• 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:
    CASCADE MOUNTING OF AIRCRAFT ENGINE THRUST REVERSE, AND AIRCRAFT ENGINE NACE. An aircraft engine thrust reverser cascade assembly includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes, including a rearmost vane, and rails defining a series of cells or passages and air between them. The cascade mount also includes a rear cascade ring detachably attached to the rear ends of the cascade segments. A flow deflection shelf is mounted on each of the cascading segments and includes a deflector portion which at least partially extends forward of a group of cells of the cascading segments along which the flow deflection shelf is mounted . The deflector portion is configured to, at least partially, redirect at least a portion of an air volume forward as the outward air passes through the cell group of the cascading segments.
    公开号:BR102012025979B1
    申请号:R102012025979-6
    申请日:2012-10-10
    公开日:2021-06-29
    发明作者:Michael Ray Aten；Sara Christiane Crawford
    申请人:Rohr, Inc；
    IPC主号:
    专利说明:

    TECHNICAL FIELD
    [0001] The report refers generally to thrust reversers for turboprop engine aircraft, and in particular refers to the cascade assembly of thrust reverser, including a flow deflection shelf, which reverses at least some of a flow turboprop engine fan annular in the forward direction when the associated cascade thrust reverser is employed. FUNDAMENTALS
    [0002] Modern aircraft turboprop engines include thrust reversers that selectively reverse the direction of an annular engine fan flow for use in decelerating an aircraft after landing. One type of thrust reverser for a turboprop engine includes a cascade arrangement mounted on a selectively enclosed outlet opening in an engine fan air duct. The cascading arrangement includes a plurality of spaced cascading vanes, which redirect fan airflow along the annular motor fan duct from a backward to an outward and forward direction when the thrust reverser is employed. Examples of various cascade type thrust reversers are described and shown in, for example, U.S. Patent No. 5, 309, 711; U.S. Patent No. 6, 170, 254; and U.S. Patent No. 6, 546, 715; all attributed to Rohr, Inc.
    [0003] Portions of a typical cascade type thrust reverser 10 for a 5 turboprop engine aircraft are shown in Figs. 1A - 1E. As shown in Figure 1A, cascade thrust reverser 10 includes a movable sleeve 16 which forms a rear portion of a nacelle surrounding the annular motor fan duct 13. The movable sleeve 16 is movable connected to the rear portion of a stationary portion. 12 of the nacelle. For normal backward fan flow through the motor fan duct 13, the movable sleeve 16 is positioned immediately behind the stationary portion 12 of the nacelle and limits the fan flow within the fan duct 13. As shown in Figures 1A-1C , when thrust reverser 10 is employed, movable sleeve 16 is moved rearwardly, thus providing an outlet opening 15 between stationary portion 12 and the forward end of movable glove 16. Outlet opening 15 typically extends over both the sides of an engine support pylon 7, and around a substantial portion of the circumference of the engine 5, and allows fan flow to be discharged from the annular engine fan duct 13 to provide reverse thrust to decelerate a landing aircraft. As shown in Figure 1C, a plurality of locking doors 18 near the forward end of the movable sleeve 16 are employed to block fan flow backward within the annular fan duct 13, and to force fan flow out of the motor through of the outlet opening 15.
    [0004] As shown in Figures 1A and 1B, a cascade assembly 20 is disposed within the outlet opening 15, and typically includes a plurality of circumferentially arranged cascade segments 28. As shown in Figure 1C, the cascade segments 28 include plurality of spaced vanes 25 configured to reverse fan output flow in an at least partially forward direction in order to provide reverse thrust. The vanes 25 are typically supported between a plurality of longitudinal support members 26. The rear ends of the cascade segments 28 are interconnected by a cascade rear ring 30 which secures the cascade segments 28 together, and secures the cascade assembly 20 against outward deflection. As shown in Figure 1D, the rear end of each cascade segment may include a flange end 29, and may be connected to the rear cascade ring 30 by a plurality of removable fasteners 21.
    [0005] In the embodiment shown in Figures 1C and 1D, the rear cascade ring 30 includes an outer portion 36 and an inner portion 34 which are each connected to opposite ends of a body portion 32 at right angles. The substantially Z-shaped cross-section of the rear cascade ring 30 provides the ring with substantial bending and torsional stiffness, although all portions 32, 34 and 36 of the ring are relatively thin. As also shown in Figures 1C and 1D, a rear vane 27 in each cascade segment 28 defines the rearmost measurement 11 of the exhaust flame as the redirected fan flow exits the outlet opening 15. As shown in Figure 1D, the rear vane 27 is positioned in front of the rear cascade ring 30, and the rear cascade ring 30 is positioned behind the rearmost measurement 11 of the exhaust flame by a distance "a". Consequently, the rear cascade ring 30 has no substantial or direct effect in reversing the outflow of the fan once the flow passes through the outflow opening 15.
    [0006] Another configuration of a known back cascade ring 60 is shown in Figure 1E. In this arrangement, each cascade segment 58 includes a rearward extension 52 for connecting to a frontward extension 63 of a rear cascade ring 60 with a plurality of removable fasteners 21. The rear cascade ring 60 generally includes a portion of body 69 and opposing outer and opposite portions 67, 65. Again, the cross-sectional shape of ring 60 provides substantial rigidity, although individual portions 63, 65, 67 and 69 of ring 60 are relatively thin. As shown in Figure 1E, the rearmost vane 57 is positioned forward of the ring 60, and the ring 60 is positioned behind the rearmost measurement 11 of the exhaust flame by a substantial distance "b". Consequently, like the rear cascade ring 30 described above, the ring 60 has no substantial or direct effect in reversing the fan outflow as soon as the flow passes through the outflow opening 15.
    [0007] Although the rear cascading rings 30, 60 described above can be used to securely and rigidly connect the rear ends of the thrust reverser cascading segments, they have some shortcomings. First, as discussed above, the rear cascade rings 30, 60 play no substantial or direct role during fan outflow and are thus therefore accessories to the primary function of their cascade assemblies 20, 50. Second, because the rear cascade rings 30, 60 are positioned behind the rearmost cascade vanes 27, 57, the rear cascade rings 30, 60 add to the overall length of the cascade mounts 20, 50 as well as add extra weight to the cascades 20, 50 without directly contributing to its air yaw function. Consequently, at least for these reasons, there is a need for an improved thrust reverser cascade assembly with an improved rear cascade ring, which directly contributes to the cascade assembly's air yaw function as well as its function. primary to provide structural support for the rear end of the cascading arrangement. This definitely reduces the overall length and weight of the cascade mount. SUMMARY
    [0008] In one embodiment, a cascade assembly of an aircraft engine thrust reverser includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes, including a further rearward vane and a rear end. The cascade assembly may additionally include a flow deflection shelf which forms a tail or rear end of the cascade segment and detachably couples to a rear cascade ring. The flow deflection shelf generally includes a vertical wall or body portion and a deflector portion that extends forwardly away from the rear end of the cascade segment. The deflector portion of each flow deflection shelf can be configured to at least partially redirect, in the forward direction, at least a portion of the fan air flow volume as the air flow passes through the rearmost cells or passageways. defined air flow between the rearmost vanes of the cascade segment and the body of the flow deflection shelf. The vertical wall or body portion of each deflection shelf may define a rear connection area of each cascade segment to allow coupling of a rear cascade ring to the rear end of the cascade assembly.
    [0009] In another embodiment, the cascade assembly of an aircraft engine thrust reverser may have a plurality of cascaded segments, each including a plurality of spaced vanes and support rails defining cells or flow passages. air between them, and at least one flow deflection shelf mounted along a forward intermediate section and further aft ends of the cascading segment. In such an embodiment, the flow deflection shelf may include a substantially longitudinally projecting deflector portion which may be mounted to an intermediate cascade vane or may be formed with a body section defining the intermediate cascade vane. The deflector portion extends ahead of the intermediate cascade vane, at least partially overlying a series of intermediate cells and is configured to redirect, in the forward direction, at least one of the air passages through the forward cascade segment of the deflection shelf. flow. The flow deflection shelf can extend laterally to define a rim support structure around the cascade assembly, aiding in the secure connection of the cascading segments and allowing for a reduction in size and weight required for the cascade ring. rear mounted on the rear end of the cascade mount.
    [00010] These and other aspects and features of the invention will be understood when considered in connection with the following detailed descriptions, together with the drawings. Those skilled in the art will further appreciate the advantages and benefits of the various embodiments discussed herein after reading the following detailed descriptions of the embodiments with reference to the drawings listed below.
    [00011] In accordance with common practice, the various features of the drawings discussed below are not necessarily drawn to scale. Dimensions of various features and elements in the drawings may be expanded or reduced to more clearly illustrate embodiments of the invention. BRIEF DESCRIPTION OF THE DRAWINGS
    [00012] Figure 1A is a perspective view of a prior art turboprop aircraft engine with a cascade type thrust reverser employed.
    [00013] Figure 1B is a perspective view of the prior art cascade type thrust reverser shown in Figure 1A.
    [00014] Figure 1C is a partial cross-sectional view of the prior art cascade type thrust reverser shown in Figures 1A and 1B. 1A and 1B taken along line C-C in Figure 1B.
    [00015] Figure 1D is a partial cross-sectional view of the prior art cascade type thrust reverser shown in Figure 1C, showing the rear end of the cascade arrangement and a prior art cascade rear ring.
    [00016] Figure 1E is a partial cross-sectional view like that of Figure 1D, showing the rear end of the cascading arrangement and another type of prior art cascade rear ring.
    [00017] Figure 2A is a partial cross-sectional view of a thrust reverser in a tidy configuration, which includes an embodiment of a cascade assembly with a flow deflection shelf according to the invention.
    [00018] Figure 2B is a partial cross-sectional view of the thrust reverser shown in Figure 2A, with the movable sleeve in an employed position.
    [00019] Figure 3A is a perspective view of an embodiment of a cascade segment of the cascade assembly with a flow deflection shelf according to the invention.
    [00020] Figure 3B is a partial cross-sectional view of the rear end of the cascade assembly with a flow deflection shelf of the thrust reverser shown in Figures 2A - 3A.
    [00021] Figure 4A is a perspective review of another embodiment of a cascade segment of the cascade assembly, with a flow deflection shelf according to the present invention.
    [00022] Figure 4B is a cross-sectional view of the cascade segment shown in Figure 4A.
    [00023] Figure 5 is a perspective view of a rear cascade ring for coupling to the rear ends of the cascade segments of the cascade assembly.
    [00024] Corresponding parts are designated by corresponding reference numbers in all drawings. DETAILED DESCRIPTION
    [00025] An embodiment of a thrust reverser 200 including an embodiment of a cascade assembly 100 and with flow deflection shelf 100, according to the invention is shown in Figures 2A and 2B. Thrust reverser 200 generally includes a movable sleeve 16 movably coupled to the rear end of a stationary portion 12 of a nacelle. In Figure 2A, the movable glove 16 is shown in a retracted or stowed position, with locking door(s) 18 stowed in a position adjacent to the interior surface of the movable glove. In Figure 2B, the movable glove 16 is shown in an employed position. In the employed position, the locking door(s) 18 are extended within a fan duct 13 to block fan flow through the duct 13. As also shown in Figure 2B, employment of the movable sleeve 16 opens an outflow passage. of air 15 in the nacelle structure, and exposes the cascade assembly 100 disposed within the outlet passage 15.
    [00026] The cascade assembly 100 includes a plurality of cascade segments 102. As indicated in Figures 2A - 3A, each cascade segment 102 includes a body 103, having longitudinally extending support ribs or rails 104 and a plurality of vanes spaced generally laterally extending 105, each configured to reverse the flow of air being exhausted through the outlet passage 15 (Figures 2A - 2B) toward at least one partially forward direction. Cascade segments 102 also include more rearward vanes 107. Vanes 105 generally have a concave, curved configuration, although other configurations may also be provided. As shown in Figures 3A and 4A, each cascade segment 102 includes a trailing or recessed end 108, a forward end 109, and a series of cells or flow passages 106 defined between support rails 104 and spaced vanes 105. The end 109 of each cascade segment 102 is generally detachably connected to one or more flanges 14 at the rear end of stationary portion 112 of the nacelle structure. The forward end of each cascade segment 102 may be connected to the flange or flanges 14 by one or more removable fasteners 23 of a type or types known in the art.
    [00027] In an embodiment of the cascade mount 102 illustrated in Figures 3A - 3B, the rear end 108 of each cascade segment 102 may include a flow deflection shelf 110 which is mounted to the rear ends of the support rails 104 in a position spaced from the rearmost vanes 107. The flow deflection shelf 110 may be mounted to the rear end of its associated cascade segment, such as by fasteners, adhesives, solders or other couplings or other joining features, as understood by those skilled in the art. Each flow deflection shelf 110 can be formed of a light weight, substantially rigid and high strength material, including various metals or metal alloys, such as aluminum, titanium, steel or similar metal materials, or it can be formed from various composites. of high strength or synthetic materials. As shown in Figures 3A - 3B, the flow deflection shelf 110 has a substantially orthogonal, L-shaped configuration including a generally longitudinally oriented, forward-extending deflector portion 112 and a vertical body or wall portion 113. Other configurations are within the scope of the invention, such as configurations that are not perfectly orthogonal.
    [00028] Figure 3B shows an enlarged detail of a rear end 108 configuration of a cascade segment 102 of the cascade assembly 100 embodiment described above. In this embodiment, the rear end of each cascade segment 102 to which the cascade rear ring 102 mounts is defined by a body or vertical wall portion 113 of the flow deflection shelf 110. The body portion 113 thereof embodiment is generally configured to provide a substantially flat or recessed rear wall to the rear end of each cascade segment and is axially spaced further behind the rearmost vanes 107 so as to define rear cells or air passages 114 for each segment in waterfall. As shown in Figure 3A, the vanes 105, including the rearmost vanes 107 and the body portion 113 of the flow deflection shelf of each segment 102, can be supported by two or more spaced apart and longitudinally extending support rails 104. providing space between the rearmost vane 107 and the flow deflection shelf 110, flow from the fan outlet may pass through the rearmost cells or air passages 114 between them, as indicated in Figure 3B by the dashed arrow 115.
    [00029] Additionally, in the present embodiment, as indicated in Figure 3B, the deflector portion extending forward 112 of the flow deflection shelf 110 is shown as oriented at a 90° angle relative to its body portion 113 , although it will be understood that the deflector portion may also be oriented at greater or lesser angles. In embodiments using the 90° angle configuration, the deflector portion 112 of the flow deflection shelf 110 is closely spaced from and generally oriented substantially flush with the upper edges of the support rails of its associated cascade segments. Optionally, the deflector portion 112 of each flow deflection shelf 110 has an arcuate configuration that closely matches the arcuate configuration of its associated cascade segment, over the entire width of the segment. In this way, the deflector portion 112 confines the body 103 of each cascading segment, thereby forming a supporting ring structure that provides structural support to the cascading segments in their connected configurations.
    [00030] The body portion 113 of the flow deflection shelf 110 includes a flat rear end wall 113, thereby defining a substantially flat mounting surface 117 for coupling a rear cascade ring 120 to the rear end of each cascade segment . By the provision of such a flat wall 113 and its associated flat mounting surface 117, the rear cascade ring 120 is in flatly disposed or flush mounting support contact with the body portion of the flow deflection shelf, thereby placing the rear cascade ring in a tighter fit, closer to the rear ends of the cascading segments compared to prior art structures. This can significantly reduce the amount of longitudinal space required within the nacelle for the rear cascade ring when mounted to the cascading segments, and consequently provide increased clearance for operation of the thrust reverser and cascade structure.
    [00031] An embodiment of a rear cascade ring 120 for use with a cascade assembly 100 as described above is generally shown in Figures 2A - 2B and 5. As shown in Figure 5, although the rear cascade ring 120 is referred to herein as a "ring", the cascading rear ring 120 may be constructed in two or more arcuate portions which may not combine to form a full 360 degree ring structure. For example, rear cascade ring 120 may include two or more arcuate portions or sections 120a, 120b that are mirror images of both, each including a body portion 122, a "deflector" or outer portion 126, and a portion. internal 124. In the embodiment shown in Figure 5, the body portion 122 is substantially flat, and rests in a plane that is substantially transverse to the longitudinal axis of an associated aircraft engine, with a plurality of mounted holes or openings 123 for use in removable attachment of ring 120 to cascading segments 102. Inner portion 124 of ring 120 may be substantially cylindrical in shape, and may extend behind an inner edge of body portion 122, with inner portion 124 arranged substantially perpendicular to the body portion 122.
    [00032] In prior art structures, as shown in Figure 1D, the cascading segments often require an additional set back wall that is mounted behind the rearmost vane (indicated at 27) to allow connection of the rear cascade ring to the set segments. waterfall. Alternatively, as indicated in Figure 1E, if the rearmost vane 57 of the cascading segments comprises the set back or rear wall of the cascading segments, the curved construction of the vanes generally requires that the cascade ring be connected to the rearmost vanes of the cascading segments. cascade by horizontally extending flanges 52 and 63 coupled by means of fasteners 21. In addition, to significantly reduce horizontal space and allow for a closer fit and fit between the cascade ring and the rear end of the cascade segments to which it is coupled , the present invention eliminates the need for such coupling flanging, as shown in Figure 1E, and the requirement for an additional rear wall portion as shown in Figure 1D. This, in turn, helps to provide significant weight savings and allows the rear cascade ring to be formed in varying sizes (eg, made taller) as needed to increase the aerodynamic operation of the thrust reverser.
    [00033] As indicated in Figure 3B, the body portion 113 of each flow deflection shelf 110 may be removably connected to the rear cascade ring 120, such as by one or more removable fasteners 125 of a type or types known in the art . For example, the rear end of each cascade segment 102 may be removably connected to the rear cascade ring 120 by one or more sets of nuts and bolts, or may be more permanently coupled such as by rivets, etc. The connection of the rear cascade ring 120 to the body portion 113 of the flow deflection shelf 110 by fasteners 125 extends in a forward direction through the body of the rear cascade ring of the flow deflection shelves. This longitudinal connection aligns the fasteners in a shear load orientation to provide added force, as opposed to a tension loaded coupling, such as created by the connection illustrated in the prior art framework of Figure 1E. Coupling the rear cascade ring 120 to the cascade segments secures the rear ends 108 of the cascade segments 102 together, adds rigidity to the cascade assembly 100, and restricts outward deflection of the cascade segments 102 when the cascade segments 102 are exposed to high velocity air flow passing through the outlet passage 15. The flow deflection shelf 100 can additionally assist in providing structural continuity and support for the connected cascade segments, which in turn can allow for a reduction in size , and so weight of the rear cascading ring.
    [00034] In operation, as the thrust reverser is*, the fan airflow is externally directed towards the airflow cells or passages 106 and 114 defined between the vanes and support rails of the cascading segments. The substantially curved or arcuate configuration of the vanes forces the airflow to be redirected in the forward direction to provide reverse thrust. The rearmost air flow, indicated by dashed lines 115 in Figure 3B, flows into the rearmost cells 114 and is directed substantially forward by impact against the lower surface of the deflector portion 112 of the flow deflection shelf 110.
    [00035] The rear cascade ring 120 may additionally include an angled deflector portion 126 which extends forward at a desired angle to aid in deflection of the more rearward airflow. As shown in Figures 3B and 5, the deflector portion 126 of an embodiment of the rear cascade ring 120 may generally extend toward the outer edge of the body portion 122. The deflector portion 126 may extend at an angle "0" relative to body portion 122. In the embodiment shown, the angle "0" between deflector portion 126 and body portion 122 is less than 90 degrees. In one embodiment, the "0" angle is between about 60 degrees and about 90 degrees, although angles less than 60 degrees can also be used. In an embodiment of the rear cascade ring 120, the deflector portion 126 may have a substantially frusto-conical shape having a larger diameter at its forward edge. Alternatively, the deflector portion 126 may have other shapes, such as a substantially arcuate shape. This deflector portion 126 may also be of an extended length, and is generally of a longer length than the deflector portion 112 of the flow deflection shelf 110 against which it is mounted, so as to substantially overlap the deflector portion 112 of the shelf. of flow deflection 110 and additionally help reverse air flow forward during reverse thrust operation.
    [00036] In a further embodiment of the cascade assembly 100 illustrated in Figures 4A and 4B, a flow deflection shelf 210 may be mounted along an intermediate portion 211 of an associated cascade segment 102, spaced axially forward of the rearmost vanes of the cascade segment and rear cascade ring 120. In this embodiment, the flow deflection shelf 210 may include a deflector portion 212 that is mounted to the upper end of an intermediate vane 213 of its associated cascade segment , or alternatively, may be formed integrally as a unitary structure with the intermediate vane, where the intermediate vane 213 defines a body portion of the flow deflection shelf. In this embodiment, the deflector portion 212 of each flow deflection shelf 210 will generally comprise a substantially longitudinally oriented projection or shelf that will extend forwardly, at least partially resting on or covering the intermediate cells or flow passages 214 located directly. in front of the flow deflection shelf. The deflector portion 212 is preferably integral with the intermediate vanes 213 and redirects at least a portion of the volume of an air flow 215 passing through it in a forward direction. Additionally, in the construction of the flow deflection shelf, where the flow deflection shelf is integrally formed with the intermediate vane 213 of its associated cascade segment, the flow deflection shelf may also include a vertically extending body portion, substantially direct, or also a wall.
    [00037] As further illustrated in Figure 4B, each cascade segment 102 may typically include a substantially flat set-back wall portion, which may be formed of a lightweight material, and to which the rear cascade ring 120 is coupled by means. of fasteners 221, with the fasteners being generally oriented in a *. The deflector portions of the flow deflection shelves by each of the cascading segments will extend laterally through their associated cascading segments, and will be arranged in an * against the upper edges of the rails and intermediate vanes. The ends of these deflector portions can be connected in series to define or help provide an * that extends over the cascading segments. Such a construction provides improved structural continuity for the coupled cascading segments, effectively forming a structural band or * that can help secure the cascading segments together. By providing this additional continuity frame or structure* for the cascading segments, the rear cascading ring can be reduced in size and thus reduced in weight, as some of the structural loads to keep the cascading segments connected in series has been taken over by flow deflection shelf. Such a reduction in size and weight of the rear cascading ring can offset any additional weight from the addition of wall sections of the cascading segments to which the rear cascading ring is attached.
    [00038] Still further, it will be understood by those skilled in the art that a plurality of flow deflection shelves can be used with the cascading segments formed in accordance with principles of the present invention. For example, a first flow deflection shelf can be mounted at the rear end of its associated cascade segment, as illustrated in Figures 3A and 3B, to provide a substantially flat connecting surface for the rear cascade ring and provide the desired redirection. of air flowing through the rearmost cells or air passages 114. In addition, one or more additional flow deflection shelves can be mounted at various intermediate locations along the length of the cascading segments with these additional flow deflection shelves being generally spaced towards the front from the rear mounted flow deflection shelf. The use of the intermediate flow deflection shelves can additionally provide the desired improvements in structural continuity for the cascade arrangement, while also allowing the flow deflection shelves and/or the rear cascade ring to be made of lightweight materials for help reduce the overall size of the cascade assembly, without an undesirable reduction in the structural strength and brace continuity of the coupled cascade segments.
    [00039] The use of one or more flow deflection shelves 110 in accordance with the principles of the present invention can thus help to minimize the weight of the cascade assembly by allowing the thickness or thicknesses of the body portion 122 of the portion inner 124, outer portion 126 and any other portions of the rear cascade ring are substantially minimized. The present invention can further facilitate the use of varied configuration and size of the rear cascade rings which can additionally help to substantially reduce the length and weight of the cascade assembly 100. In addition, the transverse shape of the rear cascade ring 120 can be configured to provide adequate stiffness against bending and twisting, while also minimizing weight. For example, rear cascade ring 120 can be constructed of composite materials in one piece using known composite manufacturing processes. Alternatively, the rear cascade ring 120 can be constructed of strong and light weight material or combination of materials such as aluminium, titanium, composites or the like, and can also be constructed in one piece, or fabricated by joining the pieces together. multiple or joined sections.
    [00040] The embodiments of the invention described above are intended to illustrate various features and aspects of the invention. Persons skilled in the art will recognize that various changes and modifications can be made to describe embodiments without departing from the invention. For example, although various embodiments of a rear cascade ring have been described as having particular transverse shapes and specific portions, a rear cascade ring according to the invention may include various transverse shapes and/or portions which are different from the modes. of embodiments specifically described. All such changes and modifications are intended to be within the scope of the appended claims.
    权利要求:
    Claims (14)
    [0001]
    1. An aircraft engine thrust reverser cascade assembly comprising: (a) a plurality of circumferentially spaced cascade segments (28), each cascade segment (28) including a front end, a rear end, and a plurality of spaced apart ribs and vanes (25) defining a series of air passages therebetween, and with the vanes including a rearmost vane; characterized in that it comprises: (b) a flow deflection shelf (110) mounted to the along the rear end of each cascade segment (28), the flow deflection shelf mounted (110) perpendicular to the rearmost vanes and configured to at least partially redirect at least a portion of the air passing through each cascade segment. (28) forward as air passes out between the rearmost vanes and the rear end of each cascade segment (28); and (c) a rear cascade ring (30) comprising a body portion and a deflector portion, the body portion coupled to each cascade segment (28) and the position of the deflector portion to form an angle of less than 90 degrees with respect to the flow deflection shelf (110).
    [0002]
    2. Aircraft engine thrust reverser cascade assembly according to claim 1, characterized in that the deflector portion comprises a shelf extending at least partially forward over the air passages between the rearmost vanes and the body portion of the flow deflection shelf (110).
    [0003]
    3. An aircraft engine thrust reverser cascade assembly according to claim 1, characterized in that the body portion of the flow deflection shelf (110) defines a rear wall of each cascade segment (28).
    [0004]
    4. Aircraft engine thrust reverser cascade assembly according to claim 1, characterized in that the rear cascade ring (30) additionally includes a body portion having an inner portion adjacent and connected to the body portion of the flow deflection shelf (110).
    [0005]
    5. Aircraft engine nacelle with a thrust reverser cascade assembly, comprising: (a) a plurality of circumferentially spaced cascade segments (28), each cascade segment (28) comprising a series of rails and vanes spaced (25), including a rearmost vane, spaced rows of air flow passages defined between the rails and vanes, and a rear end; characterized in that it comprises: (b) a rear cascade ring (30) coupled to the rear end of each cascade segment (28) with a plurality of fasteners, the rear cascade ring (30) comprising a body and a deflector portion; and (c) an airflow deflector mounted on at least a portion of the rearmost vane and between the rearmost vane and the baffle portion, the airflow baffle at least partially overlapping perpendicularly to a rearmost row of airflow passages for redirecting at least a portion of the air passing to the outside through the selected row of airflow passages.
    [0006]
    6. Aircraft engine nacelle according to claim 5, characterized in that the air flow deflector comprises at least one flow deflection shelf (110) mounted in at least one cascade segment (28) and including a deflector portion positioned behind the rearmost vane and wherein the deflector portion extends forward from the rear end of the at least one cascade segment (28), and a body portion defining a flat rear end wall to which the ring cascades rear (30) is coupled in a flush mounted arrangement.
    [0007]
    7. Aircraft engine nacelle according to claim 6, characterized in that the deflector portion has a flat configuration extending forwards, at least partially superimposed on a row of rearmost airflow passages defined between the vane rearmost of the at least one cascade segment (28) and the body portion of the flow deflection shelf (110).
    [0008]
    8. Aircraft engine nacelle according to claim 5, characterized in that each flow deflection shelf (110) is connected in series to define a rim structure extending around and supporting the cascading segments (28) to form the cascade assembly.
    [0009]
    9. Aircraft engine nacelle according to claim 5, characterized in that the rear cascade ring (30) comprises at least two arcuate ring segments.
    [0010]
    10. Cascade assembly for an aircraft engine thrust reverser, comprising: (a) a plurality of cascade segments (28) connected in series, each of the cascade segments (28) including a rear end, a front end , a series of longitudinally extending rails, a series of laterally extending vanes, including a rearmost vane connected to the rails, and a plurality of rows of airflow passages defined between the rails and the vanes; :(b) a rear cascade ring (30) comprising a body portion and a flow deflection portion mounted at the rear end of each cascade segment (28), the body portion configured to couple and maintain the cascade segments (28) connected in series and the flow deflection portion configured to at least partially direct a flow of discharge air through a rear row of air flow passages; and (c) a plurality of flow deflection shelves, each mounted between each of the segments and the rear cascade ring (30) and including a forwardly extending deflector portion that at least partially overlaps a row. of air flow passages so as to redirect at least a portion of air passing through the selected row of air passages.
    [0011]
    11. Cascade assembly according to claim 10, characterized in that each of the flow deflection shelves is mounted adjacent to the rear end of an associated cascade segment (28) spaced rearward from the rearmost vane of the associated cascade segment (28).
    [0012]
    12. Cascade assembly according to claim 11, characterized in that each of the flow deflection shelves further comprises a vertical body portion defining a flat rear wall of its cascade segment (28) associated with which the ring in rear cascade (30) is coupled in a flush mounting arrangement.
    [0013]
    13. Cascade assembly according to claim 10, characterized in that each of the flow deflection shelves is mounted along the rear ends of the cascade segments (28), spaced behind the rearmost vane of each of the cascading segments (28) and defining a flat rear wall to which the rear cascading ring (30) is coupled in a flush mounted arrangement.
    [0014]
    14. Cascade assembly according to claim 10, characterized in that the flow deflection shelves are connected in series to define a support ring structure to connect the cascade segments (28) in series.
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    US20140250863A1|2014-09-11|Rear mounted reverse core engine thrust reverser
    US20140252167A1|2014-09-11|Reverse core engine thrust reverser for under wing
    US4858430A|1989-08-22|Thrust reverser for a turbofan engine
    JP5215157B2|2013-06-19|Aircraft jet engine intermediate casing with improved design
    ES2400729T3|2013-04-11|Connection system between an internal structure and an external structure of a turbojet gondola
    US20150121896A1|2015-05-07|Reverse core flow engine mounting arrangement
    ES2438511T3|2014-01-17|Front frame for a thrust inverter structure with deflection grilles
    CA2638860C|2015-08-04|Thrust reverser door
    RU2717173C2|2020-03-18|Rear frame for thrust reverser, aircraft thrust reverser for aircraft nacelle and nacelle, equipped with such thrust reverser
    US10759541B2|2020-09-01|Nacelle bifurcation with leading edge structure
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    CN103047048B|2016-11-30|There is the reverse thrust unit leaf grating assembly flowing to deflection rack
    同族专利:
    公开号 | 公开日
    CA2792065A1|2013-04-13|
    US20130092755A1|2013-04-18|
    US9086034B2|2015-07-21|
    EP2581593A3|2017-10-11|
    EP2581593A2|2013-04-17|
    BR102012025979A2|2013-11-12|
    CN103047048A|2013-04-17|
    EP2581593B1|2020-05-06|
    CA2792065C|2019-09-03|
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    法律状态:
    2013-11-12| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2013-12-24| B03H| Publication of an application: rectification [chapter 3.8 patent gazette]|
    2018-12-11| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2020-01-21| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-05-04| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-06-29| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 10/10/2012, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US201161546737P| true| 2011-10-13|2011-10-13|
    US61/546737|2011-10-13|
    US13/308,865|US9086034B2|2011-10-13|2011-12-01|Thrust reverser cascade assembly with flow deflection shelf|
    US13/308865|2011-12-01|
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