• 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 thrust reverser (40) of a turbofan engine (20) includes a translation structure (52) and an inverter flap device (62) capable of diverting a bypass flow path (34) and a reverse a direction of propulsion. The translation structure (52) moves axially between a forward position and a rear position and thereby causes a composite motion of an inverting flap (64) of the inverter flap device (62) which moves between a respective folded state and a deployed state. The composite motion is attributable to the inverter flap (64) pivotally engaged on the translation structure (52), and to a multi-arm linkage (66) of the device (62) which is pivotally engaged between a stationary structure ( 60), the inverter flap (64) and the translation structure (52). The linkage (66) is further oriented so as not to substantially obstruct the bypass flow path (34) when the inverter flap (64) is in the folded state.
    公开号:FR3018864A1
    申请号:FR1552321
    申请日:2015-03-20
    公开日:2015-09-25
    发明作者:Timothy Gormley
    申请人:Rohr Inc；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present disclosure relates to a thrust reverser for a turbofan engine and, more particularly, to a hidden thrust reverser device of the thrust reverser. Dual flow turbofan engines are known to include a blower section which produces a bypass air flow to provide most of the engine propulsion and a combustion or core air flow for compression, mixed with the fuel. , combustion and expansion via a turbine to drive the blower section. The engines further include pods that partially surround the engine core, include a mast for securing the engine to a structure such as an aircraft wing, and provide an annular bypass air flow duct allowing direct the bypass airflow in a backward direction to produce a forward propulsion. The nacelles may further include thrust reversers capable of redirecting the bypass airflow from the rearward direction to at least partially a forward direction thereby providing rearward propulsion. By way of example, such rearward propulsion can serve to decelerate the forward motion of an aircraft as soon as after landing. The thrust reversers may include a plurality of reversing flaps physically capable of changing positions through mechanical and hydraulic linkages from a stowed position for forward propulsion and to an extended position for rearward propulsion. There is a need to improve such linkages and reduce linkage obstruction in the bypass airflow duct. FOLLOWED An inverter flap device according to a non-limiting embodiment of the present invention includes an inverting flap; a first arm pivotally connected to the reversing shutter; a second arm pivotally connected to the first arm; and a third arm pivotally connected to the second arm. In addition to the foregoing embodiment, the reversing shutter device includes a pivot coupling engaged to the reversing shutter; a first joint spaced from the pivot connection and connecting the inverter flap and the first arm; a second joint spaced from the first joint along the first arm and connecting the first and second arms; and a third hinge engaged on the second arm and spaced from the second hinge along the second arm.
    [0002] Alternatively or in addition thereto, in the foregoing embodiment, the inverter flap device includes a fourth hinge engaged on the third arm; and a fifth joint spaced apart from the fourth joint along the third arm and connecting the third arm to the second arm. As a variant or in addition to this, in the previous embodiment, the fifth articulation is close to the second articulation. Alternatively or in addition to this, in the previous embodiment, the fifth joint is located between the third joint and the second joint along the second arm. Alternatively or in addition thereto, in the foregoing embodiment, the joints are constructed and arranged to pivot about respective axes which are substantially parallel to each other. Alternatively or in addition thereto, in the foregoing embodiment, the inverting flap has a collapsed state, a transient state and an expanded state, and the third hinge is constructed and arranged to reverse its direction of rotation generally to the state transient and as the inverting flap moves between folded and deployed states. Alternatively or in addition to this, in the previous embodiment, the third arm protrudes into the reversing shutter. A thrust reverser according to another non-limiting embodiment includes a fixed structure; a translation structure constructed and arranged to move between a first position and a second position; and an inverting flap device having an inverting flap pivotally connected to the translation structure and constructed and arranged to move between a folded state and an expanded state, and a multi-link linkage pivotally engaged on the inverting flap, the structure fixed and the translation structure for positioning the reversing flap in the folded state when the translation structure is in the first position, and in the deployed state when the translation structure is in the second position. In addition to the foregoing embodiment, the thrust reverser includes a gate arrangement engaged to the fixed structure and for diverting a bypass flow path defined in part by the inverting flap, and when the inverting flap is in deployed state. Alternatively or in addition to this, in the previous embodiment, the translation structure is substantially cylindrical and concentric with an axis, and the inverter flap device is one of a plurality of circumferentially distributed inverter flap devices. around the axis. Alternatively or additionally, in the foregoing embodiment, the translation structure moves axially between the first and second positions. Alternatively or in addition thereto, in the foregoing embodiment, the thrust reverser includes a pivot connection engaged between a front end portion of the translation structure and a base edge portion of the inverter flap; and the inverting flap extends from the base edge portion and toward an opposite distal edge of the inverting flap, and extends substantially axially when in the collapsed state and at least partially radially when in the deployed state. Alternatively or in addition thereto, in the foregoing embodiment, the multi-link linkage does not obstruct a bypass flow path defined in part by the inverter flap when in the folded state. Alternatively or in addition thereto, in the foregoing embodiment, the reversing shutter has a composite motion and pivots about the pivot joint as it moves between the folded and deployed states and the translational structure moves axially between them. first and second positions. The above features and elements may be combined in various non-exclusive combinations, unless expressly stated otherwise. These features and elements and their operation will become apparent in light of the following description and the accompanying drawings. It should be understood, however, that the following description and figures are intended to be exemplary and not limiting in nature. BRIEF DESCRIPTION OF THE DRAWINGS Various features will be apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiments. The drawings accompanying the detailed description may be briefly described as follows: FIG. 1 is a perspective view of a turbofan engine according to a non-limiting embodiment of the present disclosure; Figure 2 is an exploded view of the turbofan engine; Fig. 3 is a partial sectional view of a thrust reverser with an inverting flap in a folded state and taken along the line 3-3 of Fig. 1; Figure 4 is a partial sectional view of the thrust reverser similar to Figure 3 but with the inverter flap removed to show internal details; Figure 5 is a partial sectional view of the thrust reverser moving to a deployed state from the folded state; Figure 6 is a partial sectional view of the thrust reverser in a transient state and moving further to the deployed state; Figure 7 is a partial sectional view of the thrust reverser moving further to the deployed state; Figure 8 is a partial sectional view of the thrust reverser in an expanded state; and Fig. 9 is a partial perspective view of the thrust reverser in the deployed state.
    [0003] DETAILED DESCRIPTION Referring to FIGS. 1 and 2, a turbojet engine 20 is centered about an axis 22 and includes a nacelle 24 which supports and generally surrounds an internal engine core which includes a fan section 26, a compressor section 28, a combustion chamber section 30 and a turbine section 32. The blower section 26 draws air along a flow path or bypass duct 34. Part of the air from the blower section 26 enters the motor core flow path (not shown) for compression by the compressor section 28, then into the combustion chamber section 30. The core air is mixed with the fuel in the combustion chamber section 30 and Burned, producing energy. The core or exhaust air from the combustion chamber section 30 is expanded through the turbine section 32 and, in turn, drives a central shaft (not shown) which propels the blower section 26. The air flow The burned core generally propels the blower section 26 and the bypass airflow provides most of the forward propulsion to the engine 20. More conventional turbofan engines can have a flow ratio. Bypass air flow (ie bypass ratio) of about six (6: 1). More recent high bypass ratio engines, such as a reducer turbojet, may have larger shunt ratios and may exceed ten (10: 1).
    [0004] The nacelle 24 may include an intake cowl 36 disposed in front of the fan section 26, a fan cowl 38 circumferentially surrounding and shielding the fan section 26, a thrust reverser 40 which can circumferentially surround the compressor sections, combustion chamber and turbine 28, 30, 32, and a central exhaust core 42 at the rear of the turbine section 32, an exhaust nozzle 44 which is spaced radially outwardly of the central exhaust core 42 and a mast 46 which supports the engine 20 typically to a landing gear of an aircraft wing (not shown). Referring to FIGS. 2 to 4, the thrust reverser 40 generally has an inner shell 48 (see FIG. 6) and an outer translation shell 50 spaced radially outwardly of the inner shell 48. bypass flow 34 is defined by and located radially between the inner and outer shells 48, 50; can be generally ring-shaped; and may be located immediately downstream of the blower section 26. The outer shell 50 may have a forward section or a translational structure 52 and a rear section 54, both of which are generally cylindrical and concentric with the motor shaft 22. The rear section 54 can translate with the translation structure 52, or in some examples, can be stationary and stationary with respect to the inner shell 48 and / or the mast 46. The translation structure 52 can include a pressure sleeve 56 and an outer housing 58 generally spaced radially outwardly of the pressure sleeve 56. The pressure sleeve 56 axially spans the portion between a stationary structure fan housing 60 and a stationary rear grid ring 59 of the structure During a normal forward propulsion of, for example, aircraft Similarly, the outer casing 58 axially spans the rearward portion of the hood 38. The pressure sleeve 56 and the outer casing 58 both axially span the rearward portion 25 and join to each other at a point which is located substantially at the rear of the ring. rear grille 59. Namely, a section of the translation structure 52 resembles a horseshoe which is open in the forward direction relative to a forward propulsion of the engine 20. A plurality of flap devices Inverter 62 of the thrust reverser 40 is distributed circumferentially about the axis 22. Each device 62 has an inverting flap 64 which is generally located radially inwardly of the pressure sleeve 56 of the translation structure 52 and spans axially the portion from the fan housing 60 to the rear section 54 of the outer ring 50 and the rear gate ring 59 during a forward propulsion of the motor 20. The inverter flap 64 and the trailing structure Both are able to move concomitantly with the stationary gate ring 59, which redirects the bypass airflow into the bypass flow path 34 which can generally change the aircraft power. between forward propulsion and reverse propulsion. Each inverter flap device 62 may further include a multi-link linkage 66 capable of providing flap stability and guiding the movement of the inverter flap 64 between a folded state 68 (see Figures 3 and 4) for propulsion. forward aircraft and a deployed state 70 (see Figures 8 and 9) for reverse or aft aircraft propulsion. The translational structure 52 of the outer shell 50 is substantially driven in an axial direction (see arrow 72), between a forward position 74 (see Fig. 3), placing the inverter flap 64 in the folded state 68 , and a rear position 76 (see FIG. 8) placing the reversing shutter 64 in the deployed state 70. When in the forward position 74, the translational structure 52 may be substantially axially aligned with, and radially located towards the outside of the folded inverting shutter 64. When in the rear position 76, the translational structure 52 may be substantially axially rearward (that is to say at the rear) of the reversing shutter 64 and the gate ring 59, and located substantially radially outwardly of the inverting flap 64. At least one master actuator 78 of the thrust reverser 40 (see Figure 3) causes the axial movement of the translation structure 52 and may (as non-limiting examples) be operated hydraulically or electrically or a combination of both. The actuator 78 may include a drive unit rigidly attached to the blower housing 60 and a hydraulic arm connected to the translation structure 52 and capable of being extended and retracted from the drive unit. The actuator 78 may be described as a "master" and the linkage 66 may be described as a "slave linkage" in the sense that the actuation of the linkage 66 is directly dependent on the driven movement of the translation structure 52. linear movement of the structure 52, the linkage 66 can not move. Referring to FIGS. 3 and 8, the inverting flap 64 has a concave exposed surface 80 which partially defines the bypass flow path 34 and an opposed surface 82 which is radially outwardly facing towards the sleeve when the inverter flap 64 is in the folded state 68. When in the deployed state 70, the surface 82 of the inverter flap 64 may be facing in a substantially axial downstream direction. The inverting flap 64 further includes and extends between a base or edge portion 84 attached to a front end of the pressure sleeve 56 of the translation structure 52 by a pivot connection 86, and an opposing distal edge 88. When it is in the folded state 68, the edge portion 84 may be near a rear edge of the blower housing 60 and the distal edge 88 may be near a leading edge of the rear section 54 of the outer shell 50. Similarly, and when in the folded state 68, a leading edge of the pressure sleeve 56 can be releasably sealed to the rearward edge of the blower housing 60; and a front edge of the outer housing 58 of the translation structure 52 is near an edge or a rearward portion of the fan cowl 38. When in the deployed state 70, the inverter 64 extends substantially radially, the edge portion 84 of the flap 64 remains pivotally engaged on the pressure sleeve 56, and the distal edge 88 can be moved to a position closer to the motor shaft 22. Referring 3 to 5 and 8, the inverter flap 64 is capable of a "composite movement" which includes: 1) a linear movement attributable to the flap 64 directly engaged on the translation structure 52 and 2) a rotational or pivoting attributable to the rotational capability of the pivot connection 86 and the multi-link linkage 66. In addition, the inverter flap device 62 may contain a "vacuum displacement" device in the sense that the translation structure 52 can move a distance to xiale relatively short rearward when initially away from the position before and before the reversing flap 64 begins to rotate and leave the folded state. This empty motion is enabled by the configuration of the linkage 66. The linkage 66 may also include first, second and third arms 90, 92, 94 with first, second, third, fourth and fifth pivot joints 96, 98, 100, 102, 104 associated. Each hinge 96, 98, 100, 102, 104 and the pivot connection 86 have respective axes of rotation 106 which are substantially parallel to each other. A first end of the first arm 90 is engaged on the inverter flap 64 by the hinge 96 and an opposite second end of the first arm 90 is engaged on one end of the second arm 92 by the second hinge 98. A second, opposite end of the second arm arm 92 is engaged on the fan housing 60 (or stationary structure engaged rigidly thereto) by the third hinge 100. One end of the third arm 94 is engaged on the translation structure 52 by the fourth hinge 102 and an opposite end of the hinge third arm 94 is engaged on the second arm 92 by the fifth hinge 104. The fourth hinge 102 is spaced axially downstream of the pivot connection 86, and the fifth hinge 104 is located between the second and third hinges 98, 100, and may be closer to and slightly spaced from the second 98 joint. Referring to 9, the inverting flap 64 may comprise a channel 108 which extends longitudinally between the edge portion 84 and the distal edge 88, and a slot 110 of the same extent which communicates via the flap 64. The slot 110 can communicate through the base or edge portion 88 and extends longitudinally to, but without substantially reaching, the distal edge 88 or the location of the first hinge 96. The third arm 94 extends across the slot 110 and is located near the edge portion 84 when the inverter flap 64 is in the deployed state 70, and is generally located at an opposite end of the slot near the first hinge 96 when the inverter flap 64 is in the folded state 68 (see Figures 3 and 4). The channel 108 is defined by the exposed surface 80 and extends from the distal end of the slot 110 and further toward the distal edge 88, but without reaching it. The first hinge 96 may be in the channel 108, and the combined length of the channel 108 and the slot 110 may be limited to about the length of the second arm 92. With the inverter flap 64 in the folded state 68, the channel 108 and the slot 110 serve to store the first and second arms 90, 92 and a substantial portion of the third arm 94; thus, substantially reducing or eliminating any obstruction in the bypass flow path 34. That is, no substantial portion of the multi-link linkage 66 extends through or otherwise obstructs the bypass air flow, thus the efficiency of the air flow is not reduced during normal flight operating conditions and the noise is minimized. To further enhance this storage capacity, the third arm 94 may be in the form of a "tuning fork" so that the second arm 92 can bend into the third arm 94. Similarly, the second arm may be in the form of a "tuning fork" So that the first arm 90 can bend into the second arm 92 when in the folded state 68. In operation and during normal flight conditions, the thrust reverser 40 is not deployed and the inverting flaps 64 of the inverter flap device 62 are in the folded state 68 (see FIG. 3) thus partially defining the non-bypassed bypass flow path 34. During this folded state 68, there is has no inverter shutter linkages traversing the bypass flow path 34, which optimizes the flow efficiency when the bypass air flows the flow path in a backward direction, contributing to a propulsion flow. ion to the front of the aircraft.
    [0005] During certain flight scenarios, such as landing, and when it is desired to reduce the speed of the aircraft forward, the thrust reverser 40 may be triggered. The master actuator 78 can then push the translational structure 52 in the backward direction 72. As the translational structure 52 moves backward, a clearance 114 (see Fig. 7) begins to move. open between a forward end of the structure 52 and the rearward combined edges of the blower hood 38 and the blower housing 60. In addition, and since the inverter flaps 64 are attached to the pressure sleeve 56 of the translational structure 52, the deflection 114 also expands between the forward edge portion 84 of the inverter flaps 64 and the rearward edge of the blower housing 60. As the travel 114 widens a grid arrangement or at least one rotating blade 116, once stored between the pressure sleeve 56 and the outer casing 58 of the translation structure 52, is becoming more and more operative to further rotate the flow of derivation of e air (see arrow 118) in at least one direction partially forward (see arrow 120). The arrangement 116 may span the portion between the blower housing 60 and the rear gate ring 59, and may be rigidly attached to one or both. During a triggering of the thrust reverser, the inverting flaps 64 also begin to pivot at the pivot connection 86 engaged between the edge portion 84 and a front end of the thrust sleeve 56. This pivoting movement is maintained by the linkage. 66 as the second arm 92 of the linkage begins to rotate and turn clockwise (see arrow 112 in Fig. 5) at the third hinge 100 secured to the stationary structure or fan housing 60. As the inverting flap 64 continues to expand and open, the inverter flap device 62 achieves a transient state 122 (see FIG. 6) generally located between the folded and deployed states 68, 70. In this state transient 122, the second arm 92 begins to reverse the direction of rotation at the third hinge 100 and begins to rotate in a counterclockwise direction (see arrow 124 on Figure 7). Referring to FIGS. 8 and 9, and when fully deployed, the bypass flow path 34 is substantially or completely diverted through gate arrangement 116 (see FIG. 7). Each inverting flap 64 has moved an axial distance substantially equal to the fully extended deflection 114 which may be about the length of the reversing flap 64, and has also pivoted about the pivot connection 86 in a clockwise direction and about ninety degrees. When in the fully deployed state 70, the distal edge 88 of each inverter pane 64 may be proximate to the inner shell 48 and the linkage 66 may generally traverse the diverted bypass flow path. It should be understood that the relative position terms such as "forward", "backwards", "superior", "lower", "above", "below" and the like are references to the normal operational base and should not otherwise be considered as limiting. It should also be understood that like reference numerals identify corresponding or similar elements throughout the various drawings. It should be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will also benefit. While particular step sequences may be shown and described, it should be understood that the steps can be performed in any order, separated or combined unless otherwise indicated and will always benefit from the present disclosure. The foregoing description is given by way of example rather than defined by the limitations described. Various non-limiting embodiments are disclosed; however, one of ordinary skill in the art will recognize that various modifications and variations in light of the foregoing teachings will fall within the scope of the invention described above. It is thus understood that within the scope of the appended claims, the disclosure may be put into practice other than what is specifically described. For this reason, the appended claims should be studied to determine the actual scope and content.
    权利要求:
    Claims (15)
    [0001]
    CLAIMS: 1. Inverter shutter device (62) comprising: an inverting flap (64); a first arm (90) pivotally connected to the inverter flap (64); a second arm (92) pivotally connected to the first arm (90); and a third arm (94) pivotally connected to the second arm (92).
    [0002]
    An inverting shutter device according to claim 1, further comprising: a pivot connection (86) engaged to the inverting shutter (64); a first hinge (96) spaced from the pivot fitting (86) and connecting the inverter flap (64) and the first arm (90); a second hinge (98) spaced from the first hinge (96) along the first arm (90) and connecting the first and second arms (90, 92); and a third hinge (100) engaged on the second arm (92) and spaced apart from the second hinge (98) along the second arm (92).
    [0003]
    An inverting shutter device according to claim 2, further comprising: a fourth hinge (102) engaged to the third arm (94); and a fifth hinge (104) spaced from the fourth hinge (102) along the third arm (94) and connecting the third arm (94) to the second arm (92).
    [0004]
    4. Inverter shutter device according to claim 3, wherein the fifth articulation (104) is close to the second articulation (98).
    [0005]
    An inverting shutter device according to claim 3 or 4, wherein the fifth hinge (104) is located between the third hinge (100) and the second hinge (98) along the second arm (92).
    [0006]
    Inverter flap device according to any one of claims 2 to 5, wherein the joints (96, 98, 100, 102, 104) are constructed and arranged to pivot about respective axes (106) which are substantially parallel. each other.
    [0007]
    An inverting shutter device according to any one of claims 2 to 6, wherein the inverting shutter (64) has a folded state, a transient state and an expanded state, and the third articulation (100) is constructed and arranged to invert its direction of rotation generally in the transient state and as the inverting flap (64) moves between the folded and deployed states.
    [0008]
    8. Inverter shutter device according to any one of the preceding claims, wherein the third arm (100) protrudes into the inverter shutter (64).
    [0009]
    A thrust reverser (40) comprising: a fixed structure (60); a translation structure (52) constructed and arranged to move between a first position and a second position; and an inverting flap device (62) according to any one of the preceding claims wherein the inverting flap (64) is pivotally connected to the translation structure (52) and constructed and arranged to move between a collapsed state and a deployed state, and a multi-link linkage (66) pivotally engaged to the inverting flap (64), the fixed structure (60) and the translation structure (52) to position the inverting flap (64) in the folded state when the translation structure (52) is in the first position, and in the expanded state when the translation structure (52) is in the second position.
    [0010]
    The thrust reverser of claim 9, further comprising: a gate arrangement (116) engaged to the fixed structure (60) and for diverting a bypass flow path (34) defined in part by the inverter flap (64), and when the inverting flap (64) is in the deployed state.
    [0011]
    The thrust reverser of claim 9 or 10, wherein the translation structure (54) is substantially cylindrical and concentric with an axis (22), and the inverter flap device (62) is one of a plurality inverter flap devices (62) distributed circumferentially about the axis (22).
    [0012]
    A thrust reverser according to claim 9, 10 or 11, wherein the translation structure (52) moves axially between the first and second positions.
    [0013]
    A thrust reverser according to any one of claims 9 to 12, further comprising: a pivot connection (86) engaged between a front end portion of the translation structure (52) and a base edge portion ( 84) of the reversing shutter (64); and wherein the inverting flap (64) extends from the base edge portion (84) and toward an opposite distal edge (88) of the inverting flap (64), and extends substantially axially when in the folded state and at least partially radially when in the deployed state.
    [0014]
    A thrust reverser according to claim 13, wherein the inverting flap (64) has a composite motion and pivots about the pivot fitting (86) as it moves between the folded and deployed states and the translational structure (52). moves axially between the first and second positions.
    [0015]
    A thrust reverser according to any one of claims 9 to 14, wherein the multi-link linkage (66) does not obstruct a bypass flow path (34) defined in part by the inverter flap (64). when in the folded state.
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    同族专利:
    公开号 | 公开日
    US20150267640A1|2015-09-24|
    US9938929B2|2018-04-10|
    FR3018864B1|2018-04-27|
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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 |
    2017-04-07| PLSC| Publication of the preliminary search report|Effective date: 20170407 |
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    US14/222,134|US9938929B2|2014-03-21|2014-03-21|Thrust reverser for a turbofan engine|
    US14222134|2014-03-21|
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