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  • 专利说明
  • 权利要求
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    • 专利摘要:
    The invention relates to a longitudinal strut assembly (10) for use in a thrust reverser (30) of a propulsion system (18). The thrust reverser (30) includes a fixed structure (36) and a sliding structure (38) that at least partially define an airflow bypass duct (40) therebetween. The sliding structure (38) is movable relative to the fixed structure (36). The sliding structure (38) includes an inverter flap (46) disposed at least partially within the airflow bypass duct (40). The longitudinal strut assembly (10) includes a longitudinal strut fitting (12) and a longitudinal strut (14). The longitudinal strut fitting (12) is attached to the fixed structure (36) of the thrust reverser (30). The longitudinal strut (14) includes a first end portion (52) and a second opposite end portion (54). The first end portion (52) is pivotally coupled to the inverter flap (46). The second end portion (54) is pivotally coupled to the longitudinal strut fitting (12). The second end portion (54) includes a curved section.
    公开号:FR3020412A1
    申请号:FR1553718
    申请日:2015-04-24
    公开日:2015-10-30
    发明作者:Stuart J Byrne
    申请人:Rohr Inc；
    IPC主号:
    专利说明:

    [0001] LONGITUDINAL CONTRAFIT ASSEMBLY INCLUDING BACKLIT LONGITUDINAL BACKLIGHT FERRULE [0001] 1. Technical Field. The aspects of the present invention relate to a propulsion system nacelle which includes a thrust reverser and more particularly relate to a longitudinal strut assembly included in the thrust reverser of a propulsion system nacelle. [0003] 2. Background information. The existence of a propulsion system is known which includes an engine (for example, a gas turbine engine), a nacelle which at least partially surrounds the engine and a mast which connects the engine and the nacelle to a vehicle (for example, a plane). In some examples, the nacelle includes a thrust reverser and the thrust reverser includes a plurality of inverting flaps. In these examples, the inverting flaps can be moved from a retracted position to an extended position, and can thereby redirect a bypass duct airflow so that it is evacuated through a series of grilles. The thrust reverser also includes a plurality of longitudinal strut assemblies, each of which includes a longitudinal strut and a longitudinal strut fitting. A radially outer end portion of each longitudinal strut is pivotably coupled to an inverter flap, and a radially inner end portion of each longitudinal strut is pivotally coupled to a longitudinal strut fitting. In previous longitudinal strut assembly designs, the longitudinal strut fittings are mounted on an aerodynamic surface of the thrust reverser that partially defines the bypass conduit. In these designs, the longitudinal strut fitting extends radially into the bypass duct, and thus has a negative impact on the aerodynamic flow of the bypass duct airflow. Aspects of the present invention relate to this problem and other problems.
    [0002] SUMMARY OF THE INVENTION [0005] According to one aspect of the present invention, there is provided a longitudinal strut assembly for use in a thrust reverser of a propulsion system. The thrust reverser includes a fixed structure and a sliding structure that at least partially define an annular airflow bypass duct therebetween. The sliding structure is movable relative to the fixed structure. The sliding structure includes an inverter flap disposed at least partially within the airflow bypass duct. The longitudinal strut assembly includes a longitudinal strut fitting and a longitudinal strut. The longitudinal strut fitting is attached to the fixed structure of the thrust reverser. The longitudinal strut includes a first end portion and a second end portion opposite. The first end portion is pivotally coupled to the inverter flap. The second end portion is pivotally coupled to the longitudinal strut fitting. The second end portion includes a curved section. According to another aspect of the present invention, there is provided a thrust reverser of a gas turbine propulsion system for an aircraft. The thrust reverser includes an inverting flap, a longitudinal strut fitting and a longitudinal strut. The inverting flap pivots between a retracted position and an extended position in which the inverting flap redirects the air to generate reverse thrust. The longitudinal strut fitting is attached to a fixed structure of the thrust reverser at least in part by a fastener. The longitudinal strut has a first end and a second distal end. The first end is pivotally attached to the inverter flap, and the second end is pivotally attached to the longitudinal strut fitting. The second end of the longitudinal strut is disposed at least partially in a channel of the longitudinal strut fitting. The fastener is disposed at least partially in the channel and below the second end of the longitudinal strut. In addition or alternatively, the present invention may include one or more of the following features separately or in combination: the thrust reverser extends between a front end and a rear end along an axial center line; and the thrust reverser extends circumferentially about the axial centerline; the fixed structure of the thrust reverser includes a radially inner fixed structure and a radially outer fixed structure; and the longitudinal strut fitting is embedded within the internal fixed structure; the fixed structure of the thrust reverser includes a radially internal fixed structure and a radially external fixed structure; at least a portion of the longitudinal strut fitting is disposed in a cavity which extends radially in the internal fixed structure; the cavity extends radially between an inner surface of the inner fixed structure and an opposite aerodynamic surface of the inner fixed structure; and the aerodynamic surface partially defines the airflow bypass duct; - A radially outermost surface of the longitudinal strut fitting 10 is at least substantially radially aligned with the aerodynamic surface of the inner fixed structure; and the aerodynamic surface partially defines the airflow bypass duct; the radially outermost surface of the longitudinal strut fitting is at least substantially flush with the aerodynamic surface; the thrust reverser extends between a front end and a rear end along an axial center line and the thrust reverser extends circumferentially around the axial centerline; the longitudinal strut extends at least substantially along a longitudinal strut axis extending radially; and a pivot point of the longitudinal strut relative to the longitudinal strut fitting is at the rear of the axis of the longitudinal strut and offset from it; The fastener is at least substantially covered by the longitudinal strut when the longitudinal strut is in a first pivoting position with respect to the longitudinal strut fitting and the fastener is at least partially exposed when the longitudinal strut is within one second pivoting position with respect to the longitudinal strut fitting; The fastener is at least partially exposed to an airflow bypass duct of the thrust reverser when the longitudinal strut is in a second pivoting position with respect to the longitudinal strut fitting; the channel is at least substantially covered by the longitudinal strut when the longitudinal strut is in a first pivoting position relative to the longitudinal strut fitting and the channel is at least partially exposed when the longitudinal strut is in a second position of pivoting with respect to the longitudinal strut fitting; and the channel is at least partially exposed to an airflow bypass duct of the thrust reverser when the longitudinal strut is in a second pivoting position with respect to the longitudinal strut fitting. These and other aspects of the present invention will become apparent in light of the drawings and the detailed description provided hereinafter. BRIEF DESCRIPTION OF THE DRAWINGS [0009] Figure 1 is a perspective view of a propulsion system. FIG. 2 is an exploded perspective view of the propulsion system of FIG. 1. FIG. 3 is a diagrammatic sectional view of the thrust reverser in its retracted position, of the fan casing parts. central ejection body and ejection nozzle of the nacelle which are included in the propulsion system of FIG. 1. FIG. 4 is a schematic sectional view of the thrust reverser in its deployed position, parts of the fan casing, central ejection body and nacelle ejection nozzle which are included in the propulsion system of FIG. 1. FIG. 5 is a perspective view of the longitudinal strut assembly which is included in the propulsion system of FIG. 1. FIG. 6 is another perspective view of the longitudinal strut assembly of FIG. 5. FIG. 7 is an elevation view in section of FIG. longitudinal strut fitting included in the longitudinal strut assembly of FIG. 5. FIG. 8 is a sectional elevational view of the longitudinal strut assembly of FIG. 5. FIG. 9 is a perspective view of another embodiment of longitudinal strut assembly. Figure 10 is a sectional elevational view of the longitudinal strut assembly of Figure 9. [0019] Figure 11 is a perspective view of another embodiment of longitudinal strut assembly. Figure 12 is a plan view of the longitudinal strut assembly of Figure 11.
    [0003] DETAILED DESCRIPTION OF THE ASPECTS OF THE INVENTION [0021] The present disclosure describes the embodiments of a longitudinal strut assembly 10 (see FIGS. 3-6 and 8-12) which includes a longitudinal strut fitting 12 and a longitudinal strut 14 The present disclosure describes the aspects of the present invention with reference to the exemplary embodiments illustrated in the drawings; however, aspects of the present invention are not limited to the exemplary embodiments illustrated in the drawings. The present disclosure may describe one or more features as having a length extending with respect to an x axis, a width extending with respect to an y axis, and / or a height extending with respect to an z axis. The drawings illustrate the respective axes. The present disclosure uses the terms "circumferential", "annular", "abut", and variations thereof, to describe one or more characteristics. The term " circumferential " and variations thereof are used herein to indicate that a feature extends along a curve which is centered about an axis of rotation. The term " annular " and variations thereof are used herein to indicate that a characteristic is at least partially in the form of a ring (e.g., of a circular ring or a ring). other form). The term "abuts" and variants thereof are used herein to indicate either a first characteristic is in direct contact with a second characteristic, or a first characteristic is almost in direct contact with a second characteristic. characteristic and is separated from the second characteristic only by one or more small spaces. If we look at Figure 1, the longitudinal strut assembly 10 (see Figures 3-6 and 8-12) is included in a nacelle 16, and the nacelle 16 is included in a propulsion system 18. The system of propulsion 18 and the nacelle 16 can be configured in various different ways. In the illustrated embodiment, the propulsion system 18 is a turbofan propulsion system which includes the platform 16, a gas turbine engine 20 and a mast 22. If we look at FIG. gas 20 extends in a longitudinal direction along an axial center line 24, between a front end and a rear end. The nacelle 16 partially surrounds the gas turbine engine 20. The mast 22 connects the nacelle 16 and the gas turbine engine 20 to the underside of an aircraft wing (not shown). The nacelle 16 includes an inlet 26, a fan cowl 28, a thrust reverser 30, a central ejection body 32 and an ejection nozzle 34. The longitudinal strut assembly 10 (see FIGS. 3-6 and 8- 12) is included in the thrust reverser portion 30 of the nacelle 16. [0025] If we look at FIGS. 3 and 4, in the illustrated embodiment, the thrust reverser 30 is a thrust reverser of the type thrust deflection grating which includes a fixed structure 36 and a sliding structure 38. The fixed structure 36 and the sliding structure 38 partially define an annular bypass duct 40. The fixed structure 36 includes a radially inner fixed structure 37 and a radially fixed structure external 39. The external fixed structure 39 extends in a generally longitudinal direction from a rear end of a fan casing 42 which surrounds a fan 44 of the gas turbine engine 20 (see FIG. 2). The sliding structure 38 can be selectively moved (for example, by means of one or more cylinders) in a generally longitudinal direction relative to the fixed structure 36, between a retracted position (see FIG. 3) (for example, at the during a normal push operation) and an extended position (see Figure 4) (for example, during a thrust reversal operation). FIGS. 3 and 4 illustrate the relative positioning of the internal fixed structure 37, of the external fixed structure 39 and of the sliding structure 38 of the thrust reverser 30, as well as of the fan casing portions 42, the central body of FIG. ejection 32 and ejection nozzle 34 of the nacelle 16. [0026] The sliding structure 38 includes a plurality of inverting flaps 46, each extending between a front portion and a rear portion. The front part of each reversing flap 46 is pivotally mounted on the sliding structure 38 of the thrust reverser 30, and the rear part of each reversing flap 46 is pivotally coupled to a longitudinal strut 14, as will be described. in detail below. Each of the inverting flaps 46 can be moved between a retracted position (see FIG. 3) (for example, during a normal pushing operation) and an extended position (see FIG. 4) (for example, during an operation thrust reversal). The inverting flaps 46 are configured to be in their respective retracted positions (see FIG. 3) when the sliding structure 38 is in its retracted position (see FIG. 3), and are configured so as to be in their respective deployed positions (see FIG. 4) when the sliding structure 38 is in its extended position (see FIG. 4). If we look again at FIG. 2, during the operation of the propulsion system 18 in this embodiment, an air flow (not shown) enters the gas turbine engine 20 through the fan 44 of the gas turbine engine 20, and the air flow is subsequently divided into at least one main air flow (not shown) and a secondary air flow 48 (see Figures 3 and 4). The main air stream enters the gas turbine engine 20, where it is compressed in a compressor section (not shown), heated in a combustion chamber section (not shown), and expanded to produce a combustion power. rotation in a turbine section (not shown). The main air stream is then exhausted through the rear end of the gas turbine engine 20, and is then finally discharged through the exhaust nozzle portion 34 of the nacelle 16 to produce normal thrust. If we look again at FIGS. 3 and 4, when the sliding structure 38 is in the retracted position (see FIG. 3), the secondary air flow 48 can pass from a front end of the bypass duct 40 to a rear end of the bypass duct 40 and then to the ejection nozzle 34, through which it can be evacuated to allow normal thrust. The longitudinal struts 14 each block only a small portion of the bypass duct 40, and thus the bypass airflow 48 can pass around them relatively easily. When the sliding structure 38 is in its extended position (see FIG. 4), the series of grids 50 is exposed to the bypass air flow 48 passing through the bypass duct 40, and is exposed to surrounding ambient air. the thrust reverser 30. The inverter flaps 46 are deployed to redden a portion of the bypass air flow 48 to the series of grids 50, through which the secondary air flow 48 can be evacuated to generate the reverse thrust . If we look at Figures 3 and 4, each of the longitudinal struts 14 includes a radially outer end portion 52, a radially inner end portion 54, and a shaft portion which extends radially between the portion of outer end 52 and the inner end portion 54. The outer end portion 52 of each longitudinal strut 14 is pivotably coupled to a rear end of an inverter flap 46, and the inner end portion 54 of each Longitudinal strut 14 is pivotally coupled to a longitudinal strut fitting 12 which is disposed with respect to the inner fixed structure 37 of the thrust reverser 30, as will be described in detail hereinafter. If we look at Figures 3 and 4, each of the longitudinal struts 14 can be pivotally displaced around its inner end portion 54, between a retracted position (see Figure 3) and an extended position (see Figure 4). ). The longitudinal struts 14 are configured so as to be in their respective retracted positions (see FIG. 3) when the sliding structure 38 and its inverting flaps 46 are in their respective retracted positions (see FIG. 3), and the longitudinal struts 14 are configured. so as to be in their respective deployed positions (see FIG. 4) when the sliding structure 38 and its inverting flaps 46 are in their respective deployed positions (see FIG. 4). In some embodiments (see, for example, Figures 5, 6 and 8), the inner end portion 54 of the longitudinal strut 14 has a "straight" configuration, so that the part of internal end 54 and the shaft portion of the longitudinal strut 14 extend at least substantially along a common axis extending radially. In other embodiments (see, for example, FIGS. 9-12) in which longitudinal strut 14 is said to be in a "bot-foot" configuration, the inner end portion 54 of the longitudinal strut 14 is curved with respect to the axis of the shaft portion extending radially, and the shaft portion extends along a second axis which is angularly offset from the first axis. In the "bot-foot" configuration, the pivot point of the longitudinal strut 14 with respect to the longitudinal strut fitting 12 is behind (i.e., aft of), and offset from , the axis of the longitudinal strut shaft portion 14 extending radially. The shaft portion of each longitudinal strut 14 may be linear with the axial central league 24 of the gas turbine engine 20, or may be "twisted". In embodiments in which the shaft portion is linear with the axial center line 24 (see Figures 5, 6 and 8), an axis extending between a leading edge and a trailing edge of the shaft portion extends in a longitudinal direction which is at least substantially parallel to the axial center line 24 of the gas turbine engine 20 (see FIG. 2). In embodiments in which the shaft portion is twisted (see Figs. 11 and 12), an axis 56 (see Fig. 12) extending between the leading edge and the trailing edge of the shaft portion is angled (ie, is shifted) with respect to an axial centerline 24. [0034] Looking at FIG. 8, each of the longitudinal struts 14 also includes a longitudinal strut bearing 58 positioned within an opening extending through the inner end portion 54 of the longitudinal strut 14. The longitudinal strut bearing 58 allows the inner end portion 54 of each longitudinal strut 14 to be pivotably coupled to a longitudinal strut fitting 12, as will be described in detail below. The longitudinal strut bearing 58 is aligned about a longitudinal strut bearing axis 60. The longitudinal strut bearing axis 60 extends in a transverse direction that is at least substantially normal to the axial center line 24 of the engine. gas turbine 20 (see Figure 2). This may be the case even in embodiments in which the shaft portions of the longitudinal struts 14 are twisted, as described above. If we look at Figures 5 to 12, each longitudinal strut fitting 12 is "embedded" in the internal fixed structure 37 of the thrust reverser 30 (see Figures 2 to 4). The term "recessed" and its variants are used herein with respect to longitudinal strut fittings 12 to indicate that at least substantially all longitudinal strut fittings 12 are nestled in a recess 62 (see FIGS. 7, 8 and 10) which extends radially (i.e. towards the axial center line 24 of the gas turbine engine 20) in the internal fixed structure 37. In some embodiments, the longitudinal strut fittings 12 are embedded in the structure internal fixed member 37 such that a radially outermost surface 64 (see FIGS. 7, 8 and 10) of the longitudinal strut fitting 12 is at least substantially radially aligned with an aerodynamic surface 66 (see FIGS. 8 and 10) of the internal fixed structure 37. If we look at FIGS. 7, 8 and 10, in the illustrated embodiments, the internal fixed structure 37 extends radially between a surface 68 and an aerodynamic surface 66. The aerodynamic surface 66 partially defines the bypass duct 40. The aerodynamic surface 66 may include one or more known noise suppression features that reduce the acoustic noise present within the bypass duct 40 The internal fixed structure 37 includes a plurality of cavities 62, each extending radially between the inner surface 68 and the aerodynamic surface 66 of the inner fixed structure 37. Each of the longitudinal strut fittings 12 is disposed in one of the cavities 62 so that the outermost surface 64 of the longitudinal strut fitting 12 is at least substantially flush with the aerodynamic surface 66. [0036] If we look at FIGS. 7, 8 and 10, each of the fittings longitudinal struts 12 includes an external fitting 70 and an internal fitting 72. The external fitting 70 is attached to the stub. internal fixed structure 37 of the thrust reverser 30 (see FIGS. 2-4). The inner fitting 72 is attached to the outer fitting 70. The outermost surface 64 of each longitudinal strut fitting 12 may be defined by one or both of the outer fitting 70 and the inner fitting 72. [0037 The outer fitting 70 of the longitudinal strut fitting 12 can be configured in a variety of different ways. If we look further at FIGS. 7, 8 and 10, in the illustrated embodiments, the external fitting 70 includes an external fitting base 74 and an outer fitting flange 76 which extends radially away from the base of external fitting 74. The external fitting base 74 abuts against the internal surface 68 of the internal fixed structure 37, and is attached to the internal fixed structure 37 by means of a plurality of external fitting screws 78 and external fitting nuts 80 (see FIG. 7). The external fitting screws 78 extend through the openings disposed in the external fitting base 74, and extend through the openings disposed in the inner fixed structure 37. The outer fitting flange 76 is positioned on the inside one of the cavities 62 of the internal fixed structure 37. The external fitting flange 76 can abut against the surface which defines the cavity 62. The external fitting 70 of the longitudinal strut fitting 12 does not need to be attached to the inner fixed structure 37 of the thrust reverser 30 as illustrated in the drawings; other attachment methods, and / or other types of fasteners, may be used additionally or alternatively. The internal fitting 72 of the longitudinal strut fitting 12 can be configured in various different ways. If we look further at FIGS. 7, 8 and 10, in the illustrated embodiments, the internal fitting 72 includes an internal fitting base 82, an internal fitting channel 84 (see FIGS. 8 and 10), first and second bearings internal fitting 86, 88 (see FIG. 8), and an internal fitting pin 90 (see FIGS. 8 and 10). The internal fitting base 82 is positioned inside the cavity 62 of the internal fixed structure 37 so that it abuts against the external fitting base 74 and the external fitting flange 76 of the longitudinal strut fitting 12. The internal fitting base 82 is attached to the internal fitting base 74 with one or more internal fitting screws 92, 94 (see FIGS. 7 and 10). The internal fitting screws 92, 94 extend through the openings in the internal fitting base 82, and engage with the threaded openings 96, 98 (see FIGS. 7 and 10) disposed in the external fitting base. 74. The internal fitting base 82 does not need to be attached to the external fitting base 74 in the manner illustrated in the drawings; other fixing methods and / or other types of fasteners may be used in addition or alternatively. The internal fitting channel 84 extends radially in the internal fitting base 82, and is configured to receive the inner end portion 54 of the longitudinal strut 14. In some embodiments, at least one internal fitting screws 92, 94 extends through an opening in a surface of the internal fitting base 82 which defines the internal fitting channel 84. If we look at FIG. 9, for example, in the illustrated embodiment the internal fitting 72 of the longitudinal strut fitting 12 includes first and second internal fitting screws 92, 94. The first internal fitting screw 92 extends through an opening in a surface of the internal fitting base 82 which defines the internal fitting channel 84. [0041] If we look at FIG. 8, in the illustrated embodiment, the first and second internal fitting bearings 86, 88 are positioned within the openings that extend between the inner bracket channel 84 and an outer surface of the inner bracket base 82. The first and second inner bracket bearings 86, 88 are aligned about an internal bracket bearing shaft 100. The bracket shaft internal 100 extends in a transverse direction which is substantially normal to the axial center line 24 of the gas turbine engine 20 (see Figure 2). The first and second inner bracket bearings 86, 88 and the inner bracket pin 90 pivotally couple the inner end portion 54 of a longitudinal strut 14 to the inner bracket base 82. The inner bracket pin 90 is rotatably supported by the longitudinal strut bearing 58 and the first and second inner fitting bearings 86, 88. The axial ends of the inner fitting pin 90 abut against the outer fitting flange portion 76 of the strut fitting longitudinal 12.
    [0004] That is, the outer bracket 70 holds the hinge pin 90 in place when the inner bracket 72 is positioned between the outer bracket flange 76. The inner bracket pin 90 can be used to rotate around the hinge pin 90. longitudinal strut bearing axis 60 and the internal fitting bearing shaft 100, which are axially aligned with each other. If we look at Figure 8, a method of installation of the illustrated embodiments of the longitudinal strut assembly 10 includes the following steps: (1) the attachment of the external fitting 70 of the longitudinal strut fitting 12 to the internal fixed structure 37 using the plurality of external fitting screws 78 and outer fitting nuts 80 or other suitable fastening method; (2) pivotally connecting the outer end portion 52 of the longitudinal strut 14 to a rear end of an inverter flap 46 (see FIGS. 3 and 4) using one or more known means; (3) positioning the outer end portion 54 of the longitudinal strut 14 within the internal fitting channel 84 of the inner fitting 72 such that the longitudinal strut bearing 58 is axially aligned with the axis bearing of internal fitting 100; (4) positioning the inner fitting pin 90 relative to the first and second inner bracket bearings 86, 88 and the longitudinal strut bearing 58 to pivotally couple the inner end portion 54 of the longitudinal strut 14 to the internal fitting 72 of the longitudinal strut fitting 12; and (5) positioning the internal fitting 72 of the longitudinal strut fitting 12 between the outer fitting flanges 76 and attaching it to the external fitting 70 of the longitudinal strut fitting 12 by means of the internal fitting screws 92 , 94. [0043] A method of uninstalling the illustrated embodiments of the longitudinal strut assembly 10 includes the following steps: (1) removing the internal fitting screws 92, 94 to separate the internal fitting 72 from the longitudinal strut 12 of the external fitting 70 of the longitudinal strut fitting 12; (2) removing the inner fitting pin 90 from the first and second inner bracket bearings 86, 88 and the longitudinal strut bearing 58; (3) removing the inner end portion 54 of the longitudinal strut 14 from the internal fitting channel 84 of the inner fitting 72; (4) uncoupling the outer end portion 52 of the longitudinal strut 14 from the rear end of an inverter flap 46 (see FIGS. 3 and 4); and (5) removing the plurality of outer fitting screws 78 and outer fitting nuts 80 to separate the outer fitting 70 from the longitudinal strut fitting 12 of the inner fixed structure 37. [0044] In wherein at least one of the internal fitting screws 92, 94 extends through an opening in a surface of the internal fitting base 82 which defines the internal fitting channel 84, it may be necessary to position the longitudinal strut 14 in its retracted position or its deployed position before the respective internal fitting screw 92, 94 can be installed or uninstalled. If we look at Figure 8, for example, when the longitudinal strut 14 is in its retracted position (shown in Figure 8), the inner end portion 54 of the longitudinal strut 14 blocks access to the first internal fitting screw 92 ; however, when the longitudinal strut 14 is in its extended position (not shown), the inner end portion 54 of the longitudinal strut 14 is positioned so that the first internal fitting screw 92 is accessible. Thus, in this mode of In that embodiment, the longitudinal strut 14 must be positioned in its extended position (not shown) before the first internal fitting screw 92 can be installed or removed. The present longitudinal strut assembly 10 has several significant advantages. Since the present longitudinal strut fitting 12 is embedded in the internal fixed structure 37 of the thrust reverser 30 (see FIGS. 2-4), the present longitudinal strut assembly 10 allows an improved aerodynamic flow of the flow. secondary air 48 through the bypass duct 40, as compared with previous longitudinal counterpart assembly designs. In the previous designs, the longitudinal strut fittings are mounted on the aerodynamic surface of the internal fixed structure of the thrust reverser, and the longitudinal strut fittings extend radially into the bypass conduit and have a negative impact on the aerodynamic flow of the secondary air stream through the bypass duct. A maintenance provider can easily remove the longitudinal strut 14 and parts of the longitudinal strut fitting 12 via the bypass duct 40. That is to say that it is not necessary to access to the inner surface 68 of the inner fixed structure 37 to remove the longitudinal strut 14 and portions of the longitudinal strut fitting 12. This is despite the fact that the longitudinal strut fitting 12 is embedded in the internal fixed structure 37 of the thrust reverser 30. The fitting of the longitudinal strut fitting 12 into the inner fixed structure 37 prevents only the outer fitting part 70 of the longitudinal strut fitting 12 from being easily withdrawn via the bypass duct 40; however, the external fitting 70 is the component of the longitudinal strut assembly 10 that is least likely to be removed for repair or replacement purposes (e.g., it may be permanently attached to the internal fixed structure 37 for the entire life of the thrust reverser 30). The embodiments of the "bot-foot" longitudinal strut 14 shown in FIGS. 9-12 may have aerodynamic advantages over the embodiment of the "straight" longitudinal strut 14 shown in FIGS. , 6 and 8. The embodiment of the "straight" longitudinal strut 14 requires that the internal fitting channel 84 of the longitudinal strut fitting 12 (see FIG. 8) extends towards the rear of the end portion internal 54 of the longitudinal strut 14 to allow the longitudinal strut 14 to pivot in its extended position without hitting the inside of the internal fitting base 82 of the longitudinal strut fitting 12 (see Figure 8). FIG. 6 shows the longitudinal strut 14 in its deployed position, with the inner end portion 54 of the longitudinal strut 14 partially positioned inside the internal fitting channel 84 of the longitudinal strut fitting 12 (see FIG. 8) . In the embodiment of the "straight" longitudinal strut 14, when the longitudinal strut 14 is in its retracted position, the internal fitting channel 84 is partially exposed to the bypass duct 40 and thus generates aerodynamic drag. In contrast to the embodiment of the "rectilinear" longitudinal strut 14, the embodiments of the longitudinal strut 14 of the "bot-foot" type allow the longitudinal strut 14 to pivot about a pivot point which is situated behind ( that is, at the back of), and offset from, the axis of the shaft portion of the longitudinal strut 14 extending radially. Thus, when the longitudinal strut 14 of the "bot-foot" type pivots towards its extended position (see FIG. 9), it is not necessary for the internal fitting channel 84 of the longitudinal strut fitting 12 (see FIG. 8). extends rearwardly of the inner end portion 54 of the longitudinal strut 14 to allow the longitudinal strut 14 to pivot to its deployed position without striking the inside of the internal fitting base 82 of the longitudinal strut fitting 12 (see Figure 8). FIG. 11 shows that the internal fitting channel 84 does not extend towards the rear of the internal end portion 54 of the longitudinal strut 14. In the embodiments of the longitudinal strut 14 of the bot-foot type, the internal fitting channel 84 may be at least substantially covered by the inner end portion 54 of the longitudinal strut 14 when the longitudinal strut 14 is in a retracted position, which can eliminate the aerodynamic drag that may otherwise result from the fact that the Inner channel 84 is partially exposed to bypass duct 40. [0049] The position of internal fitting screw 92 shown in FIG. 10 is advantageous because the internal fitting screw 92 is not exposed to the bypass duct. 40 when the longitudinal strut 14 is in its retracted position. In the retracted position, the inner end portion 54 of the longitudinal strut 14 substantially covers the internal fitting screw 92 and thereby eliminates the aerodynamic drag that may otherwise result from the fact that the internal fitting screw 92 is positioned to be exposed to the conduit. bypass 40 when the longitudinal strut 14 is in its retracted position. The embodiment of the longitudinal strut 14 "twisted" shown in Figures 11 and 12 may have aerodynamic advantages over the embodiments of the longitudinal strut 14 "linear" shown in Figures 5-10. In some embodiments of the gas turbine engine 20, the secondary air flow 48 (see FIGS. 3 and 4) can pass through a portion of the bypass duct 40 in the vicinity of the longitudinal strut 14 in a flow direction which is not linear with (for example, non-parallel to) the axial center line 24 of the gas turbine engine 20. In such an embodiment, if a "linear" longitudinal strut 14 is used, the direction of flow the secondary air flow 48 may not be aligned with the axis extending between the leading edge and the trailing edge of the shaft portion of the longitudinal strut 14. This could in turn generate unacceptably high levels aerodynamic drag. The aerodynamic drag could be minimized by using instead a longitudinal strut 14 "twisted" so that the axis 56 (see Figure 12) extending between the leading edge and the trailing edge of the shaft portion the longitudinal strut 14 is aligned with the direction of flow of the secondary air flow 48.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A longitudinal strut assembly (10) for use in a thrust reverser (30) of a propulsion system (18), the thrust reverser (30) including a fixed structure (36) and a slide structure (38) ) which at least partially define an annular airflow bypass duct (40) therebetween, the sliding structure (38) being movable relative to the fixed structure (36), the sliding structure (38) including an inverting flap (46) disposed at least partially within the airflow bypass duct (40), the longitudinal strut assembly (10) comprising: a longitudinal strut fitting (12) attached to the fixed structure (36) the thrust reverser (30); and a longitudinal strut (14) having a first end portion (52) and a second opposite end portion (54), the first end portion (52) being pivotally coupled to the inverter flap (46), the second end portion (54) being pivotally coupled to the longitudinal strut fitting (12), and the second end portion (54) including a curved section.
    [0002]
    The longitudinal strut assembly of claim 1, wherein the thrust reverser (30) extends between a front end and a rear end along an axial center line (24), and the thrust reverser thrust (30) extends circumferentially about the axial centerline (24); wherein the fixed structure (36) of the thrust reverser (30) includes a radially inner fixed structure (37) and a radially outer fixed structure (39); and wherein the longitudinal strut fitting (12) is embedded within the inner fixed structure (37).
    [0003]
    The longitudinal strut assembly of claim 1, wherein the fixed structure (36) of the thrust reverser (30) includes a radially inner fixed structure (37) and a radially outer fixed structure (39); Wherein at least a portion of the longitudinal strut fitting (12) is disposed in a cavity (62) extending radially in the inner fixed structure (37), wherein the cavity (62) extends radially between an inner surface (68) of the inner fixed structure (37) and an opposite aerodynamic surface (66) of the inner fixed structure (37); and wherein the aerodynamic surface (66) partially defines the airflow bypass duct (40).
    [0004]
    A longitudinal strut assembly according to claim 1, 2 or 3, wherein a radially outermost surface (64) of the longitudinal strut fitting (12) is at least substantially radially aligned with an aerodynamic surface (66). ) of the internal fixed structure (37); and wherein the aerodynamic surface (66) partially defines the airflow bypass duct (40).
    [0005]
    The longitudinal strut assembly of claim 4, wherein the radially outermost surface (64) of the longitudinal strut fitting (12) is at least substantially flush with the aerodynamic surface (66).
    [0006]
    The longitudinal strut assembly of claim 1, wherein the thrust reverser (30) extends between a front end and a rear end along an axial center line (24), and the thrust reverser thrust (30) extends circumferentially about the axial centerline (24); wherein the longitudinal strut (14) extends at least substantially along a radially extending longitudinal strut axis (60); wherein a pivot point of the longitudinal strut (14) relative to the longitudinal strut fitting (12) is at the rear of the longitudinal strut axis (60) and offset therefrom.
    [0007]
    A thrust reverser (30) for a gas turbine engine propulsion system (18) for an aircraft, comprising: an inverting flap (46) which pivots between a retracted position and an extended position in which the inverting flap ( 46) redirects the air to generate the reverse thrust; a longitudinal strut fitting (12) attached to a fixed structure (36) of the thrust reverser (30) at least in part by a fastener; a longitudinal strut (14) having a first end (52) and a second distal end (54), the first end (52) being pivotally attached to the inverter flap (46), and the second end (54) being attached pivotally to the longitudinal strut fitting (12); and wherein the second end (54) of the longitudinal strut (14) is disposed at least partially in a channel (84) of the longitudinal strut fitting (12), and the fastener is disposed at least partially in the channel ( 84) and below the second end (54) of the longitudinal strut (14).
    [0008]
    A thrust reverser according to claim 7, wherein the fastener is at least substantially covered by the longitudinal strut (14) when the longitudinal strut (14) is in a first pivotal position with respect to the longitudinal strut fitting ( 12), and the fastener is at least partially exposed when the longitudinal strut (14) is in a second pivotal position with respect to the longitudinal strut fitting (12).
    [0009]
    A thrust reverser according to claim 7 or 8, wherein the channel (84) is at least substantially covered by the longitudinal strut (14) when the longitudinal strut (14) is in a first pivoting position with respect to the fitting longitudinal strut (12), and the channel (84) is at least partially exposed when the longitudinal strut (14) is in a second pivotal position with respect to the longitudinal strut fitting (12).
    [0010]
    A thrust reverser according to claim 7, 8 or 9, wherein the channel (84) is at least partially exposed to a bypass airflow duct (40) of the thrust reverser (30) when the longitudinal strut (14) is in a second pivoting position with respect to the longitudinal strut fitting (12).
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    同族专利:
    公开号 | 公开日
    FR3020412B1|2019-08-23|
    US10612490B2|2020-04-07|
    US20150308381A1|2015-10-29|
    引用文献:
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    US10294892B2|2016-04-18|2019-05-21|United Technologies Corporation|Blocker door link arm and fitting|
    US10480453B2|2016-09-07|2019-11-19|United Technologies Corporation|Hidden thrust reverser blocker door link arm fitting|
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    法律状态:
    2016-03-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-01-05| PLSC| Search report ready|Effective date: 20180105 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-03-25| PLFP| Fee payment|Year of fee payment: 5 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/262,393|US10612490B2|2014-04-25|2014-04-25|Drag link assembly including buried drag link fitting|
    US14262393|2014-04-25|
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