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US 5,507,143 AGranted
Cascade assembly for use in a thrust-reversing mechanism
AssigneeThe Boeing Company
InventorsClint A. Luttgeharm, Marty J. Todd, John M. Welch
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AssigneeThe Boeing Company
InventorsClint A. Luttgeharm, Marty J. Todd, John M. Welch
Estimating the term…
A cascade assembly (14) for use in a thrust reversing mechanism (16) of a jet engine (18) includes at least one group of substantially identically-shaped cascade elements (28) each in the shape of a predefined polygon. The cascade elements (28) are positioned in an array, wherein each cascade element (28) in the group may be interchanged in a location in the array with any other cascade element (28) in the group. In a first preferred embodiment, the predefined polygon is a regular polygon and each cascade element (28) is rotatable in its array position about an axis generally normal to the cascade element (28). The array substantially approximates sections of two intersecting spheres, wherein a central axis of the array is generally coincident with the longitudinal axis of the jet engine (18). The cascade elements (28) are supported in the cascade assembly (14) by a truss structure (30) having a framework defining openings (32) in the shape of the predefined regular polygon for receiving the cascade elements (28).
A cascade assembly for use in a thrust-reversing mechanism of a jet engine, comprising at least one group of substantially identically-shaped cascade elements, each cascade element in the group having an outer periphery approximating the shape of a predefined polygon, and each cascade element including a plurality of vanes, the cascade elements being positioned in an array, wherein each cascade element in the group may be interchanged in a location in the array with any other cascade element in the group, and wherein the array comprises at least two circumferentially extending rows of cascade elements, one row positioned longitudinally aft of another row, wherein the cascade elements in the group comprise two different types, a first type having the plurality of vanes arranged in a first pattern and a second type having the plurality of vanes arranged in a second pattern.
A cascade assembly for use in a thrust-reversing mechanism of a jet engine, comprising at least one group of cascade elements, each cascade element in the group having an outer periphery approximating the shape of an equilateral triangle, and each cascade element including a plurality of vanes.
A cascade assembly for use in a thrust-reversing mechanism of a jet engine, comprising at least one group of cascade elements, each cascade element in the group having an outer periphery approximating the shape of a triangle, and each cascade element including a plurality of vanes, the cascade elements being positioned in an array, which substantially approximates sections of at least two intersecting hollow multi-faceted polyhedrons, the array having a central axis generally coincident with the longitudinal axis of the jet engine, the cascade elements being supported by a truss structure forming part of the cascade element, wherein the truss structure comprises a framework defining a plurality of openings in the shape of the triangles, wherein the openings are adapted to receive and support the cascade elements.
A cascade assembly for use in a thrust-reversing mechanism of a jet engine, comprising at least one group of cascade elements, each cascade element in the group having an outer periphery approximating the shape of a triangle, and each cascade element including a plurality of vanes, the cascade elements being positioned in an array, which substantially approximates sections of at least two intersecting hollow multi-faceted polyhedrons, the array having a central axis generally coincident with the longitudinal axis of the jet engine, wherein the cascade elements in the group comprise two different types, a first type having the plurality of vanes arranged in a first pattern and a second type having the plurality of vanes arranged in a second pattern.
A cascade assembly for use in a thrust-reversing mechanism of a jet engine, comprising at least one group of cascade elements, each cascade element having an outer periphery approximating a predefined regular polygon, and each cascade element having a plurality of vanes, the cascade elements in the group being of two different types, a first type having a set of vanes arranged in a first pattern and a second type having a set of vanes arranged in a second pattern.
Dependencies are inferred from the claim text.