is coupled to the wing 102 via the pylon 108. The aircraft engine 106 includes an inlet 202, a nacelle 204, an engine core 206, and a nozzle 208. The nacelle 204 of the illustrated example includes a fan door 210 and a thrust reverser 212. The thrust reverser 212 of the illustrated example includes a first thrust reverser portion 214 (e.g., a right-hand thrust reverser or first half) and a second thrust reverser portion 216 (e.g., a left-hand thrust reverser or second half). For example, the first thrust reverser portion 214 includes a first wall 218, and the second thrust reverser portion 216 includes a second wall 220. The first thrust reverser portion 214 and the second thrust reverser portion 216 surround or enclose the engine core 206. Additionally, the thrust reverser 212 may be movably coupled (eg, pivotally coupled) to the pylon 108 to allow access to the engine core 206 during maintenance.

[0048] Figure 3 yes Figure 1 FIG. 1 is a cross-sectional view of an aircraft engine 106. The aircraft engine 106 has a fan 302 that draws airflow 304 into an air inlet 306 defined by the inlet 202. The thrust reverser 212 is disposed between the engine core 206 and the first wall 218 and the second wall 220 ( Figure 2 ) define a bypass 308 between the intake 306 and the combustion chamber 312 of the engine core 206. In addition, the thrust reverser 212 of the illustrated example defines a designed core compartment fire zone 310. In operation, a portion 304a of the airflow 304 flows to the engine core 206, and a portion 304b of the airflow 304 flows through the bypass 308. The airflow 304 provided to the engine core 206 by the air intake 306 (e.g., by a compressor) is highly pressurized and provided to the combustion chamber 312 of the engine core 206, where the fuel is injected and mixed with the highly pressurized air and ignited. The heat energy from the combustion chamber 312 of the engine core 206 is discharged to the nozzle 208 (e.g., via a turbine) Figure 2 ), where the thermal energy mixes with a portion of the airflow (e.g., cool air) that is accelerated by fan 302 and passes through bypass 308. The converted thermal energy of engine core 206 and the accelerated airflow of bypass 308 are discharged from nozzle 208 to generate forward thrust that provides lift and / or propels aircraft 100 (e.g., in a forward direction).

[0049] The sealing system 200 disclosed herein prevents aerodynamic loss of the portion 304b of the airflow 304 in the bypass 308. For example, the sealing system 200 of the illustrated example prevents the portion 304b of the airflow 304 in the bypass 308 from leaking into the core compartment fire zone 310. In addition, the sealing system 200 of the illustrated example prevents fire from escaping from the core compartment fire zone 310 and entering the bypass 308 and / or other portions of the aircraft engine 106. Thus, the sealing system 200 provides a fireproof seal to contain a fire in a designated core compartment fire zone 310.

[0050] Figure 4 yes Figure 1-3 FIG. 4 is a schematic front view of an aircraft engine 106 showing the aircraft engine 106 in a closed position 400 . Figure 5 yes Figure 1-4 FIG. 5 is a schematic front view of an aircraft engine 106 , which shows the aircraft engine 106 in an open position 500 .

[0051] See also Figure 4 and Figure 5 To enable access to the engine core 206 (e.g., during maintenance), a first thrust reverser section 214 (e.g., a thrust reverser door) and a second thrust reverser section 216 (e.g., a thrust reverser door) are movably coupled to the pylon 108. For example, the first thrust reverser section 214 and the second thrust reverser section 216 are pivotally coupled to the pylon 108 via respective hinges 402, 404 to enable the first thrust reverser section 214 and the second thrust reverser section 216 to move between a closed position 400 and an open position 500. The aircraft engine 106 of the illustrated example includes a sealing system 200 to provide sealing at a first interface 406 between the pylon 108 and the thrust reverser 212, at a second interface 408 between the thrust reverser 212 and the engine core 206, and at a third interface 410 between the first thrust reverser section 214 and the second thrust reverser section 216.

[0052] The sealing system 200 of the illustrated example includes a first seal 412 engaging a second seal 414. Thus, each of the interfaces 406-410 includes a first seal 412 and a second seal 414. For example, the first seal 412 may be coupled to the first thrust reverser portion 214, and the second seal 414 may be coupled to the second thrust reverser portion 216. Additionally, the first seal 412 may be disposed around a perimeter (e.g., an edge) of the first wall 218 of the first thrust reverser portion 214, and the second seal 414 may be disposed around a perimeter (e.g., an edge) of the second wall 220 of the second thrust reverser portion 216. In some examples, the pylon 108 may include a first seal 412 on a first side 416 of the pylon 108 to engage or interact with a second seal 414 of the second thrust reverser portion 216, and the pylon 108 may include a second seal 414 on a second side 418 of the pylon 108 opposite the first side 416 to engage or interact with the first seal 412 of the first thrust reverser portion 214. Likewise, the engine core 206 may include a first seal 412 that engages or interacts with the second seal 414 of the second thrust reverser portion 216 and a second seal 414 that engages or interacts with the first seal 412 of the first thrust reverser portion 214.

[0053] Figure 6 This article discloses that Figure 1-5 6. A cross-sectional view of an exemplary sealing system 600 of an exemplary sealing system 200 of the illustrated example. The sealing system 600 of the illustrated example is shown in an initial or uncompressed state 601. The sealing system 600 of the illustrated example seals an interface 602 between a first structure 604 and a second structure 606. For example, the interface 602 may correspond to the first interface 406, the first structure 604 may correspond to the thrust reverser 212 (e.g., one of the first thrust reverser portion 214 or the second thrust reverser portion 216), and the second structure may represent the pylon 108. In some examples, the interface 602 may correspond to the second interface 408, the first structure 604 may correspond to the thrust reverser 212 (e.g., one of the first thrust reverser portion 214 or the second thrust reverser portion 216), and the second structure 606 may correspond to the engine core 206. In some examples, interface 602 may correspond to third interface 410, first structure 604 may correspond to first thrust reverser portion 214, and second structure 606 may correspond to second thrust reverser portion 216. In some examples, interface 602 may correspond to any other interface between two structures of aircraft engine 106.

[0054] The sealing system 600 includes a first seal 608 (e.g., corresponding to the first seal 222) and a second seal 610 (e.g., corresponding to the second seal 224). The first seal 608 of the illustrated example is coupled to the first structure 604, and the second seal 610 is coupled to the second structure 606. The first seal 608 is coupled to the first structure 604 via a first retainer 612, and the second seal 610 is coupled to the second structure 606 via a second retainer 614.

[0055] The first seal 608 of the illustrated example includes a first sealing body 616 (e.g., a first bulb) and a first leg 618. The first leg 618 is positioned or coupled within a first channel 612a of a first retainer 612, which is positioned or formed on a first wall 604a (e.g., a surface or edge) of a first structure 604. For example, to couple the first seal 608 to the first structure 604, the first leg 618 of the first seal 608 may be positioned or slid within the first channel 612a of the first retainer 612. In some examples, the first seal 608 may be coupled to the first structure 604 by a clip, a staple, an adhesive, and / or any other fastener(s). In some examples, the first seal 608 and / or the first sealing body 616 provide a first sealing device, and the first seal 608 and / or the first leg 618 provide a first device for attaching to the first retainer 612.

[0056] The first seal 616 of the illustrated example is a tubular structure defining a cavity 620. The first seal 616 has a length extending along the periphery or edge of the first wall 604a. The first seal 616 of the illustrated example has a first shape or structure. For example, the first seal 616 has a first cross-sectional shape (e.g., a circular cross section). The first seal 616 of the illustrated example has a thickness 622 defined by an inner diameter 624 and an outer diameter 626. For example, the thickness 622 of the first seal 616 is uniform around the circumference of the first seal 616. However, in some examples, the thickness 622 of the first seal 616 may vary (e.g., increase or decrease) around the circumference of the first seal 616. In some examples, the thickness 622 of the first seal 616 is approximately between one tenth (1 / 10) inch and one quarter (1 / 4) inch, the inner diameter 624 is between about 0.75 inch and 1.9 inches, and the outer diameter 626 is between about 1 inch and 2 inches. In some examples, first encapsulation 616 can have an oval cross-sectional shape or any other shape(s).

[0057] The second seal 610 of the illustrated example includes a second sealing body 628 (e.g., a second bulb-shaped or cup-shaped seal) and a second leg 630. The second leg 630 is positioned or coupled within a second channel 614a of a second retainer 614, which is formed along a portion of a perimeter or edge of a second wall 606a of a second structure 606. For example, in order to couple the second seal 610 to the second structure 606, the second leg 630 of the second seal 610 may be positioned or slid within the second channel 614a of the second retainer 614. In some examples, the second seal 610 may be coupled to the second structure 606 by a clip, a staple, an adhesive, and / or any other (one or more) fasteners. In some examples, the second seal 610 and / or the second sealing body 628 provide a second sealing device, and the second seal 610 and / or the second leg 630 provide a second device for attaching to the second retainer 614.

[0058] The second seal 628 of the illustrated example is a tubular structure having a cavity 632 and a length extending along a portion of the periphery or edge of the second wall 606a. The second seal 628 of the illustrated example has a shape or structure different from the shape of the first seal 616. For example, the second seal 628 of the illustrated example has a second cross-sectional shape different from the first cross-sectional shape of the first seal 616. The second seal 628 of the illustrated example has a rectangular cross-sectional shape. For example, the second seal 628 has a width 634 and a height 636. The height 636 of the illustrated example is greater than the width 634. However, in some examples, the width 634 may be less than or equal to the height 636. In some examples, the width 634 and / or height 636 of the second seal 628 may depend on the size (e.g., outer diameter 626) of the first seal 616. For example, the width 634 may be approximately 1 to 2 times larger than the outer diameter 626 of the first seal 616, and the height 636 may be approximately 0.5 to 1.5 times the width 634 of the second seal 628.

[0059] The second sealing body 628 includes a first side 638 (e.g., a front surface or a bonding surface), a second side 640 (e.g., an upper surface), a third side 642 (e.g., a lower surface), and a fourth side 644 (e.g., a rear surface). The first side 638 is located opposite the fourth side 644, and the second side 640 is located opposite the third side 642. The first side 638 has an arc shape or a first radius of curvature 646, which has a recess 648 (e.g., a cup-shaped portion) facing the first sealing body 616. The second side 640 has an arc shape or a second radius of curvature 650, which has a recess 652 facing away from the third side 642. The third side 642 has an arc shape or a third radius of curvature 654, which has a recess 656 oriented away from the second side 640. The fourth side 644 is substantially flat or straight. The second leg 630 of the illustrated example extends from the fourth side 644.

[0060] A first transition 658 (e.g., a first corner) between the first side 638 and the second side 640 has a first radius of curvature 660, a second transition 662 (e.g., a second corner) between the first side 638 and the third side 642 has a second radius of curvature 664, a third transition 666 (e.g., a third corner) between the second side 640 and the fourth side 644 has a third radius of curvature 668, and a fourth transition 670 (e.g., a fourth corner) between the third side 642 and the fourth side 644 has a fourth radius of curvature 672. In the example shown, the first radius of curvature 660 is substantially similar or identical to the second radius of curvature 664 (e.g., within 1%). The third radius of curvature 668 is substantially similar or identical to the fourth radius of curvature 672 (e.g., within 1%). The first radius of curvature 660 and the second radius of curvature 664 are different from the third radius of curvature 668 and the fourth radius of curvature 672.

[0061] In addition, the second seal 628 of the illustrated example has a thickness 674. In some examples, the thickness 674 of the second seal 628 varies (e.g., increases or decreases) along the perimeter of the second seal 628. For example, a first thickness 674a of at least a portion of the first side 638 can be different from a second thickness 674b of at least a portion of the second side 640 and / or a third thickness 674c of at least a portion of the third side 642. In some examples, the thickness 674 can be uniform or constant around the perimeter of the second seal 628.

[0062] The second seal 610 of the illustrated example is configured to partially collapse in response to the first seal 608 engaging the second seal 610. For example, the second seal 610 of the illustrated example is configured to deflect and / or conform to at least partially receive the first seal 608 (e.g., a portion of the first seal body 616). In order to enable the first side 638 to deflect and / or conform to the first seal 608, the second seal 610 of the illustrated example includes a first pivot 676 and a second pivot 678. The first pivot 676 of the illustrated example is located or formed on the second side 640, and the second pivot 678 of the illustrated example is located or formed on the third side 642. Specifically, the first pivot 676 is positioned at or near the midpoint between the first side 638 and the fourth side 644, and the second pivot 678 is positioned at or near the midpoint between the first side 638 and the fourth side 644.

[0063] The pivots 676, 678 may be formed as living hinges. For example, to provide the first pivot 676 and the second pivot 678, the second thickness 674b of a portion of the second side 640 defining the second pivot 676 and the third thickness 674c of a portion of the third side 642 defining the second pivot 678 may be less than the thickness 674 of other portions of the second side 640 and the third side 642 that do not define the first pivot 676 and the second pivot 678. The first pivot 676 and the second pivot 678 are flexible to allow rotation of the first transition portion 658 and the second transition portion 662 (e.g., without causing fatigue or cracking of the second side 640 and the third side 642). In addition, the second side 640 and the third side 642 each have a stiffness characteristic that resists buckling while allowing rotation about the first pivot 676 and the second pivot 678. The stiffness characteristics of the second side 640 and the third side 642 may be increased by increasing the number of fabric layers of the second side 640 and the third side 642.

[0064] Additionally, the first seal 608 of the illustrated example has a stiffness characteristic that is greater than a stiffness characteristic of the second seal 610. In some examples, the stiffness characteristic of the first seal 608 is greater than a stiffness characteristic of the second seal 610 due to the cross-sectional shape of the first seal body 616 compared to the cross-sectional shape of the second seal body 628. In some examples, the stiffness characteristic of the first seal 608 can be greater than a stiffness characteristic of the second seal 610 due to the material property(s) of the first seal 608 and the second seal 610.

[0065] The first seal 608 and the second seal 610 of the illustrated example may be constructed of the same material(s) or different materials(s). The first seal 608 and / or the second seal 610 may be constructed of materials including fiberglass and / or ceramic fabrics impregnated with silicone (e.g., high temperature silicone), metallic materials, elastomeric materials, and / or any other material(s).

[0066] Figure 7 is shown in a compressed state 700 (eg, an active state) Figure 6 6. Specifically, the sealing system 600 of the illustrated example seals a gap 702 between a first structure 604 and a second structure 606. The size of the gap 702 may vary due to different flight conditions during flight (e.g., pressure fluctuations, temperature fluctuations, etc.). For example, the size of the gap 702 may increase or decrease by approximately 0.3 inches. In some cases, the size of the gap 702 may increase or decrease by more than 0.3 inches.

[0067] In response to the first seal 608 engaging the second seal 610, the first seal 608 applies a force 704 to the first side 638 of the second seal 610, causing the first side 638 to compress and / or move toward the fourth side 644. In turn, the second seal 610 at least partially deforms and / or conforms to the shape of the first seal body 616. For example, in response to the first seal 608 engaging the second seal 610, at least a portion of the second seal body 628 deforms and / or wraps around at least a portion or segment 706 of the first seal body 616. Specifically, the second seal 610 deforms and / or collapses about the first pivot 676 and the second pivot 678, causing the first side 638 of the second seal 610 to sealingly engage the segment 706 of the first seal 608. In response to the second seal 610 collapsing, the second seal body 628 forms a pocket 708 to receive at least a portion of the first seal body 616. The first side 638 of the second seal body 628 defining the bladder 708 forms a shape that is complementary to the shape of the first seal body 616, with which the first seal body 616 engages the second seal body 628. For example, the first pivot 676 and the second pivot 678 enable the respective first transition portion 658 and the second transition portion 662 to move (e.g., roll or pivot) inwardly toward the first seal body 616 (e.g., toward the outer surface of the first seal body 616). In other words, the second seal 610 at least partially collapses in response to the first seal 608 engaging the second seal 610, so that at least a portion of the second seal 610 (e.g., the first side 638) can be wrapped around at least a portion of the first seal 608 (e.g., the segment 706). For example, when the sealing system 600 is in the compressed state 700, the first side 638 of the second seal body 628 at least partially surrounds the first seal body 616 (e.g., between 40% and 60% of the circumference of the first seal body 616). The first pivot 676 and the second pivot 678 provide flexibility to allow rotation of the corresponding first transition portion 658 and the second transition portion 662 and / or the second side 640 and the third side 642 without causing fatigue or fracture of the first transition portion 658 and the second transition portion 662 and / or the second side 640 and the third side 642.

[0068] Additionally, when the sealing system 600 is in the compressed state 700, the first side 638 has a fourth radius of curvature 710 that is different from (eg, smaller than) the fourth radius of curvature 710 when the sealing system 600 is in the uncompressed state 601 ( Figure 6). For example, when the sealing system 600 is in the compressed state 700, the fourth radius of curvature 710 of the first side 638 is substantially similar to (e.g., equal to or within 5% of) the radius of curvature 712 of the first seal body 616. Additionally, although not shown, the first seal body 616 of the first seal 608 may deform or compress (e.g., have an elliptical shape) when the first seal 608 engages the second seal 610 and / or when the size of the gap 702 decreases. In some such examples, the first side 638 conforms to the shape (e.g., elliptical shape) of the first seal body 616 that contacts (e.g., directly engages) the first side 638 of the second seal body 628. Thus, in some examples, at least a portion (e.g., the first side 638) of the second seal body 628 has a cross-sectional shape that is complementary to the cross-sectional shape of the portion of the first seal body 616 of the first seal 608 that engages the second seal 610.

[0069] Similarly, when the sealing system 600 is in the compressed state 700, the second side 640 has a fifth radius of curvature 714 that is different from the fifth radius of curvature 714 when the sealing system 600 is in the uncompressed state 601 ( Figure 6 Similarly, when the sealing system 600 is in the compressed state 700, the third side 642 has a sixth radius of curvature 716, which is different from the sixth radius of curvature 716 when the sealing system 600 is in the uncompressed state 601 ( Figure 6 ). In some examples, when the sealing system 600 is in the compressed state 700, the recessed portion 718 of the second side 640 of the second seal 610 faces the recessed portion 720 of the third side 642 of the second seal 610 (i.e., faces the recessed portion 720 of the third side 642 of the second seal 610). Figure 6 Recesses 718, 720 are in opposite orientations compared to corresponding recesses 652, 656 shown in FIG. 1 ).

[0070] Figure 8 The second seal 610 is shown in solid lines when the sealing system 600 is in a compressed state 700, and the second seal 610 is shown in dashed lines when the sealing system 600 is in an uncompressed state 601. Thus, for example, when the gap 702 changes and / or when the first structure 604 (e.g., the first thrust reverser portion 214) moves relative to the second structure 606 (e.g., the second thrust reverser portion 216) to an open position (e.g., Figure 5 When the first seal 608 and the second seal 610 are in the open position 500, Figure 6 The uncompressed state 601 and Figure 7As the first side 638 moves toward the fourth side 644 along the direction 802, the first transition portion 658 and the second transition portion 662 move toward the first seal body 616. For example, when the second seal 610 is in the compressed state 700, the distance 804 between the first transition portion 658 and the second transition portion 662 (e.g., Figure 8 The vertical distance in the orientation of the first transition portion 658 is less than the distance 806 between the first transition portion 658 and the second transition portion 662 when the second seal 610 is in the uncompressed state 601.

[0071] The deflection or cupping of the first side 638 of the second seal 610 relative to the first seal body 616 of the first seal 608 increases the contact surface area between the first seal 608 and the second seal 610. Increasing the contact surface area between the first seal 608 and the second seal 610 significantly increases the friction or sealing force between the first seal 608 and the second seal 610. As a result, the seal provided between the first seal 608 and the second seal 610 can withstand a greater amount of force during operation. For example, the seal can withstand the force from the bypass 308 ( Figure 3 ) of the high pressure airflow, and thus provide an improved barrier to prevent air leakage compared to conventional seals. In some examples, the sealing system 600 of the illustrated example forms a tortuous path for fire, and thus provides an improved barrier to prevent air leakage in the core compartment fire zone 310 (compared to conventional seals). Figure 3 )It is more effective to contain the fire inside.

[0072] In addition, during operation, the size of the gap 702 can change during flight. For example, due to pressure fluctuations, the gap 702 can increase or decrease by an amount between about 0.5 inches and 3 inches. In some examples, the gap 702 can be greater than 3 inches. As the size of the gap 702 changes, the first seal 608 remains in sealing engagement with the second seal 610, because the first pivot 676 and the second pivot 678 enable the first transition portion 658 and the second transition portion 662 to move or rotate with the first seal body 616 to maintain the seal. Due to the flexibility of the first seal 608 and the second seal 610, the sealing system 600 of the illustrated example is more effective than conventional seals when sealing a wider range of deflections. In some examples, in order to improve the (one or more) cup seal compression characteristics of the sealing system 600, a foam structure (e.g., a tubular structure) can be positioned in the cavity 620 of the first seal 608 and / or in the cavity 632 of the second seal 610.

[0073] As can be appreciated from the foregoing, exemplary methods, apparatus, and articles improve seal effectiveness by increasing the seal contact area and / or friction between seals. This improved seal effectiveness provides an improved barrier to air leakage and / or improved fire containment. In addition, the increased seal contact area enables the seal to better tolerate defects or surface repairs, and / or enables the sealing system to be more effective over a larger deflection range. In some examples, the increased seal contact area reduces over-compression, thereby reducing damage that might otherwise be caused by over-compression of the seal. In some examples, the increased seal contact area reduces damage to the seal surface that might otherwise occur due to relative motion (e.g., friction) between the seals.

[0074] "Include" and "comprising" (and all forms and tenses thereof) are used herein as open-ended terms. Thus, whenever a claim employs any form of "includes" or "comprising" (e.g., comprises, includes, comprising, including, having, etc.) as a preamble or in any kind of claim reference, it should be understood that additional elements, terms, etc. may be present without falling outside the scope of the corresponding claim or reference. As used herein, when the phrase "at least" is used as a transitional term, such as in the preamble of a claim, it is open-ended in the same manner as the terms "includes" and "comprising." When the term "and / or" is used, such as when used in a form such as A, B, and / or C, it 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 mean implementations that include any of (1) at least one A, (2) at least one B, and (3) 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 mean implementations that include any of (1) at least one A, (2) at least one B, and (3) 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 mean implementations that include any of (1) at least A, (2) at least B, (3) at least A and at least 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 mean implementations that include any of (1) at least A, (2) at least B, and (3) at least A and at least B.

[0075] At least some of the foregoing examples include one or more features and / or benefits including, but not limited to, the following:

[0076] Example 1 includes a sealing system having a first seal coupled to a first thrust reverser portion, wherein the first seal has a first cross-sectional shape. A second seal coupled to a second thrust reverser portion opposite the first seal. The second seal has a second cross-sectional shape different from the first cross-sectional shape. The second seal receives at least a portion of the first seal in response to the first seal engaging the second seal.

[0077] Example 2 includes the system of Example 1, wherein the first seal has a circular cross-sectional shape when the first seal is in an uncompressed state.

[0078] Example 3 includes the system of any of Examples 1-2, wherein the second seal has a rectangular cross-sectional shape.

[0079] Example 4 includes the system of any of Examples 1-3, wherein the second seal is rotatable about a first pivot and a second pivot to enable a first portion of the second seal to sealingly engage a section of the first seal.

[0080] Example 5 includes a system according to any of Examples 1-4, wherein the second seal at least partially collapses in response to the first seal engaging the second seal so that at least a portion of the outer surface of the second seal can be wrapped around at least a portion of the outer surface of the first seal.

[0081] Example 6 includes a system according to any of Examples 1-5, wherein the first seal includes a first leg coupling the first seal to the first thrust reverser portion, and the second seal includes a second leg coupling the second seal to the second thrust reverser portion, the first seal engaging the second seal when the first thrust reverser portion and the second thrust reverser portion are in a closed position.

[0082] Example 7 includes the system of any of Examples 1-6, wherein the first seal and the second seal are comprised of the same material.

[0083] Example 8 includes the system of any of Examples 1-7, wherein the first seal and the second seal are comprised of different materials.

[0084] Example 9 includes an aircraft comprising an engine having a thrust reverser portion and a sealing system according to any of Examples 1-8.

[0085] Example 10 includes a sealing system having a first seal including a first sealing body and a second seal including a second sealing body. At least a portion of the second sealing body deforms and wraps around at least a portion of the first sealing body in response to the first seal engaging the second seal.

[0086] Example 11 includes the system of Example 10, wherein the first sealing body has a circular cross-sectional shape when the first sealing body is in an uncompressed state, and the second sealing body has a rectangular cross-sectional shape when the second sealing body is in an uncompressed state.

[0087] Example 12 includes the system of any of Examples 10-11, wherein the second seal is configured to partially collapse in response to the first seal engaging the second seal.

[0088] Example 13 includes the system of any of Examples 10-12, wherein, in response to the second sealant collapsing, the second sealant forms a pocket to receive the at least a portion of the first sealant.

[0089] Example 14 includes a system according to any of Examples 10-13, wherein, in response to the first seal engaging the second seal, an outer surface of the second seal body defining the bladder conforms to a shape complementary to a shape of the first seal body engaged with the outer surface of the second seal body.

[0090] Example 15 includes the method of any of Examples 10-14, wherein when the first seal engages the second seal, at least a portion of the second seal has a cross-sectional shape that is complementary to a cross-sectional shape of the at least a portion of the first seal.

[0091] Example 16 includes the system of any of Examples 10-15, wherein the first seal comprises a first standoff attaching the first seal body to a first structure, the first standoff being received by a channel of the first structure.

[0092] Example 17 includes the system of any of Examples 10-16, wherein the second seal comprises a second standoff attaching the second seal body to the second structure, the second standoff being received by a channel of the second structure.

[0093] Example 18 includes a system according to any of Examples 10-17, wherein a distance between a first transition portion and a second transition portion of the second seal when the sealing system is in an uncompressed state is greater than a distance between the first transition portion and the second transition portion when the sealing system is in a compressed state.

[0094] Example 19 includes an exemplary sealing system including a first sealing device having a first cross-sectional shape and a second sealing device having a second cross-sectional shape different from the first cross-sectional shape. The second sealing device receives at least a portion of the first sealing device in response to the first sealing device engaging the second sealing device.

[0095] Example 20 includes the system of Example 19, wherein the first sealing device includes a first device for attaching the first sealing device to a first portion of a first structure.

[0096] Example 21 includes the system of any of Examples 19-20, wherein the second sealing device includes a second device for attaching the second sealing device to a second portion of a second structure.

[0097] Example 23 includes a method comprising engaging a first seal having a first sealing body with a second seal having a second sealing body such that in response to the first seal engaging the second seal, at least a portion of the second sealing body is deformed and wrapped around at least a portion of the first sealing body.

[0098] Example 24 includes the method of Example 23, further comprising partially collapsing the second seal in response to the first seal engaging the second seal.

[0099] Example 25 includes the system of any of Examples 23-24, further comprising the second sealing body forming a bladder to receive the at least a portion of the first sealing body in response to the second sealing body partially collapsing.

[0100] Although certain exemplary methods, apparatus, and articles have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all methods, apparatus, and articles that fully fall within the scope of the claims of this patent.

Claims

1. A sealing system, comprising: a first seal coupled to the first thrust reverser portion, the first seal having a first cross-sectional shape; as well as a second seal coupled to a second thrust reverser portion opposite the first seal, the second seal having a second cross-sectional shape different from the first cross-sectional shape, the second cross-sectional shape including a first side, a second side, a third side opposite the second side, and a fourth side opposite the first side, the first side having a recessed portion configured to at least partially collapse and wrap around at least a portion of the first seal in response to the first seal engaging the second seal, the second side having a recessed portion with two ends distal to the third side and a middle proximate to the third side, and the third side having a recessed portion with two ends distal to the second side and a middle proximate to the second side; wherein the second seal includes a first pivot formed on the second side and a second pivot formed on the third side to allow a first angle between the first side and the second side and a second angle between the first side and the third side to rotate about the first pivot and the second pivot, respectively, in response to the first seal engaging the second seal, so that the recess of the first side can sealingly engage at least a portion of the first seal.

2. The sealing system of claim 1, wherein the first seal has a circular cross-sectional shape when the first seal is in an uncompressed state, and optionally wherein the second seal has a rectangular cross-sectional shape.

3. The sealing system of claim 1 , wherein the first seal includes a first leg coupling the first seal to the first thrust reverser portion, and the second seal includes a second leg coupling the second seal to the second thrust reverser portion, the first seal engaging the second seal when the first thrust reverser portion and the second thrust reverser portion are in a closed position.

4. The sealing system according to any one of claims 1 to 3, wherein the first seal and the second seal are composed of the same material.

5. The sealing system according to any one of claims 1 to 3, wherein the first seal and the second seal are composed of different materials.

6. An aircraft comprising an engine having a thrust reverser section and a sealing system according to claim 1.

7. A sealing system comprising: a first seal having a first sealing body; and A second seal having a second sealing body, the second sealing body comprising a first side, a second side, a third side opposite the second side and a fourth side opposite the first side, the first side having a recess, the recess being configured to at least partially collapse and wrap around at least a portion of the first sealing body in response to the first seal engaging the second seal, the second side having a recess with both ends away from the third side and a middle close to the third side, the third side having both ends away from the second side and a middle close to the second side, wherein the second seal comprises a first pivot formed on the second side and a second pivot on the third side to allow a first angle between the first side and the second side and a second angle between the first side and the third side to rotate about the first pivot and the second pivot, respectively, in response to the first seal engaging the second seal, so that the recess of the first side can sealingly engage the at least a portion of the first sealing body.

8. The sealing system of claim 7, wherein: The first sealing body has a circular cross-sectional shape when the first sealing body is in an uncompressed state, and the second sealing body has a rectangular cross-sectional shape when the second sealing body is in an uncompressed state.

9. The sealing system of claim 8, wherein: In response to the second seal collapsing, the second seal body forms a pocket to receive the at least a portion of the first seal body, and optionally wherein in response to the first seal engaging the second seal, an outer surface of the second seal body defining the pocket conforms to a shape complementary to the shape of the first seal body engaged with the outer surface of the second seal body.

10. The sealing system of any one of claims 7-9, wherein when the first seal engages the second seal, at least a portion of the second seal body has a cross-sectional shape that is complementary to a cross-sectional shape of the at least a portion of the first seal body.

11. A sealing system according to claim 7, wherein the first seal includes a first leg attaching the first seal body to a first structure, the first leg being received by a channel of the first structure, and optionally wherein the second seal includes a second leg attaching the second seal body to a second structure, the second leg being received by a channel of the second structure.

12. The sealing system of claim 7, wherein a distance between a first transition portion and a second transition portion of the second seal when the sealing system is in an uncompressed state is greater than a distance between the first transition portion and the second transition portion when the sealing system is in a compressed state.

13. A sealing system comprising: a first sealing device having a first cross-sectional shape; and A second sealing device, the second sealing device has a second cross-sectional shape different from the first cross-sectional shape, the second cross-sectional shape includes a first side, a second side, a third side opposite the second side, and a fourth side opposite the first side, the first side having a recess, the recess being configured to at least partially collapse and wrap around at least a portion of the first sealing device in response to the first sealing device engaging the second sealing device, the second side having a recess with both ends away from the third side and the middle close to the third side, the third side having both ends away from the second side and the middle close to the second side, wherein the second sealing device includes a first pivot formed on the second side and a second pivot formed on the third side to allow a first angle between the first side and the second side and a second angle between the first side and the third side to rotate around the first pivot and the second pivot respectively in response to the first sealing device engaging the second sealing device, so that the recess on the first side can sealingly engage the at least a portion of the first sealing device.

14. The sealing system of claim 13, wherein the first sealing means comprises first means for attaching the first sealing means to a first portion of a first structure.

15. The sealing system of claim 14, wherein the second sealing means comprises second means for attaching the second sealing means to a second portion of a second structure.

16. A method for sealing, comprising: A first seal having a first sealing body is engaged with a second seal having a second sealing body, the second sealing body comprising a first side, a second side, a third side opposite the second side, and a fourth side opposite the first side, the first side having a recessed portion so that the recessed portion of the first side at least partially collapses and wraps around at least a portion of the first sealing body in response to the first seal engaging the second seal, wherein the second side has a recessed portion with both ends away from the third side and a middle close to the third side, and the third side has a recessed portion with both ends away from the second side and a middle close to the second side, wherein the second seal comprises a first pivot formed on the second side and a second pivot formed on the third side so that during engagement, a first angle between the first side and the second side and a second angle between the first side and the third side rotate about the first pivot and the second pivot, respectively, so that the recessed portion of the first side can sealingly engage the at least a portion of the first seal.

17. The method of claim 16, further comprising the second sealing body forming a pocket to receive the at least a portion of the first sealing body in response to the second sealing body partially collapsing.

Images