• 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:
    An aircraft propulsion system includes a fixed internal structure (SIF) (132, 137) and an outer sleeve (465, 460) that can be separately coupled to a pylon (110). For example, the internal fixed structure (465, 460) and the outer sleeve (432, 437) can be removable independently of one another. A single lock of the closure system (200) disclosed herein may be configured to lock the panels (eg, the two halves of the SIF (432, 437) and the two doors of the outer sleeve (465, 460)) together and / or in a close position and retained.
    公开号:FR3013682A1
    申请号:FR1461552
    申请日:2014-11-27
    公开日:2015-05-29
    发明作者:Anthony Lacko
    申请人:Rohr Inc；
    IPC主号:
    专利说明:

    [0001] The present disclosure relates to an aircraft engine nacelle, and more particularly to the construction of a thrust reverser of such a nacelle. BACKGROUND A nacelle for a turboprop system on a typical commercial aircraft represents the structure that surrounds the engine to provide smooth aerodynamic surfaces for the flow of air around and within the engine. The nacelle also makes it possible to define a bypass air duct through the propulsion system. The nacelle may also include a thrust reverser that can deploy and provide reverse thrust that helps slow the aircraft after landing. The structure of the thrust reverser is generally constructed in two halves which are mounted separately through hinges on either side of the propulsion system. Both halves can be unlocked and opened to allow access to the engine for maintenance or other purposes. SUMMARY A system for closing a thrust reverser of an aircraft as described herein. In this system, the fixed internal structure (SIF) and the outer sleeve can be coupled separately to the pylon. For example, the fixed internal structure (SIF) and the outer sleeve can be articulated separately to the pylon. For example, the fixed internal structure and the outer sleeve can be removable independently of one another. A single closure of the closure system disclosed herein may be configured to lock the panels (e.g., the two halves of the SIF and the two doors of the outer sleeve) together and / or in a close and retained position. There is provided a closure system configured for a thrust reverser of an engine nacelle comprising: 1 a first outer sleeve holder a second outer sleeve holder each mounted for movement between an open position of an outer sleeve holder and a closed position of an outer sleeve door; a first half of the inner fixed structure and a second half of the inner fixed structure each removably mounted between an open position and a closed position, the first half of the inner fixed structure and the second half of the inner fixed structure being configured for a kinematic movement independent of the kinematic movement independent of the first door of the outer sleeve and the second door of the outer sleeve, and wherein in response to the fact that the first door of the outer sleeve and the second door of the outer sleeve being in position closed, the first half of the internal fixed structure and the second half of the internal fixed structure are retained so that the kinematic movement between the open position and the closed position of the first half of the internal fixed structure and the second half of the internal fixed structure is prevented.
    [0002] The closure system may further include a pylon The first half of the inner fixed structure and the second half of the inner fixed structure may be hingedly coupled to the pylon along a first axis of rotation. The first outer sleeve door and the second outer sleeve door may be hingedly coupled to the pylon along a second axis of rotation.
    [0003] The first axis of rotation and the second axis of rotation may be different axes. The first door of the outer sleeve and the first half of the inner fixed structure can be coupled to the pylon independently.
    [0004] The first door of the outer sleeve and the second door of the outer sleeve may both be distinct structures with respect to the first half of the inner fixed structure and the second half of the inner fixed structure. The first door of the outer sleeve, the second door of the outer sleeve, the first half of the internal fixed structure, the second half of the internal fixed structure can be at least partially retained by a single latch of the closure system. The first door of the outer sleeve may include a recess for at least partially enclosing a portion of a distal edge of the first half of the inner fixed structure.
    [0005] The first half of the inner fixed structure may include a flange configured to mate with a recess integrated in the first outer sleeve door. A seal may be coupled between the union of the first half of the inner fixed structure and the first door of the outer sleeve. A flame retardant seal may be coupled between the union of the first half of the internal fixed structure and the second half of the internal fixed structure.
    [0006] A sensor may be configured to indicate that the first door of the outer sleeve and the second door of the outer sleeve are retained in a closed position. An area of the first half of the inner fixed structure and a surface of the first door of the outer sleeve may be configured to cooperate to define between them a portion of a bypass duct. In addition, there is provided a system comprising a first door of the outer sleeve, a second door of the outer sleeve, a first half of the internal fixed structure and a second half of the internal fixed structure. The first half of the internal fixed structure can be configured for independent kinematic movement with respect to the kinematic movement of the first outer sleeve door. The second half of the internal fixed structure is configured for kinematic movement independent of the kinematic movement of the second outer sleeve door, and in response to the fact that the first outer sleeve door and the second outer sleeve door are locked. together, the kinematic movement of the first half of the inner fixed structure and the second half of the inner fixed structure is prevented.
    [0007] The first half of the internal fixed structure and the first door of the outer sleeve may be configured to cooperate to define between them a first portion of a bypass duct; and the second half of the internal fixed structure and the second door of the outer sleeve may be configured to cooperate to define between them a second portion of a bypass duct. The first door of the outer sleeve and the first half of the internal fixed structure, the second door of the outer sleeve and the second half of the inner fixed structure can be coupled to a tower each configured for independent kinematic movement. 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. FIGs. 1A-1B illustrate a typical propulsion system and its elements; FIGs. 2A-2B are a schematic illustration of a typical articulated opening of the thrust reverser; FIG. 3 illustrates a schematic sectional view of a fastening system of a fixed internal structure in accordance with the various embodiments; and FIG. 4 illustrates a schematic sectional view of the thrust reverser of FIG. 3 in an open position. 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 can be made. in accordance with this invention and the teachings therein. Thus, the detailed description given herein is presented for illustrative and non-limiting purposes only. The scope of disclosure is defined by the appended claims. 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, total, 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.
    [0008] 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.
    [0009] As illustrated in FIG. 1A and 1B, a typical commercial aircraft propulsion system includes a motor 140, a tower 110, and a pod assembly. The set of nacelles type, or just the nacelle, may include an inlet 120, a cover 125, a thrust reverser 130 and an exhaust system comprising an exhaust cone 145, and an exhaust nozzle 150. The nacelle surrounds the engine providing smooth aerodynamic surfaces around and within the engine. The nacelle also makes it possible to define a bypass air duct through the propulsion system. A fan sucks and directs a flow of air through and through the propulsion system. At the blower outlet, the air is divided into two main flow paths, one flow path through the engine core, and another flow path through the bypass air duct. The flow of air in the flow path of the engine core first passes through a compressor which increases the pressure, and then through a combustion chamber in which the compressed air is mixed with the fuel and alight. Combustion of the fuel and air mixture causes a series of turbine blades to rotate at the rear of the engine core which in turn drives the compressor and the engine fan. The high pressure exhaust gases from combustion of the fuel and air mixture are then directed through an exhaust nozzle at the rear of the engine for high speed thrust. The air in the bypass flow path is compressed by the fan and then oriented around the engine core in a conduit or conduits defined by the nacelle. The bypass air exits the duct through a nozzle at the rear of the propulsion system to provide thrust. In turboprop systems, the bypass flow generally provides a large part of the thrust. If the nacelle includes a typical thrust reverser, the thrust reverser selectively prevents the derivative air in the derived air duct from reaching the nozzle, and instead redirects the derived air out of the duct in a forward direction. the aircraft to generate a reverse thrust.
    [0010] The thrust reverser 130 is generally articulated to a pylon 110 at one or more joints. This articulated type attachment and the relative hinged movement are illustrated in FIGS. 2A-2B. The thrust reverser 130 generally comprises a fixed internal structure (SIF) 137 and an outer sleeve 132 which cooperate to define between the bypass duct. Traditionally, outer sleeve 132 and SIF 137 rotate in unison (as a single element). An outer surface of the outer sleeve 132 is part of the aerodynamic outer surface of the nacelle. An inner surface of the outer sleeve 132, with the outer surface of the SIF, partially defines the bypass duct. A typical thrust reverser can be constructed in two halves, with an outer sleeve 132 on the right and a right SIF on the right, and an outer sleeve on the left 132 and a left SIF on the other half. The left half and right half of the thrust reverser are locked together when the thrust reverser is closed. In a typical arrangement, the right half of the SIF is attached or attached to the right half of the outer sleeve 132 with fasteners, and similarly the left half of the SIF is attached to or attached to the left half of the outer sleeve. 132 with fasteners, and each assembly is independently hinged to a support structure such as a pylon. When each half of the thrust reverser is closed, the right half and the left half of the SIF cooperate to form a chamber around the engine core. According to various embodiments and with reference to FIG. 3, the halves of the fixed inner structure 432, 437 (SIF) and the outer sleeve halves 460, 465 may be separately hinged or attached to the support structure so that the movement of the halves of the fixed inner structure 432, 437 (SIF) may be independent of the movement of the halves of the outer sleeve 460, 465. For example, half of the fixed internal structure 432 and half of the outer sleeve 465 may be hinged separately to different parts and / or locations of the pylon with coaxial or non-coaxial hinge pins. Or, half of the SIF 432 may be hinged to the half of the outer sleeve 465, half of the outer sleeve 435 being in turn articulated to the pylon or other support structure. In addition, at least one of the outer sleeve halves 460, 465 and halves of the fixed inner structure 432, 437 may be configured to slide in a forward and backward direction while at least 1 one of the halves of the outer sleeve 460, 465 and the halves of the inner fixed structure 432, 437 may be configured to pivot about an axis.
    [0011] According to various embodiments and again with reference to FIG. 3, a closure system 200 in which a latch can be used to hold the two halves of the SIF 432, 437 and to obtain the halves of the outer sleeve 460, 465 is revealed. The closure system 200 may comprise one or more latches, for example three nacelle closures, (e.g., at distinctly different locations axially along the lower edge of the sleeve), which retain each of the separately articulated SIF halves 432 437 and halves of the outer sleeve 460, 465. For example, the lower edges of the SIF halves 432, 437 may include one or more structures configured to mate and / or to be picked up by receptacles, e.g. beam-type receptacles, outer sleeve 460, 465.
    [0012] A single latch of the closure system 200 can then be used to lock the panels (eg, the two halves of SIF 432, 437 and the two halves of the outer sleeve 460, 465) together and / or in a close position and detention. Joints can be placed between the component interfaces. Rails 450, 455 may traverse a portion or the entire axial length of the outer sleeve halves 460, 465. Similarly, flanges 435, 430 may traverse a portion or the entire axial length of SIF halves 432, 437. The rails 450, 455 may be of any suitable form. The rails 450, 455 may be integrated with the halves of the outer sleeve 460, 465, or they may be coupled to the halves of the outer sleeve 460, 465. The flanges 435, 430 may be of any suitable shape. The flanges 435, 430 may be integrated with the halves of SIF 432, 437, or they may be coupled to the halves of SIF 432, 437. Even though the flanges 435, 430 are illustrated as extending into a recess, (e.g. , rail 450, 455) formed in the doors of the outer sleeve 460, 465, it is contemplated herein that the halves of the outer sleeve 460, 465 may include a member extending into a recess formed in a distal end of the SIF halves. 432, 437. In operation, the two halves of the SIF 432, 437 can be oriented in a closed position so that the two halves of the SIF 432, 437 are substantially adjacent and the two halves of the outer sleeve 460, 465 can be closed around the two halves of SIF 432, 437 and in particular around the flanges 435, 430. Two doors of the outer sleeve 460, 465, at least partially encapsulating the flange 435, 430, can be held in place. The closure system 200 may be any one of a closed closure system for locking two surfaces together. Two surfaces together may be called "very close" as shown by location 445 in FIG. 3. Seals may be placed as desired in the system 200. For example, seals 446, 456 may be located at or near the union of the rail 455 and the flange 435 and / or at the the union of the rail 450 and the flange 430. Seals 446, 456 can be configured as an aerodynamic seal and / or performance. The system 200 is designed for slamming, friction and premature wear of the closure system 200 not to occur. Seals 446, 456 can reduce this wear and / or exist for deflection purposes. Put differently, the seal 446, 456 can reduce metal to metal contact, friction and / or vibration. A flame retardant seal 440 may be placed in any location in the system 200. For example, a fire zone may be maintained with a flame retardant seal 440 located toward the distal end and coupling the halves of the SIF 432, 437. Thus, the SIF of the system 200 represents a flame retardant barrier for the rest of the nacelle. Put otherwise, the fire zone, which can be considered as the core of the engine and the area surrounding the engine core, is insulated by a flame retardant seal 440. The closure system may comprise a latch 410 held in a lock housing 420 which is attached to the outer sleeve door 465. On the adjacent door of the outer sleeve 460, a latch 415 is secured in the latch housing 416 to engage the latch 410 to close the closure system 200. Each housing 420 416 may be permanently and / or integrally attached to the respective door of the outer sleeve 465, 460.
    [0013] The closure system 200 that functions as described above to keep the two halves of the SIF closed and the outer sleeve halves is lighter than a set of closures that hold closed only the halves of the SIF and a set separate closures that keep closed only the halves of the outer sleeve. The halves of the SIF can be picked up by the closed halves of the outer sleeve. Put differently, in response to their capture, the SIF halves can not open as the closed halves of the outer sleeve interfere with the kinematic operation of the SIF halves. The term "kinematic" may include radial, rotational and axial movement. But also, the SIF halves can be captured in such a way that they remain restricted during a pneumatic duct rupture event, thus preventing engine failure from spreading to the rest of the aircraft. FIGs. 3 and 4 illustrate sectional views of examples of outer sleeve doors 465, 460 in closed and open positions, respectively. In the closed position, latch 410 and latch 415 would be firmly engaged while in the open position latch 410 and latch 415 are disengaged (as shown in FIG 4). In response to the closure system 200 being in the closed position, a handle coupled to the latch 410 is housed in a depression (not shown) formed in the doors of the outer sleeve 465 so that an airfoil is formed. The latch 410 and the latch 415 may be any suitable latch and latch for the lens and will operate in a manner known to those skilled in the art. When properly loaded and locked in the closed position, the closure system 200 is configured to hold the doors of the outer sleeve 460, 465 in a closed orientation. The handle can be identified by a visual indicator such as, a red paint, for better visibility so that when it is moved away from the latch 415, the handle is hung down below the nacelle of the motor 470 to allow indication. since the closure system 200 is in the open position.
    [0014] Sensors, such as a strain gauge 457 shown in FIG. 4, may be coupled to the system to indicate at least one of the outer sleeve doors 465, 460 are touching and / or in the locked position, the closure system 200 is closed, the closure system 200 is open , and / or that the two halves of SIF 432, 437 are touching, for example at the damper 450. The sensors can be configured to capture the conductivity, the power level, the stress, the temperature, the pressure , the torsion as well as other sensors of the conditions or characteristics of a closure system 200 and / or structures 432, 437, 465, 460. These sensors can at least transmit by cable or wireless an indication to the least one pilot, cockpit, maintenance personnel at a receiver and / or a screen.
    [0015] Systems, methods and apparatus are described herein. In the detailed description given herein, references to the terms "an embodiment", "an embodiment", "various embodiments", etc., indicate that the described embodiment may include a property, structure or feature particular, 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) on how to implement the disclosure in alternative embodiments. Furthermore, no element, component or process step of the present disclosure is intended for the public regardless of whether the element, component or process step is explicitly described in the claims. Nothing claimed here shall be construed in accordance with the provisions of 35 USC 112 (0 unless the element is implicitly indicated with the phrase "means for." As used herein, the terms "includes", "comprising Or any other variation thereof, are intended to cover a non-exclusive inclusion, so that a method, method, article, or apparatus that includes a list of elements does not include not only these elements but may include other elements that are not implicitly listed or inherent in such a method, method, article or apparatus.
    [0016] 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. 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. Similarly, the scope of the inventions should be limited only by the appended claims, in which the reference to an element in the singular does not mean "one and only one" except in the case of precision of this, but rather "one or more ". In addition, when a phrase such as "at least one of A, B or C" is used in the claims, it is contemplated that the sentence be interpreted to have the meaning that A alone may be present in a realization, 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; for example, A and B, A and C, B and C or A and B and C. Different hatches are used in the figures to indicate different parts but not necessarily to indicate the same material or different materials. 11
    权利要求:
    Claims (4)
    [0001]
    REVENDICATIONS1. A closure system (200) configured for a thrust reverser of an engine nacelle comprising: a first outer sleeve gate (465) and a second outer sleeve gate (460) each mounted for movement between an open position of an outer sleeve holder and a closed position of an outer sleeve holder; a first half of the inner fixed structure (432) and a second half of the inner fixed structure (437) each removably mounted between an open position and a closed position, the first half of the inner fixed structure (432) and the second half of the internal fixed structure (437) being configured for kinematic movement independent of the kinematic movement independent of the first door of the outer sleeve (465) and the second door of the outer sleeve (460), and wherein in response to the fact the first door of the outer sleeve (465) and the second door of the outer sleeve (460) being in the closed position, the first half of the inner fixed structure (432) and the second half of the inner fixed structure (437) are held so that the kinematic movement between the open position and the closed position of the first half of the inner fixed structure (432) and the second half of the internal fixed structure (437) is prevented.
    [0002]
    2. Closure system according to claim 1, also comprising a pylon (110), wherein the first half of the inner fixed structure (432) and the second half of the inner fixed structure (437) are hingedly coupled to the pylon (110) along a first axis of rotation, and wherein the first gate of the outer sleeve (465) and the second gate of the outer sleeve (460) are hingedly coupled to the pylon (110) along an second axis of rotation.
    [0003]
    3. Closure system according to claim 2, wherein the first axis of rotation and the second axis of rotation are different axes.
    [0004]
    A closure system according to claim 2 or claim 3, wherein the first door of the outer sleeve (465) and the first half of the inner fixed structure (432) are coupled to the pylon (110) independently. The closure system of any one of the preceding claims, wherein the first outer sleeve door (465) and the second outer sleeve door (460) are both separate structures from the first half of the internal fixed structure (432) and the second half of the internal fixed structure (437). Closure system according to one of the preceding claims, wherein the first door of the outer sleeve (465), the second door of the outer sleeve (460), the first half of the internal fixed structure (432), the second half of the internal fixed structure (437) are at least partially retained by a single latch (410) of the closure system (200). A closure system as claimed in any one of the preceding claims, wherein the first door of the outer sleeve (465) comprises a recess (455) for at least partially enclosing a portion of a distal edge of the first half of the structure internal fixed (432). The closure system of claim 7, wherein the first half of the inner fixed structure (432) comprises a flange (435) configured to mate with a recess (455) integral with the first outer sleeve door (465). ). The closure system of claim 7 or claim 8, wherein a seal (446) is coupled between the union of the first half of the inner fixed structure (432) and the first door of the outer sleeve (465). A closure system according to any one of the preceding claims, wherein a flame retardant seal (440) is coupled between the union of the first half of the inner fixed structure (432) and the second half of the inner fixed structure ( 437). The closure system of any preceding claim, wherein a sensor (457) is configured to indicate that the first door of the outer sleeve (465) and the second door of the outer sleeve (460) are held in a position closed. The closure system of any preceding claim, wherein a surface of the first half of the inner fixed structure (432) and a surface of the first gate of the outer sleeve (465) are configured to cooperate to define between them a portion of a bypass duct. A system (200) comprising: a first gate of the outer sleeve (465); a second door of the outer sleeve (460); a first half of the internal fixed structure (432); and a second half of the internal fixed structure (437), wherein the first half of the inner fixed structure (432) is configured for independent kinematic movement with respect to the kinematic movement of the first gate of the outer sleeve (465); wherein the second half of the inner fixed structure (437) is configured for kinematic movement independent of kinematic movement of the second outer sleeve door (460), and wherein in response to the first outer sleeve door (465) and the second door of the outer sleeve (460) are locked together, the kinematic movement of the first half of the inner fixed structure (432) and the second half of the inner fixed structure (437) is prevented. The system of claim 13, wherein the first half of the inner fixed structure (432) and the first gate of the outer sleeve (465) are configured to cooperate to define between them a first portion of a bypass conduit; and wherein the second half of the internal fixed structure (437) and the second gate of the outer sleeve (460) are configured to cooperate to define between them a second portion of a bypass conduit. The system of claim 13 or claim 14, wherein the first outer sleeve door (465) and the first half of the inner fixed structure (432), the second outer sleeve door (460) and the second half of the internal fixed structure (437) is coupled to a pylon (110) each configured for independent kinematic movement. 14
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20150143796A1|2015-05-28|
    FR3013682B1|2020-10-02|
    US9366202B2|2016-06-14|
    引用文献:
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    法律状态:
    2015-10-23| PLFP| Fee payment|Year of fee payment: 2 |
    2016-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 6 |
    2019-12-06| PLSC| Publication of the preliminary search report|Effective date: 20191206 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/092,372|US9366202B2|2013-11-27|2013-11-27|System and method for captured inner fixed structure|
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