• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A thermal insulation system (135) is described for a component of an aircraft to protect the component, e.g., engine heat. The component includes a latch half (136) which is attached thereto, which is also covered by the thermal insulation system (135). In some scenarios, half of the latch (136) must be detached from the component because latch (138) is locked in the closed position. The thermal insulation system (135) includes a portion (141) thereof that overlaps half of the latch (136) and detaches from the other portion of the thermal insulation system (135) when half of the latch (136) is detached.
    公开号:FR3018770A1
    申请号:FR1552323
    申请日:2015-03-20
    公开日:2015-09-25
    发明作者:Michael Sean Pretty；Stephen M Erickson
    申请人:Rohr Inc；
    IPC主号:
    专利说明:

    [0001] The present disclosure relates to nacelles for an aircraft propulsion system, and more specifically, to thermal insulators which protect the nacelles from the heat of the engine. HISTORY During the maintenance of an airplane, the internal parts of the propulsion system may have to be accessed. Access can be achieved by tilting one or more parts of the nacelle from a closed position to an open position. One or more parts of a nacelle can be held together by latches. If a latch does not release, it may be necessary to remove it so that the basket can be opened. Latch removal can result in damage to parts of the Thermal Protection System ("SPT"), which is typically composed of thermal insulators attached to the pod components to protect them from radiant convective heat from the engine. This can result in the grounding of an aircraft until the SPT can be replaced, which is detrimental to the availability or the rate of use of the aircraft.
    [0002] SUMMARY In various embodiments, a system may include a structure, a latch system, a first portion of an SPT, and a second portion of an SPT. The latch system may include a first half-latch and a second half-latch. The first half-latch can be attached to the structure. The first part of the SPT can be coupled to the structure. The second part of the SPT can be coupled to the first half-latch. The first part of the SPT and the second part of the SPT comprise a detachable seal formed between them. The detachable seal can be configured to separate when the first half-latch is removed from the structure.
    [0003] The detachable seal can be created in a material having adhesive characteristics. The material may be vulcanized silicone at room temperature. The detachable seal can be created with a spot weld.
    [0004] The first half of the latch can be coupled to the structure by a plurality of fasteners. The first half of the latch can be detachably coupled to the structure by fasteners. The first part can be re-attachable to the second part by at least one material having adhesive properties and spot welding. The structure may be configured to surround an engine core and wherein the first portion of the STP is configured to thermally isolate the engine core structure. In various embodiments, a propulsion system may include a gas turbine engine, a first panel, a second panel, a first half latch, a second half latch and a thermal protection system. The first panel and the second panel may be adapted to be removable between an open position in which access to the engine is permitted during maintenance and a closed position in which the first and second panels substantially surround and enclose at least a portion of the motor. The first half-latch can be connected to the first panel. The second half-latch can be connected to the second panel. The first and second half latches may be adapted to lock together when the first and second panels are in the closed position to maintain the panels in the closed position. The thermal protection system may cover a substantial portion of a face of the first panel facing the engine when the first and second panels are closed. The thermal protection system may include a detachable portion surrounding and substantially covering the first half-latch. The first panel and the second panel may be parts of a fixed internal structure. The detachable portion may be a frangible seal. The frangible seal can be made of at least one spot weld and the vulcanized silicone at room temperature. In various embodiments, a thermal protection system may include a first portion of the insulation and a second portion of the insulation. The second part of the insulation can be coupled to the first part of the insulation by a detachable joint. The detachable seal may be configured to allow substantially permanent attachment of the second portion of the insulation to the first portion of the insulation during operation. The detachable seal may also be configured to allow the second portion of the insulation to separate cleanly from the first portion of the insulation in response to a maintenance event. The first part of the insulation can be configured to attach to a fixed internal structure. The detachable portion may be a frangible seal. The frangible seal can be made of at least one spot weld and the vulcanized silicone at room temperature. The frangible joint can be defined by overlapping folds between the first part of the insulation and the second part of the insulation. The substantially permanent attachment between the first part of the insulation and the second part of the insulation may be an overlap fold between the first part of the insulation and the second part of the insulation. The substantially permanent attachment between the first portion of the insulation and the second portion of the insulation may be interference between the first portion of the insulation and the second portion of the insulation. The foregoing features and elements may be combined in various non-exclusive combinations, unless otherwise indicated in this document. These features and elements as well as the operation of the disclosed embodiments will be more apparent in light of the following description and accompanying illustrations. BRIEF DESCRIPTION OF THE FIGURES The object of the present disclosure is particularly emphasized and distinctively claimed in the conclusion portion of the description. A more complete understanding of the present disclosure, however, can be obtained by referring to the detailed description and claims when considered in connection with the illustrations, in which the corresponding figures denote corresponding elements. 3 FIG. 1A illustrates a perspective view of an aircraft, according to various embodiments. FIG. 1B illustrates an exploded perspective view of a propulsion system according to various embodiments.
    [0005] FIG. 2 illustrates a sectional front view of a view of a propulsion system according to various embodiments. FIG. 3A illustrates a fixed internal structure including a thermal protection system according to various embodiments. FIG. 3B illustrates a first portion of the seal and a second portion of the seal that connect the two hemispheres of the nacelle, according to various embodiments. FIG. 4A schematically illustrates a first part of a fixed internal structure and a second part of a fixed internal structure connected together by a set of latches, according to various embodiments.
    [0006] FIG. 4B schematically illustrates a first portion of a fixed internal structure separated from a second portion of a fixed internal structure, in accordance with various embodiments. DETAILED DESCRIPTION The detailed description of the exemplary embodiments described herein refers to the accompanying drawings, which illustrate exemplary embodiments by the illustration. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the inventions, it should be understood that other embodiments can be made and that logical modifications and adaptations in the design can be made. and the construction may be made in accordance with the invention and the teachings herein. Thus, the detailed description given herein is presented for illustrative and non-limiting purposes only. For example, the steps described in any of the methods or process descriptions can be performed in any order and are not necessarily limited to the order presented. In addition, any reference to the singular comprises plural embodiments, and any reference to several components or steps may include an embodiment or a singular step. But also, any reference to the terms "attached", "fixed", "connected", etc., may include any permanent, removable, temporary, partial, full 4 and / or any other possible attachment option. In addition, any reference to the term "contactless" (or similar terms) may also include reduced contact or minimal contact. In addition, any reference to the singular comprises plural embodiments, and any reference to several components or steps may include an embodiment or a singular step. The shaded lines on the surface can be used in all figures to identify different parts but not necessarily to identify the same material or different materials. In this context, the term "aft" describes the direction associated with the tail (for example, the aft end) of an aircraft, or generally, the direction of the exhaust of a gas turbine. In this context, the term "before" describes the direction associated with the nose (for example, the front end) of an aircraft, or generally, the direction of flight or movement. In various embodiments and with reference to FIGs. 1A and 1B, an aircraft 100 may include a fuselage 102 and a pair of wings 104. The propulsion system 110 (e.g., a turbojet engine having a pod assembly) may be mounted below the wing 104. The Propulsion system 110 may be configured to provide forward thrust and / or propulsion for the aircraft 100. In various embodiments, the propulsion system 110 may include a motor 140 (eg, a blower 142). and a motor core 144), a pylon 115 is a nacelle assembly. The typical nacelle assembly, or simply a nacelle, may comprise an inlet 120, a fan cowl 125, a thrust reverser 130A and 130B, and an exhaust system comprising an exhaust cone 145 and a nozzle. 150. The nacelle surrounds the motor core 144 providing smooth aerodynamic surfaces for the flow of air around the motor 140 and therein. The nacelle also helps define a deflection air duct through the propulsion system 110. In various embodiments, a blower 142 can suck and direct a flow of air into and through the propulsion system 110. After the blower 142, the air is divided into two main flow paths, one path passing through the motor core 144, and the other path passing through a deflection air duct. The flow path of the motor core is oriented in the motor core 144 and initially passes through a compressor which increases the pressure of the air flow, and then through a combustion chamber in which the air is mixed with the air. fueled and lit. Combustion of the fuel / air mixture causes rotation of a series of turbine blades at the rear of the engine core 144, and drives the rotor and blower of the engine. The high pressure exhaust gases from combustion of the fuel / air mixture are then directed through the exhaust nozzle 150 at the rear of the engine 140 for thrust. In various embodiments and with reference to FIGs. 1B and 2, the path of the deflection air duct comprises air that is oriented around the motor core 144 in a duct or ducts defined by the nacelle (e.g., the area after the blower 142 and between the thrust reverser 130 and the fixed internal structure ("SIF") 131). The SIF includes a SIF panel 131A and a SIF panel 131B. The deflected air exits the deflection air ducts A1 and A2 at an exhaust nozzle at the rear end of the nacelle for thrust. In turbojet engines, the deflection flow generally provides a large percentage of the thrust for an aircraft. The deflection air ducts A1 and A2 in the nacelle of FIG. 2 are C-shaped, and are primarily defined by the outer surface of SIF 131 and the inner surface of the thrust reverser 130A and 130B (illustrated as thrust reverser 130A and thrust reverser 130B in FIG 1B). In various embodiments, the motor 140 may be mounted on a tower 115 at two locations. One of these places is the rear end of the tower 115, above the turbojet housing, and in one of the two places at the front end of the tower 115: the engine core (core mounting) or the blower housing of the motor (blower mounting). Pylon 115 transmits structural loads (including thrust) between engine 140 and wing 104 as shown in FIG. 1A. In various embodiments, the thrust reverser 130 may comprise two halves, a thrust reverser 130A and a thrust reverser 130B, generally configured to surround the engine core 144. The thrust reverser 130 may be hinged to the pylon 115 through one or more hinges that can allow access to the inner portion of the propulsion system 110 and / or the engine 140. For example, as shown in FIG. 2, the thrust reverser 130A and the thrust reverser 130B can be opened and / or rotated around an attachment point on the tower 115. The thrust reverser 130 can comprise a SFI 131A panel and a panel SFI 131B and an outer sleeve. The SFI panel 131A and the SFI panel 131B can generally surround the motor core 144. In various embodiments, the first hemisphere of the thrust reverser 130A and the second hemisphere of the thrust reverser 130B can be actuated by a closed position and held together by a system of latches. In this regard, the latch system may be configured to hold and / or retain the first hemisphere of the thrust reverser 130A and the second hemisphere of the thrust reverser 130B in a closed position about the engine core 144. In various embodiments and still with reference to FIGs. 1B and 2, the thermal protection system ("SPT") 135 (e.g., one or more thermal insulators) can be installed on the inner surface of the SFI 131 facing the motor core 144. The SPT 135 can be configured to isolate and / or retain heat from the motor core 144. The SPT 135 may be configured to act as an insulating barrier to protect the IF1 131 against heat emitted by the motor core 144 and other components . Without the thermal protection of the SPT 135, the IFS 131 can overheat and lose its structural integrity. The SPT 135 can generally be linked to a connector panel of each of the SFI panel 131A and the SFI panel 131B. In this regard, fasteners may couple the SPT 135 and / or at least portions of the SPT 135 to the link panel. The bonding panel may form the inner surface of each SFI 131A panel and SFI 131B panel. In various embodiments and with reference to FIGs. 3A-3B, the SFI panel 131A and the SFI panel 131B can be held and / or connected together by a latch system 138. The latch system 138 may be any suitable latch system. For example, the latch system 138 may be a front-end latch system. The latch system 138 may include a first portion of the seal 136 (e.g., a first half of the latch) and a second portion of the seal 137 (e.g., a second half of the latch). The front protection latch system must be remotely operable. For example, the front-end latch system may include a cable 132 that can be actuated to open the latch system 138, thereby allowing the SFI panel 131A and the SFI panel 131B to separate and open. In addition, the latch system 138 may constrain and / or limit the SFI panel 131A and the panel 131B to bend outward. In various embodiments and with reference to FIGs. 3A-3B and 4A-4B, during maintenance, the latch system 138 may be released to allow access to portions of the propulsion system 110, such as, for example, the motor core 144. In operation, the SFI panel 131A and the SFI panel 131B can be operably coupled together and closed when the first portion of the seal 136 is locked to the second portion of the seal 137. To unlock the latch system 138, the first part of the seal 136 may be released from the second portion of the seal 137. In some circumstances, the latch system 138 may be blocked and it becomes impossible to release the first portion of the seal 136 from the second portion of the seal 137. Since the first portion of the seal 136 is attached to the SFI panel 131A, and the second portion of the seal 137 is attached to the SFI panel 131B, when the latch is locked, the panels 131A and 131B can not be separated. res and open for access during the interview. In such a scenario, it becomes necessary to disconnect the first portion 136 of the SFI 131A panel. To do this, fasteners 139-1, 139-2 and 139-3 and any other fasteners securing the first portion 136 to the SFI panel 131A can be removed. Fasteners 139 can be accessed from the blower duct. The SFI panel 131A, when completely separated from the first portion of the seal 136, can now be folded out of the SFI panel 131B and opened.
    [0007] In a typical nacelle installation, an integral portion of the SPT 135A that overlaps the first portion of the seal 136 may be trapped between the first portion of the seal 136 and the second portion of the seal 137, while the other portion of the SPT 135A opens with half of SFI 131A, which can tear the SPT 135A and cause irreparable damage. The irreparable damage required the replacement of the entire portion of the TPS (eg, TPS 135A), which can be time consuming and expensive. In various embodiments, the SPT 135 may comprise individual parts, parts, and / or modules including, for example, the first portion 141 and the second portion 143. The first portion 141 of the SPT 135A may surround the first portion of the seal 136. and may be an individual part of the SPT 135. In this regard, the first portion 141 of the SPT 135A may be coupled to the other portion of the SPT 135A by a "detachable" seal 133. The detachable seal 133 may be configured to permit separate an individual part of TPS 135 (eg, first part 141 of TPS 135A and / or second part 143 of TPS 135B) from the other part of TPS 135 without any irreparable and / or significant damage or deformation and / or degradation. In various embodiments, the detachable seal 133 may be any seal that provides clean separation (e.g., nondestructive separation) between the individual parts of the SPT 135. In this regard, the detachable seal 133 does not cause of damage, deformation and / or irreparable degradation to the 8 connected structures in response to the separation of the detachable seal 133. For example, the detachment point 133 may be a frangible seal, a spot weld, a fold overlapping between individual parts of SPT 135, or overlapping and interfering individual parts TPS 135 (e.g., when a first part 141 and SPT 135A have an interference fit with each other). In various embodiments, the latch system 138 may be detached from the SPT 131 (eg, by removing fasteners 139) allowing at least one of the first portion 141 and the second portion 143 to separate from the SPT 135 at a detachable seal 133. As indicated herein, the detachable seal 133 may be a straddle joint, a folded seal and / or a frangible seal. In this regard, the first portion 141 and / or the second portion 143 may be removed, separated and / or detached from the SPT 135 at the detachable seal 133 without damaging, cutting and / or removing other individual portions of the SPT 135A and or 135B to have access to the first portions of the seal 136 and / or the second portion of the seal 137.
    [0008] In various embodiments, the detachable seal 133 may comprise a material and / or a tack with adhesive characteristics such as, for example, room temperature silicone vulcanization (RTV), spot welding, and / or etc. . In this regard, the detachable seal 133 may be coupled and / or bonded to individual parts of the SPT 135 in a substantially permanent manner for the operation of the aircraft. However, during maintenance and in case of failure of the latch system 138, the first joint portion 136 and the second portion of the seal 137 may be detached from the SFI panels 131A or 131B, respectively, and the first portion 141 of the SPT 135A and / or the second portion 143 of the SPT 135B may be cleanly and non-destructively separated from the other portion of the SPT 135A or 135B. The semi-permanent nature of the detachable seal 133 may allow the opening of a locked latch system 138 without significant damage to the SPT 135. In this regard, the first portion 141 of the SPT 135A and / or the second portion 143 of the SPT 135B may detach from the remainder of the SPT 135 structure, reducing, limiting and / or eliminating any damage, deformation and / or degradation of the SPT 135.
    [0009] In various embodiments, the latch system 138, the first portion of the gasket 136 and / or the second portion of the gasket 137 may be repaired in response to the detachment of the first portion 141 and / or the second portion 143 of the SPT 135 In this regard, when IFC 131 is open, a technician can access the latch system 138 to perform a repair. In response to the completion of the repair, the detachable seal 93 can be relocated between the SPT 135 and at least one of the first portion 141 and the second portion 143. In this regard, the SPT 135, the first portion 141 and / or the second portion 143 may be intact and may be reused. The benefits, other benefits, and solutions to the problems have been described here in relation to the specific embodiments. In addition, the connection lines illustrated in the various figures of this document are intended to represent an example of functional relationships and / or physical couplings between the various elements. It should be noted that several functional or alternative or additional physical connections may be present in a practical system.
    [0010] However, any benefits, advantages, solutions to problems or anything that permits the achievement, or improvement, of a benefit, advantage or solution should not be interpreted as critical, necessary or essential elements, or elements of any of the inventions. According to the present invention, the reference to an element in the singular does not mean "one and only one" except in the case of precision, but rather "one or more". In addition, when a sentence similar to "at least one of A, B or C" is used in, it is contemplated that the sentence be interpreted to have the meaning that only A may be present in one embodiment, B alone may be present in one embodiment, only C may be present in one embodiment, or any combination of elements A, B and C may be present in a single embodiment; or that any combination of elements A, B and C may be present in a single embodiment; for example, A and B, A and C, B and C or A and B and C. Systems, methods and apparatus are described herein. In the detailed description given herein, references to "various embodiments", "an embodiment", "an exemplary embodiment", etc., indicate that the described embodiment may comprise a property, structure or particular feature, but not all embodiments necessarily have the particular property, structure, or feature. In addition, such sentences do not necessarily refer to the same embodiment. In addition, when a particular property, structure, or feature is described in relation to an embodiment, it is understood that a domain specialist has the ability to assign such a particular property, structure, or feature in relation to other embodiments, whether or not explicitly described. After reading the description, it will be obvious to a specialist of the relevant field (s) to implement the disclosure in alternative embodiments. As used herein, the terms "comprises", "including" or any other variation thereof, are intended to cover a non-exclusive inclusion, so that a process, method, article or that a device that includes a list of elements includes not only these elements but may include other elements that are not expressly listed or inherent in such a process, method, article or apparatus. 11
    权利要求:
    Claims (6)
    [0001]
    REVENDICATIONS1. System comprising: a structure; a latch system (138) including a first latch half (136) and a second latch half (137), the first latch half (136) attached to the structure; a first portion (141) of a thermal protection system ("SPT") (135) coupled to the structure; a second portion (143) of the STP (135) coupled to the first half of the latch (136), the first portion (141) of the STP (135) and the second portion (143) of the STP (135) having a detachable seal ( 133) formed therebetween, the detachable seal (133) being configured to separate in response to the removal of the first half of the latch (136) from the structure.
    [0002]
    The system of claim 1, wherein the detachable seal (133) is created in a material having adhesive characteristics.
    [0003]
    3. System according to claim 2, wherein the material is vulcanized silicone at room temperature.
    [0004]
    The system of claim 1, 2 or 3, wherein the detachable seal (133) is created with a spot weld.
    [0005]
    The system of any preceding claim, wherein the first half of the latch (136) is coupled to the structure by a plurality of fasteners (139).
    [0006]
    The system of claim 5, wherein the first half of the latch (136) is detachably coupled to the structure by fasteners (139). A system according to any one of the preceding claims, wherein the first portion (141) is re-attachable to the second portion (143) by at least one material having adhesive properties and spot welding. The system of any preceding claim, wherein the structure is configured to surround a motor core (144) and wherein the first portion (141) of the STP (135) is configured to thermally isolate the core structure. of motor (144). 9. Propulsion system (110), comprising: a turbojet engine (140); a first panel (131A) and a second panel (131B) adapted to be removable between an open position in which access to the motor (140) is allowed during maintenance and a closed position in which the first and second panels ( 131A, 131B) surround and substantially enclose at least a portion of the motor (140); a first latch half (136) connected to the first panel (131A); a second latch half (137) connected to the second panel (131B), the first and second half of the latch (136, 137) being adapted to lock together when the first and second panels (131A, 131B) are in position closed to hold the panels (131A, 131B) in the closed position; a thermal protection system (135) covering a substantial portion of a face of the first panel (131A) facing the motor (140) when the first and second panels (131A, 131B) are closed; and the thermal protection system (135) may include a detachable portion (133) surrounding and substantially covering the first half-latch (136). The propulsion system of claim 9, wherein the first panel (131A) and the second panel (131B) are portions of a fixed internal structure (131). The propulsion system of claim 9 or 10, wherein the detachable portion (133) constitutes a frangible seal. The propulsion system of claim 11, wherein the frangible seal is made of at least one spot weld and the vulcanized silicone at room temperature. A thermal protection system (135) comprising: a first portion of the insulation (141); a second portion of the insulation (143) coupled to the first portion of the insulation (141) via a detachable seal (133), wherein the detachable seal (133) is configured to allow substantially permanent attachment of the second portion from the insulator (143) to the first portion of the insulator (141) during operation, and wherein the detachable seal (133) is configured to allow the second portion of the insulator (143) to separate cleanly the first portion of the insulation (141) in response to a maintenance event. The thermal protection system of claim 13, wherein the first portion of the insulation (141) is configured to attach to a fixed internal structure (131). The thermal protection system of claim 13 or 14, wherein the detachable portion (133) constitutes a frangible seal. The propulsion system of claim 15, wherein the frangible seal is made of at least one spot weld and the vulcanized silicone at room temperature. 17. The propulsion system of claim 15 or 16, wherein the frangible seal is defined by overlapping folds between the first portion of the insulator (141) and the second portion of the insulator (143). The thermal protection system of any one of claims 13 to 17, the substantially permanent attachment between the first portion of the insulation (141) and the second portion of the insulation (143) being an overlap fold between the first part of the insulation (141) and the second part of the insulation (143). 14. The thermal protection system of any one of claims 13 to 18, the substantially permanent attachment between the first part of the insulator (141) and the second part of the insulator (143) being an interference between the first part insulation (141) and the second part of the insulation (143). 15
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    同族专利:
    公开号 | 公开日
    US9932119B2|2018-04-03|
    FR3018770B1|2019-05-17|
    US20150266587A1|2015-09-24|
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    法律状态:
    2016-02-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-02-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-01| PLSC| Publication of the preliminary search report|Effective date: 20180601 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-18| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14222428|2014-03-21|
    US14/222,428|US9932119B2|2014-03-21|2014-03-21|Break-away thermal blanket joint|
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