Abstract:
A cascade assembly is provided for installation in an aircraft nacelle. The cascade assembly comprises a first cascade portion fixed to a non-movable portion of the nacelle. The first cascade portion comprises a bracket. A second cascade portion is fixed to a translating sleeve portion of the nacelle. The second cascade portion comprises a catch. The bracket is configured to receive the catch in response to the translating sleeve portion being in a deployed position.

Description:
FIELD 
     The present disclosure relates to thrust reverser air management and, more particularly, to a system and apparatus for a split cascade. 
     BACKGROUND 
     Jet powered aircraft employ thrust reversers to reduce speed during aircraft landing. Thrust reversers generally exhaust fan air in the forward direction to create reverse thrust. Thrust reversers typically employ cascades to direct the exhausted fan air. 
     SUMMARY 
     In various embodiments, a cascade assembly comprising a first cascade portion and a second cascade portion may be installed in an aircraft nacelle. The first cascade portion may be fixed, attached or otherwise coupled to a non-movable portion of the nacelle. The first cascade portion may comprise a bracket. The second cascade portion may be fixed, attached or otherwise coupled to a translating sleeve portion of the nacelle. The second cascade portion may comprise a catch. In response to the translating sleeve being deployed (e.g., moved to the aft position when the thrust reverser is activated), the catch may receive the bracket, coupling the first cascade portion to the second cascade portion to form the cascade assembly. In various embodiments, the bracket may comprise an aperture. In various embodiments, the catch may comprise a hook. In various embodiments, the hook may be receivable in the aperture. 
     In various embodiments, a thrust reverser system capable of being installed in an aircraft nacelle may comprise a cascade and a blocker door system. The cascade may comprise a translating portion and a fixed portion. The translating portion may be coupled to a translating sleeve of a nacelle. The fixed portion may be coupled to a non-translating portion of the nacelle. In response to the translating sleeve being deployed, the translating portion and the fixed portion operatively couple to one another. The blocker door system may be configured to redirect airflow in a fan duct through the translating portion and the fixed portion. In various embodiments, the translating portion may comprise a bottom surface that defines a first plane. Similarly, the fixed portion may comprise a top that defines a second plane. In various embodiments, the first plane may substantially parallel to the second plane. In various embodiments, the first plane may be out of phase with the second plane. 
     In various embodiments, a nacelle comprises a translating sleeve, a translating cascade and a fixed cascade. The translating sleeve may be deployable between a stowed position and an active position. The translating cascade may comprise a first catch. The translating cascade may be mounted to the translating sleeve. The fixed cascade may comprise a second catch. The fixed cascade may be coupled to a non-moveable portion of the nacelle. In response to the translating sleeve being in the active position (e.g., moved aft), the first catch may engage the second catch to join the translating cascade with the fixed cascade. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The subject matter of the present disclosure is particularly pointed out and distinctly claimed in the concluding portion of the specification. A more complete understanding of the present disclosure, however, may best be obtained by referring to the detailed description and claims when considered in connection with the drawing figures, wherein like numerals denote like elements. 
         FIG. 1A  illustrates a cross-sectional view of an aircraft nacelle in a stowed configuration in accordance with various embodiments; 
         FIG. 1B  illustrates a side view of an aircraft nacelle and engine in a stowed configuration installed on an aircraft in accordance with various embodiments; 
         FIG. 2A  illustrates a cross-sectional view of an aircraft nacelle in a thrust reverser deployed configuration in accordance with various embodiments; and 
         FIG. 2B  illustrates a side view of an aircraft nacelle and engine in a thrust reverser deployed configuration installed on an aircraft in accordance with various embodiments. 
     
    
    
     DETAILED DESCRIPTION 
     The detailed description of exemplary embodiments herein makes reference to the accompanying drawings, which show exemplary embodiments by way of illustration and their best mode. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the inventions, it should be understood that other embodiments may be realized and that logical, chemical and mechanical changes may be made without departing from the spirit and scope of the inventions. Thus, the detailed description herein is presented for purposes of illustration only and not of limitation. For example, the steps recited in any of the method or process descriptions may be executed in any order and are not necessarily limited to the order presented. Furthermore, any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step. Also, any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact. 
     As used herein, “aft” refers to the direction associated with the tail (e.g., the back end) of an aircraft, or generally, to the direction of exhaust of the gas turbine. As used herein, “forward” refers to the directed associated with the nose (e.g., the front end) of an aircraft, or generally, to the direction of flight or motion. 
     In various embodiments, a split cascade system and apparatus (collectively, the “split cascade”) may reduce the package size of a cascade structure providing for additional clearance in the nacelle. More specifically the split cascade may comprise two or more cascade pieces. For example, the split cascade may comprise one or more fixed cascade elements. The split cascade may also comprise one or more translating cascade elements (e.g., moveable elements). The fixed cascade elements may be installed on a non-moveable portion of the nacelle housing. The translating cascade elements may be installed on a translating sleeve of the nacelle. In response to the translating sleeve being moved to an aft position (e.g., the position corresponding to the thrust reverser being activated), the translating cascade element may move aft and engage, couple or otherwise join the fixed cascade element creating a cascade assembly. The cascade assembly may direct fan air flow diverted to the cascade by a blocker door while the thrust reverser is activated (e.g., during landing or any other suitable aircraft slow down event). 
     Conventional cascades may comprise a single piece matrix of passages that are configured to direct air flow during a thrust reverse event. The single piece cascades have a relatively large package size (e.g., overall geometry and/or volume) that occupies volume in the nacelle. By reducing the package size (e.g., the stowed length), the split cascade provides more clearance in the nacelle. This additional clearance may provide for improved airflow, larger fan air ducts, smaller nacelles, space for plumbing or wiring, maintenance access, drag reduction, and/or the like. 
     In various embodiments, and with reference to  FIGS. 1A and 1B , nacelle  100  is shown in the stowed position (e.g., with the thrust reverser inactive and nacelle  100  is closed, as shown in  FIG. 1B ). Nacelle  100  may house or comprise a translating sleeve  110 , a fixed cascade  120 , a translating cascade  130  that is attached to translating sleeve  110 , a blocker door  140  and a fan air duct  150 . Split line  112  identifies the separation point or plane of translating sleeve  110  from non-moveable portion of the nacelle  100 . 
     In various embodiments, fixed cascade  120  may be mounted to a non-moveable portion of nacelle  100 . Fixed cascade  120  may be mounted in any suitable fashion such as, for example, a support  124 . Translating cascade  130  may be coupled to, attached to, fixed to, mounted to, or otherwise supported by translating sleeve  110 . For example, translating cascade  130  may be mounted on translating sleeve  110  by a bracket  134 . The bracket may be any suitable size, shape, configuration, and/or material. 
     In the stowed configuration (e.g., when nacelle  100  is closed as shown in  FIG. 1B ), translating cascade  130  may be stowed separately or apart from fixed cascade  120 . Translating cascade  130  may be stowed in any portion of nacelle  100 . 
     In various embodiments, and with reference to  FIGS. 2A and 2B , translating cascade  130  may comprise a catch  132 . Similarly, fixed cascade  120  may comprise a catch  122 . In response to translating sleeve  110  deploying (e.g., moved aft, as shown in  FIG. 2B ), catch  132  may engage or couple with catch  122 . In this manner, translating cascade  130  and fixed cascade  120  are coupled together to form a cascade assembly. Catch  132  and catch  122  may also be configured to align translating cascade  130  and fixed cascade  120 . 
     In various embodiments, catch  132  may be any suitable structure or portion of a structure configured to interlock to another structure. For example, catch  132  may be a hook, bracket, aperture, flange, and/or the like. Similarly, catch  122  may be any suitable structure or portion of a structure configured to interlock to another structure. For example, catch  122  may be a hook, bracket, aperture, flange, and/or the like. More specifically, in various embodiments, catch  132  and catch  122  may be configured as mating structures. For example, catch  132  and catch  122  may be complimentary, such that, they combine, interlock, couple, support, or otherwise mate with one another while translating sleeve  110  is in a deployed position, as shown in  FIG. 2B . 
     In various embodiments, translating cascade  130  and fixed cascade  120  may be aligned or otherwise deployed in a complimentary arrangement while translating sleeve  110  is in a deployed position. For example, an aft portion of fixed cascade  120  may generally define a plane. Similarly, a forward surface of translating cascade  130  may generally define plane. In the deployed position (e.g., translating sleeve  110  moved aft), the plane associated with fixed cascade  120  may align with the plane associated with translating cascade  130 . In this manner, fixed cascade  120  and translating cascade  130  may generally align to form a single, uniform cascade assembly to direct air when the thrust reverser is active. 
     In various embodiments, translating cascade  130  and fixed cascade  120  may be arranged in or otherwise deployed in a complimentary arrangement while translating sleeve  110  is in a deployed position. For example, a top portion of fixed cascade  120  may generally define a plane. Similarly, a bottom surface of translating cascade  130  may generally define a plane. In the deployed position (e.g., translating sleeve  110  moved aft), the plane associated with fixed cascade  120  may be substantially parallel with the plane associated with translating cascade  130 . In this manner, fixed cascade  120  and translating cascade  130  may be generally parallel with one another, but out of phase (e.g., not aligned, as shown in  FIG. 2A ). 
     In various embodiments, and in response to a thrust reverser system being activated, translating sleeve  110  may move aft, separating from nacelle  100  along split line  112 . The aft movement of translating sleeve  110  may cause translating cascade  130  to move aft and engage, couple, or otherwise join fixed cascade  120 , causing catch  132  to mate with, join, and/or otherwise engage catch  122 . The aft movement of translating sleeve  110  may also cause blocker door  140  to deploy into a fan duct  150 . Blocker door  140  is actuated in fan duct  150  in response to the aft motion of translating sleeve  110 , causing a drag link  142  retained in fan duct  150  by a bracket  144  to rotate blocker door  140  into fan duct  150 . Blocker door  140  at least partially seals and/or redirects air flow in fan duct  150  through the cascade assembly (e.g., fixed cascade  120  and translating cascade  130 ). 
     In various embodiments, fixed cascade  120  may be any suitable shape or size. Fixed cascade  120  may also be configured to direct or control the flow of fan air (e.g., when the thrust reverser is active) in any suitable fashion. Similarly, translating cascade  130  may be any suitable shape or size. Translating cascade  130  may also be configured to direct or control the flow of fan air (e.g., when the thrust reverser is active) in any suitable fashion. 
     In various embodiments, the split cascade described herein may be employed on, installed on, or otherwise used with any suitable nacelle, engine, and/or thrust reverser system. 
     Thus, in various embodiments, the split cascade described herein reduces the package size of the cascade structure, creating greater clearance in an aircraft nacelle. 
     Benefits, other advantages, and solutions to problems have been described herein with regard to specific embodiments. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent exemplary functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical system. However, the benefits, advantages, solutions to problems, and any elements that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the inventions. The scope of the inventions is accordingly to be limited by nothing other than the appended claims, in which reference to an element in the singular is not intended to mean “one and only one” unless explicitly so stated, but rather “one or more.” Moreover, where a phrase similar to “at least one of A, B, or C” is used in the claims, it is intended that the phrase be interpreted to mean that A alone may be present in an embodiment, B alone may be present in an embodiment, C alone may be present in an embodiment, or that any combination of the elements A, B and C may be present in a single embodiment; for example, A and B, A and C, B and C, or A and B and C. Different cross-hatching is used throughout the figures to denote different parts but not necessarily to denote the same or different materials. 
     Systems, methods and apparatus are provided herein. In the detailed description herein, references to “one embodiment”, “an embodiment”, “an example embodiment”, etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments. 
     Furthermore, no element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112, sixth paragraph, unless the element is expressly recited using the phrase “means for.” As used herein, the terms “comprises”, “comprising”, or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.