• 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) having a translation structure (52) and an inverter flap device (62) capable of deflecting a bypass flow path (34) is disclosed. ) to reverse the direction of propulsion. The translation structure (52) moves axially between a forward position and a rearward position and thereby causes a movement composed of an inverter flap (64) of the inverter flap device (62). which moves between the respective states stored and unfolded. A passive linkage (67) of the reversing shutter device (62) is oriented between a fixed structure (55) and the reversing shutter (64) and may be used in combination with an extensible linkage (66) which can be oriented between the shutter inverter (64) and the fixed structure (55).
    公开号:FR3018865A1
    申请号:FR1552324
    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] The present description relates to a thrust reverser for a turbofan engine, and more particularly to an inverter flap device of the thrust reverser. Dual flow turbofan engines are known to include a fan section that produces a bypass airflow to provide the majority of engine propulsion and a combustion or core airflow for compression, fuel mixture, combustion and expansion through a turbine to drive the fan section. The engines further include nacelles that partially surround the engine core, include a tower for attaching the engine to a structure such as an aircraft wing, and provide an annular bypass airflow to direct the flow of the engine. Bypass air 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 toward at least partially a forward direction, thereby providing rearward propulsion. By way of example, such rearward propulsion can be used to decelerate the forward motion of an aircraft shortly after landing. The thrust reversers may include a plurality of reversing flaps physically capable of changing position by mechanical and hydraulic linkages from a stowed position for forward propulsion and an extended position for rearward propulsion. There is a need to improve such linkages and to reduce the clogging of the linkage in the bypass airflow duct. SUMMARY A thrust reverser according to a non-limiting embodiment of the present description comprises a translation structure constructed and arranged to move between first and second positions; an inverting flap pivotally engaged to the translation structure for pivotal movement between a first state when the translation structure is in the first position and a second state when the translation structure is in the second position; a fixed structure; and a telescopic push rod pivotally engaged on and extending between the fixed structure and the inverting shutter for telescopic movement between retracted and extended conditions as the inverting shutter moves between the respective first and second states. In addition to the above embodiment, the thrust reverser comprises a linkage oriented between the fixed structure and the inverting flap. According to another variant or in addition to this, in the above embodiment, the telescopic push rod has a biasing member for biasing the telescopic push rod towards the extended condition. According to another variant or in addition to this, in the above embodiment, the telescopic push rod is in the extended state when the reversing shutter is in the second state. According to another variant or in addition to this, in the foregoing embodiment, the reversing shutter has an intermediate state oriented between the first and second states and the telescopic push rod is in the extended condition when the reversing shutter pivots between the first and second states. intermediate state and the second state. According to another variant or in addition to this, in the foregoing embodiment, the telescopic push rod is in the retracted state when the reversing shutter is in the first state, and extends from the retracted state. and in the extended state when the inverting flap pivots from the respective first state and into the intermediate state.
    [0002] According to another variant or in addition to this, in the above embodiment, the push rod comprises an abutment preventing further extension of the push rod. According to another variant or in addition to this, in the above embodiment, the thrust reverser comprises a linkage oriented between the fixed structure and the inverting flap; and wherein the inverting flap has an intermediate state oriented between the first and second states and the telescopic push rod is in the extended state when the inverting flap pivots between the intermediate state and the second state, and the telescopic push rod is in the retracted state when the inverting flap is in the first state and extends from the retracted state and in the extended state when the inverting flap pivots from the respective first state and into the intermediate state, and wherein an organ the biasing member or the biasing member exerts a biasing force against the stop when the telescopic push rod is in the extended state and exerts a component of the biasing force on the linkage when the reversing shutter is at, or between, the first state and the intermediate state. According to another variant or in addition to this, in the foregoing embodiment, the telescopic push rod comprises first and second arms extending jointly along a center line and in sliding engagement with each other. another, and a first pivotal joint engaged with the fixed structure and the first shaft and a second pivotal joint engaged with the inverter flap and the second arm and wherein an elastic element in the form of a coil spring is compressed between an axial face carried by the first arm and an opposite axial face carried by the second arm. An inverting shutter device for a thrust reverser having a translational structure, according to another non-limiting embodiment, comprises a fixed structure; an inverting flap pivotally engaged to the translation structure; a passive linkage oriented between the fixed structure and the inverting flap; and an extensible linkage engaged between the fixed structure and the inverting shutter. In addition to the foregoing embodiment, the extensible linkage is pivotally engaged between the fixed structure and the reversing shutter.
    [0003] According to another variant or in addition to this, in the above embodiment, the reversing flap has a first surface and a second opposite surface and the extensible linkage is oriented between the fixed structure and the first surface and the passive linkage is oriented between the fixed structure and the second surface. According to another variant or in addition to this, in the foregoing embodiment, the extensible linkage is a telescopic push rod and the passive linkage has an arm rigidly engaged on, and protruding outwardly from , the second surface and a distal head for a contact on the fixed structure. According to another variant or in addition to this, in the foregoing embodiment, the extensible linkage has a resilient biasing member for biasing the extensible linkage from a retracted state to an extended state. According to another variant or in addition to this, in the foregoing embodiment, the reversing shutter pivots between a stored state and an expanded state and, when in the stored state, the extensible linkage is in a retracted state and the distal head is in contact with the fixed structure and, when in the expanded state, the extensible linkage is in the extended state and the distal head is spaced from the fixed structure. The foregoing features and elements may be combined in various non-exclusive combinations, unless expressly stated otherwise. These features and elements and their operation will become more apparent in light of the following description and accompanying drawings. It should be understood, however, that the following description and figures are intended to be exemplary and non-limiting in nature. BRIEF DESCRIPTION OF THE DRAWINGS Various features will become apparent to those skilled in the art from the following detailed description of the non-limiting embodiments described. The drawings that accompany the detailed description can be briefly described as follows: FIG. 1 is a perspective view of a turbofan engine according to a nonlimiting embodiment of the present description; Figure 2 is an exploded view of the turbofan engine; FIG. 3 is a partial cross-section of a thrust reverser being stored and illustrating a passive linkage being engaged, a reversing shutter in a stowed state and a translational structure in a forward position, with portions removed for show a detail, and taken along the line 3-3 of Figure 1; Figure 4 is a partial cross section of the thrust reverser similar to Figure 3, but also illustrating an extensible linkage in a retracted state; FIG. 5 is a partial cross-section of the thrust reverser being deployed illustrating the passive linkage being released, the inverter flap in an expanded state, the translation structure in a rear position and the extensible linkage in an extended state. ; Fig. 6 is a partial perspective view of the thrust reverser deployed with portions removed to show an internal detail; Figure 7 is a perspective view of an inverting flap; Figure 8 is a cross-section of the extensible linkage taken along the line 8-8 of Figure 5; Fig. 9 is a partial cross-section of the in-use passive linkage shown along line 9-9 of Fig. 3; Figure 10 is a partial cross-section of the thrust reverser illustrating the inverting flap between the stored state and the deployed state; and Fig. 11 is a partial cross-section of the thrust reverser illustrating the reversing shutter in an intermediate state.
    [0004] DETAILED DESCRIPTION Referring to FIGS. 1 and 2, a turbojet engine 20 is centered about an axis 22 and includes a nacelle 24 which generally supports and surrounds an internal engine core which includes a fan section 26, a section of compressor 28, a combustion chamber section 30, and a turbine section 32. The fan section 26 drives air along a bypass flow path or duct 34 and the combustion chamber section 30 receives an air flow. air portion of the fan section 26 and entrains air along a core flow path (not shown) for compression by the compressor section 28, then into the combustion chamber section 30. L The air of the heart is mixed with fuel in the combustion chamber section and burned producing energy. The core air or exhaust of the combustion chamber section 30 is expanded through the turbine section 32 and, in turn, drives a central shaft (not shown) which supplies the fan section 26.
    [0005] The burned core airflow generally supplies the fan section 26 and the bypass airflow provides the majority of the forward propulsion for the engine 20. More conventional turbofan engines can have a ratio of Bypass air flow to core airflow (i.e., a bypass ratio) of about six (6: 1). More recent higher-bypass ratio engines, such as a double-flow geared turbojet engine, can have larger bypass ratios that can exceed ten (10: 1). The nacelle 24 may comprise an intake cap 36 disposed at the front of the fan section 26, a fan cowl 38 circumferentially surrounding and protecting the fan section 26, a thrust reverser 40 which can surround circumferentially the compressor, combustion chamber and turbine sections 28, 30, 32, a central exhaust body 42 at the rear of the turbine section 32, an exhaust nozzle 44 which is spaced radially outwardly from the exhaust central body 42 and a pylon 46 which supports the engine 20 typically on a lower chassis of an aircraft wing (not shown). With reference to FIGS. 2 and 3, the thrust reverser 40 generally has a radially inner shell 48 and an outer translational shell 50 radially spaced outwards with respect to the inner shell 48. The trajectory of FIG. bypass flow 34 is defined by, and located radially between, the inner and outer shells 48, 50; can be of generally annular shape; and may be located immediately downstream of the fan section 26. The outer shell 50 may have a front section or translational structure 52 and a rear section 54, both of which are generally cylindrical and concentric with respect to each other. to 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 pylon 46. The structure of the translation 52 may comprise a pressure sleeve 56 and an outer casing 58 generally spaced radially outwardly from the pressure sleeve 56. The pressure sleeve 56 extends axially between an anterior portion 60 of the structure fixed 55 such as, for example, a cylindrical fan housing of the fan section 26 and a rear portion of the fixed structure 55 such as, for example, a cascade ring 61 of the structure is fixed 55 during normal forward propulsion, for example, of an aircraft. In addition, the outer housing 58 of the front section 52 may extend axially backward from the fan cowl 38. The pressure sleeve 56 and the outer housing 58 extend one and the other. other axially backward and mutually join at a point which may generally be radially inwardly and rearwardly of the cascaded ring 61. That is, a cut transverse of the translational structure 52 resembles a horseshoe which is open in the forward direction (see arrow 63 in Fig. 3) with respect to the forward propulsion of the motor 20. Referring to Figs. at 5, a plurality of reversing shutter devices 62 of the thrust reverser 40 are circumferentially distributed about the motor axis 22.
    [0006] Each device 62 has an inverting flap 64, a dynamic or extensible linkage 66 and a releasable passive linkage 67. The linkage 67 is referred to as "passive" in the sense that it does not flex inwards, does not flex outwardly. , does not extend inward, or retract on itself. The extensible linkage 66 is generally radially inwardly of the pressure sleeve 56 of the translation structure 52 and extends axially between the fan housing 60 and the inverter flap 64 during propulsion to the 20. The passive linkage 67 is engaged and generally located radially between the reversing shutter 64 and the outer casing 58 of the translation structure 52 during forward propulsion of the engine. The reversing shutter 64 and the translation structure 52 are both capable of movement coincide with the cascaded ring 61 of the fixed structure 55, which redirects the flow of bypass air into the path bypass flow 34 which can generally change the power of the aircraft between forward propulsion and reverse propulsion.
    [0007] Each inverter flap device 62 further comprises a dynamic or extensible linkage 66 capable of providing flap stability and at least partial guiding movement of the inverter flap 64 between a stored state 68 (see FIGS. 3 and 4) for propulsion to the front of the aircraft and an expanded state 70 (see Figures 5 and 6) for a reverse or rearward propulsion of the aircraft. It is further contemplated and understood that the extensible linkage 66 does not obstruct the bypass flow path 34 when the inverter flap 64 is in the stowed state 68 (i.e., does not include a stem drive). The translational structure 52 of the outer shell 50 is driven substantially in an axial direction (see arrow 72) between a forward position 74 (see FIG. 3), placing the reversing shutter 64 in the stowed state 68, and a rear position 76 (see FIGS. 5 and 6) placing the reversing shutter 64 in the deployed state 70. When in the forward position 74, the translation structure 52 can be substantially axially aligned to the inverted shutter 64 and located radially outwardly therefrom. When in the rear position 76, the translational structure 52 may be substantially axially behind the reversing shutter 64 (i.e. at the rear thereof); axially aligned with the cascaded ring 61; and located substantially radially outwardly of the inverting flap 64. With reference to FIG. 3, at least one master actuator 78 of the thrust reverser 40 controls the axial movement of the translational structure 52 and can (at As non-limiting examples) be operated hydraulically or electrically or a combination of the one and the other modes. The actuator 78 may have a drive unit rigidly attached to the fan housing 60 of the fixed structure 55 and a hydraulic arm connected to the translation structure 52 and capable of being extended and retracted relative to the unit. drive. The actuator 78 may be described as "master" and the extendable linkage 66 may be described as "slave linkage" in the sense that the actuation of the linkage 66 directly depends on the driven movement of the translation structure 52. This is that is, without substantially linear movement (e.g., axial movement) of the structure 52, the extensible linkage 66 can not move. With reference to FIG. 7, the inverter flap 64 has an exposed surface 80 which partially defines the bypass flow path 34 and an opposed surface 82 which faces radially outwardly and towards the pressure sleeve 56 when the inverter flap 64 is in the stored state 68 (see Figure 4). When in the expanded state 70 (see FIG. 5), the surface 82 of the inverter flap 64 can be rotated in an axial direction substantially downstream. Inverter flap 64 also has and extends between a base or edge portion 84 attached to a front end of pressure sleeve 56 of translation structure 52 by at least one pivot connection 86 (two connections illustrated as FIG. non-limiting example) and an opposing distal edge 88. When in the stowed state 68, the edge portion 84 may be near a trailing edge of the fan housing 60 of the fixed structure 55 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 stowed state 68, a leading edge of the pressure sleeve 56 of the translation structure 52 may be releasably sealed to the rear edge of the fan housing 60 and a leading edge of the outer housing 58 of the translation structure 52 is near an edge or rear portion of the fan cowl 38. When we are in the deployed state 70, the inverter flap 64 extends substantially radially; the edge portion 84 of the door 64 remains pivotally engaged on the pressure sleeve 56 and the distal edge 88 may be in proximity to the inner shell 48. Referring to Figure 8, a non-limiting example of the linkage dynamic or expandable 66 may be a telescopic push rod. The push rod 66 may comprise first and second elongated arms 90, 92, an elastic biasing member 94 and opposed pivot joints 96, 98. The first and second arms 90, 92 extend longitudinally together and are in a longitudinal direction. expandable or telescopic relation to each other along a center line 100. The biasing member 94 exerts a force (see arrow 102) which urges the push rod 66 to a fully extended state 104 ( see Figures 5 and 8) and away from a fully retracted state 106 (see Figure 4). The first arm 90 may be a tube having a base end connected to the pivotal joint 96 and an opposite distal end which is open for axial reception of the second arm 92. The second arm 92 may have a distal end which is in the tube 90 and an opposite base end which is connected to the pivoting joint 98. The biasing member 94 may be a helical spring located in the tube 90 and compressed between a first face 108 carried by the tube 90 and facing axially in the direction of the pivoting joint 98, and a second opposite face 110 carried by the second arm 92 and 11 facing axially in the direction of the pivoting joint 96. It is furthermore contemplated and understood that the biasing member 94 may be a pneumatic device or hydraulic or spring. The push rod 66 may further comprise a stop 112 having a first contact 114 carried by the tube 90 and a second contact 116 carried by the arm 92. The first contact 114 may be at the distal end of the tube 90 and worn. by a flange of the tube which projects radially inwards. The second contact 116 may be at or near the distal end of the second arm 92 and carried by an enlarged distal head. It is further contemplated and understood that a substantial portion of the second arm 92 can remain inside and is supported by the tube 90 when the push rod 66 is in the extended state 104 (i.e. the enlarged distal head may be elongate in the axial direction) to enhance the structural rigidity of the push rod. When the push rod 66 is in the extended state 104, the contacts 114, 116 of the stop 112 are in a contact urged by the elastic force 102 of the biasing member 94. Referring to FIGS. 5, 7 and 8 the pivoting joint 96 is also connected to the fan housing 60 of the fixed structure 55 and the pivoting joint 98 is connected to the inverter flap 64 near the distal edge 88. The orientation of the pivotal connections 86 and the gaskets 96, 98 is such that that their pivot axes 118 are substantially parallel to each other (see Figure 7). Each reversing shutter device 62 may have a centrally located push rod or two push rods 66 generally located along opposed edges 120, 122 of the inverter shutter 64 (see FIG. 7), each edge 120, 122 extending between the 84 and the distal edge 88 of the inverter flap 64. To further enhance the aerodynamic efficiency of the flow through the bypass flow path 34 when the thrust reverser 40 is stored, the exposed surface 80 of the flap Inverter 64 may define cavities 124, 126 (see FIG. 6) which extend along the respective edges 120, 122 for a sensitive storage of the respective push rods 66 when the reversing shutter 64 is in the stowed state 68 and the push rods 66 are in the retracted state 106 (see FIG. 4). That is, no substantial portion of the push rod 66 extends through, or otherwise substantially obstructs, the bypass air flow during the forward propulsion of the engine, thus the airflow efficiency is not reduced during normal flight operating conditions and the noise is minimized. With reference to FIGS. 3 to 5, the fixed structure 55 may comprise a fixed element 128 which may have at least one deflector 130 which functions to further deflect the bypass air flow (see arrow 132 in FIG. 5) from a direction downstream towards, at least in part, an upstream direction when the inverting flap 64 is in the deployed state 70. The cascade element 128 may be generally cylindrical and concentric with respect to the motor shaft 22 and extends axially between the fan housing 60 and the cascade ring 61 of the fixed structure 55. Because the element 128 can be rigidly attached to the fan housing 60 and / or the cascade ring 61, the element remains fixed. For this reason, when the translation structure 52 of the outer shell 50 is in the forward position 74 (see FIG. 3), the fixed member 128 is generally stored between the pressure sleeve 56 and the housing 58 of the translation structure 52 and the deflectors 130, supported by the element 128, are, for this reason, generally non-functional. When the translation structure 52 is in the rear position 76 (see FIG. 5), the stationary member 128 is generally exposed to, or within, the bypassed bypass flow path and the bypassed bypass air can flow through the element 128 and is further deflected by the deflectors 130 to the forward direction 61. With reference to Figures 4, 7 and 9, the releasable passive linkage 67 of the reversing shutter device 62 may be used together with the telescopic push rod 66 when the inverter shutter 64 is in or near the stored state 68, but can not be used (i.e. is released) when the inverter shutter 64 is in the deployed state 70. The passive linkage 67 may include: an arm 134 which can protrude rigidly outwardly from the surface 82 of the inverter flap 64 and to a distal reduction head 136; an elastic seal 138 which can be engaged on the surface 82 and surrounds a base of the arm 134; an opening 140 communicating through the pressure sleeve 56 (see also Fig. 10); a channel 142 in the fixed element 128 and defined between two opposite tracks 144, 146; and an opening 148 in a face 150 of the stationary member 128 which faces radially inwardly with respect to the motor axis 22 and communicates directly with the channel 142. The channel 142 extends from the opening 148 and tilts in a direction upstream (that is to say forward) and radially outwardly with respect to the motor axis 22. The track 146 has a portion front 152 which extends generally radially outwardly from the opening 148 and a rear portion 154 which extends rearwardly from the opening. Runway 144 and the anterior portion 152 of runway 146 define channel 142. Back portion 154 of runway 146 serves to guide head 136 in an axial and radially inward direction, and may be an integral portion. and contiguous with the face 150 of the fixed element 128.
    [0008] With reference to FIG. 9, the arm 134 may be a roller yoke having first and second uprights 156, 158, and the distal head 136 may be a roller having an axis of rotation 160 for rolling contact on the tracks 144, 146. The roller 136 is disposed between and supported in rotation by the distal ends of each upright 156, 158. When the inverter flap 64 is near or in the stowed state 68, the uprights 156, 158 are received by respective parallel slots 162, 164 which extend jointly axially with the channel 142 and extend in the lateral direction between the channel 142 and the face 150 of the fixed member 128. That is, that is, slots 162, 164 communicate through face 150 and with channel 142 and opening 148.
    [0009] The passive linkage 67 may further comprise a ramp-like protrusion 166 which carries the first track 144 and is located between, and in part defines, the two slots 162, 164, and is defined between the first track 144 and the face 150 of the fixed element 128. The reversing shutter 64 is capable of a "compound movement" which comprises: 1) a linear movement attributable to the flap 64 being directly engaged on the translation structure 52, and 2) a rotational movement or pivoting connection 86 and extensible linkage 66. In addition, the inverter flap device 62 may be a "dead stroke" device at least in the sense that the translation structure 52 can move an axial distance. relatively short backward when initially moving away from the forward position and before the inverter flap 64 begins to pivot away from the stored state. This dead travel is enabled by the roller 136 remaining engaged in the slot 142 and until the pressure sleeve 56 is moved back and disconnects. The slit can be of any shape, by making the slit parallel to the motor shaft 22 over a distance, the flap will not rotate (relative to the pressure sleeve 56) along the length of the parallel section.
    [0010] During operation and before the deployment of the thrust reverser 40, the reversing shutter device is in the stowed position, the translation structure 52 of the outer shell 50 is in the forward position 74, the reversing shutter 64 is in the stowed state 68, the extendable linkage 66 is in the retracted state 106 and the passive linkage 67 is generally engaged within the channel 142 (see FIGS. 3 and 4). With the extendable linkage 66 in the retracted state 106, the linkage extends axially rearwardly from the pivoting joint 96 and radially outwardly and the biasing member 94 continues to exert the biasing force 102. Because the actuator 78 is inactive and the linkage 66 extends slightly radially outwardly, a radial component (see arrow 168 in FIGS. 4 and 11) of the biasing force 102 is useful for keeping inverting flap 64 biased in stored state 68 against bumpers or flap stops (not shown) and until a higher opposing force urges inverter flap 64 to the deployed state 70 (see Figure 5). When in the stowed state 68, the radial component 168 of the biasing force 102 may help compress the seal 138 against the pressure sleeve 56 and / or the placement of the translation structure 52 in the housing. stored state 68 by the actuator 78 can force the roller 136 on the track 144 and with a slight rolling forward of the roller 136, compress the seal 138. It is further envisaged and understood that it is generally the relationship angularly between the extendable linkage 66 and the pressure sleeve 56 (created essentially by placement and spacing of the radially inwardly-facing seal 96 of the pivot connection 86) which provides the radial component of the biasing force 102 For this reason, the radial component of the biasing force may not be only in a radial direction, but may be inclined away from it and, depending on the angular relationships between the push rod 66, the shutter in pourer 64 and pressure sleeve 56.
    [0011] During the initial deployment of the thrust reverser 40, the actuator 78 exerts an axial force towards the rear (see arrow 170 in FIG. 3) against the translational element 52. Because this axial force 170 generally exceeds combined biasing force 102 of the at least one push rod 66, the translation member 52 begins to move axially 16 backward. The roller 136 of the linkage 67 contacts the front portion 146 of the track 152 and begins to roll the arm 134 back by pressing the reversing shutter 64 in a clockwise direction about the pivot connection 86. The angle of the anterior portion 152 of the track 146 also causes the arm 134 to begin movement through the opening 140 and out of the pressure sleeve 56, and the push rod 66 begins to expand. outside the retracted state 106. During this same movement, the linkage 67 rotates in a clockwise direction around the seal 96 and a counterclockwise direction around the seal 98. With the continued deployment of the thrust reverser 40, the roller 136 rolls rearward along the anterior portion 146 of the track 152 (see Figure 10), then out of the opening 148 and on the rear portion 154 of the track 152 (see Figure 11). The roller 136 continues to roll backward on the rear portion 154 and until the inverter flap 64 reaches an intermediate state 172 (see Figure 11). While the roller 136 is biased against, and rolls on the rear portion 154, any substantial and prolonged shrinkage of the arm 134 of the opening 140 may cease. In the intermediate state 172, the push rod 66 has reached the extended condition 104 and the stop 112 (see Fig. 8) is engaged. With the abutment 112 engaged, the biasing force 102 of the biasing member 94 is exerted only against the abutment 112, so the actuator 78 no longer needs to operate against this force (i.e. the force 102 is an auxiliary force during deployment), but must always overcome an increasing force produced by the bypass air flow against the reversing flap 64. Generally, in the intermediate state 172 and with the push rod 66 in the In the extended state 104, the biasing force 102 is no longer exerted against the inverter flap 64 and the radial component 168 of the force 102 becomes zero (i.e. ceases to exist). With the absence of the radial component 168 and with the axial movement towards the rear continued of the pressure sleeve 56 of the translation structure 52: the inverter flap 64 continues to pivot out of the intermediate state 172 and to the state deployed 70; the roller 136 is detached from the rear portion 154 of the track 146 (that is to say the linkage 67 is released); then the arm 134 carrying the roll 136 exits the opening 140 (i.e. the arm 134 no longer protrudes through the pressure sleeve 56). The actuator 78 continues to push the translation structure 52 rearward until the translation element reaches the rear position 76 placing the reversing shutter in the deployed state 70 and stabilized by the push rods 66 in the condition extension 104 with linkage 67 released (see Figure 5).
    [0012] It should be understood that the relative position terms such as "forward", "backward", "upper", "lower", "above", "below" and the like are with reference to the ordinary operating not be considered as otherwise limiting. It should also be understood that like reference numerals identify corresponding or similar elements on all of the multiple drawings. It should be understood that although a particular arrangement of the components is described in the illustrated embodiment, other arrangements will also be advantageous. Although particular sequences of steps can be illustrated, described, and claimed, it should be understood that the steps can be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present disclosure.
    [0013] The foregoing description is given by way of example rather than defined by the limitations described. Various non-limiting embodiments are described; however, those skilled in the art would recognize that various modifications and variations in light of the above teachings will fall within the scope of the appended claims. For this reason, it is understood that, within the scope of the appended claims, the description may be put into practice other than as specifically described. For this reason, the appended claims must be studied to determine the actual scope and content. 19
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. A thrust reverser (40) comprising: a translational structure (52) constructed and arranged to move between first and second positions; an inverting flap (64) pivotally engaged to the translation structure (52) for pivotal movement between a first state when the translation structure (52) is in the first position and a second state when the translation structure (52) is 52) is in the second position; a fixed structure (55); and a telescopic push rod (66) pivotally engaged on and extending between the fixed structure (55) and the inverter shutter (64) for telescopic movement between retracted and extended states when the reversing shutter (64) ) moves between the first and second respective states.
    [0002]
    The thrust reverser of claim 1, further comprising: a linkage (67) oriented between the fixed structure (55) and the inverter flap (64).
    [0003]
    The thrust reverser of claim 1 or 2, wherein the telescopic push rod (66) has a biasing member (94) for biasing the telescopic push rod (66) toward the extended condition. 20
    [0004]
    The thrust reverser of claim 1, 2 or 3, wherein the telescopic push rod (66) is in the extended state when the inverter flap (64) is in the second state.
    [0005]
    A thrust reverser according to any preceding claim, wherein the inverter flap (64) has an intermediate state oriented between the first and second states and the telescopic push rod (66) is in the extended state when the flap inverter (64) pivots between the intermediate state and the second state.
    [0006]
    A thrust reverser according to claim 5, wherein the telescopic push rod (66) is in the retracted state when the reversing shutter (64) is in the first state, and extends from the retracted state and in the extended condition when the inverting flap (64) pivots from the respective first state and in the intermediate state.
    [0007]
    The thrust reverser of claim 4, wherein the push rod (66) comprises a stop (112) preventing further exit of the push rod (66).
    [0008]
    The thrust reverser of claim 7, further comprising: a linkage (67) oriented between the fixed structure (55) and the inverter flap (64); and wherein the inverting flap (64) has an intermediate state oriented between the first and second states and the telescopic push rod (66) is in the extended state when the inverting flap (64) pivots between the intermediate state and the intermediate state. second state, and the telescopic push rod (66) is in the retracted state when the inverting flap (64) is in the first state and extends from the retracted state and in the extended state when the inverting flap ( 64) pivots from the respective first state and into the intermediate state, and wherein a biasing member or the biasing member (94) exerts a biasing force against the stop (112) when the telescopic push rod (66) is in the extended state and exerts a component of the biasing force on the linkage (67) when the inverter flap (64) is at or between the first state and the intermediate state.
    [0009]
    A thrust reverser according to any preceding claim, wherein the telescopic push rod (66) comprises first and second arms (90, 92) extending jointly along a center line (100) and engaged sliding with each other, and a first pivoting joint (96) engaged with the fixed structure (55) and the first arm (90) and a second pivoting joint (98) engaged with the reversing shutter (64) and the second arm (92) and wherein an elastic member in the form of a helical spring is compressed between an axial face (108) carried by the first arm (90) and an opposite axial face (110) carried by the second arm (90). arm (92).
    [0010]
    Inverter flap device (62) for a thrust reverser (40) having a translation structure (52), the inverter flap device (62) comprising: a fixed structure (55); an inverting flap (64) pivotally engaged to the translation structure (52); a passive linkage (67) oriented between the fixed structure (55) and the reversing shutter (64); and an extensible linkage (66) engaged between the fixed structure (55) and the inverter flap (64). 22
    [0011]
    An inverting shutter device according to claim 10, wherein the extensible linkage (66) is pivotally engaged between the fixed structure (55) and the inverting shutter (64).
    [0012]
    An inverting shutter device according to claim 10 or 11, wherein the inverting flap (64) has a first surface (80) and a second opposing surface (82) and the extensible linkage (66) is oriented between the fixed structure ( 55) and the first surface (80) and the passive linkage (67) is oriented between the fixed structure (55) and the second surface (82).
    [0013]
    An inverting shutter device according to claim 12, wherein the extendable linkage (66) is a telescopic push rod (66) and the passive linkage (67) has an arm (134) rigidly engaged on and protruding towards the exterior from the second surface (82) and a distal head (136) for contact with the fixed structure (55).
    [0014]
    An inverting shutter device according to claim 13, wherein the inverting flap (64) pivots between a stored state and an expanded state and, when in the stored state, the extensible linkage (66) is in the retracted state and the distal head (136) is in contact with the fixed structure (55) and, when in the expanded state, the extensible linkage (66) is in the extended condition and the distal head (136) is spaced apart from the fixed structure (55).
    [0015]
    The reversing shutter device according to any one of claims 10 to 14, wherein the extensible linkage (66) has an elastic biasing member (94) for biasing the extendable linkage (66) from a retracted state to a state in extension. 23
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    同族专利:
    公开号 | 公开日
    US20150267641A1|2015-09-24|
    FR3018865B1|2019-04-19|
    US9976516B2|2018-05-22|
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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 |
    2018-01-05| PLSC| Publication of the preliminary search report|Effective date: 20180105 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/222,182|US9976516B2|2014-03-21|2014-03-21|Thrust reverser for a turbofan engine|
    US14222182|2014-03-21|
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