Abstract: An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes arranged in a longitudinally extending array. The vanes include a first vane and a second vane. A leading edge of the first vane is disposed on the cascade inner face. A leading edge of the second vane is recessed radially into the thrust reverser cascade from the cascade inner face.

Abstract: An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes and a wall. The vanes are arranged in a longitudinally extending array along the cascade inner face. The vanes include a first vane and a second vane. The wall is configured to block gas flow radially through the thrust reverser cascade between the first vane and the second vane.

Abstract: An apparatus is provided for an aircraft propulsion system. This apparatus includes a thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between a cascade inner face and a cascade outer face. The thrust reverser cascade includes a plurality of vanes and a wall. The vanes are arranged in a longitudinally extending array along the cascade inner face. The vanes include a first vane and a second vane. The wall is configured to block gas flow radially through the thrust reverser cascade between the first vane and the second vane.

Abstract: Aspects are directed to a system configured for use in connection with a thrust reverser of an aircraft, comprising: a first subset of cascade vanes having a first forward turning angle, and a second subset of cascade vanes having a second forward turning angle that is different from the first forward turning angle.

Abstract: Aspects of the disclosure are directed to a system associated with a thrust reverser of an aircraft, comprising: a plurality of cascade vanes configured in accordance with a substantially arc-tangent profile, where a leading edge of a first of the cascade vanes has a first width, and a trailing edge of the first of the cascade vanes has a second width that is different from the first width.

Abstract: A thrust reverser included in an aircraft nacelle includes an annular nacelle, a blocker door assembly, and a cascade assembly. The annular nacelle has an inner hollowed area defining a fan duct that extends longitudinally along an axis between an upstream inlet and a downstream outlet. The blocker door assembly is disposed in the fan duct and between the upstream inlet and the downstream outlet. The blocker door assembly is configured to selectively deploy a plurality of blocker doors that extend radially from the nacelle into the fan duct so as to form a plurality of air leakage paths that define a total leakage area (AL). The cascade assembly is circumferentially disposed upstream from the blocker door assembly. The cascade assembly including a plurality of vents that define an inner circumferential area (AC2) of the cascade assembly as a ratio (RC) with respect to the AL.

Abstract: Aspects of the disclosure are directed to a thrust reverser of an aircraft. Aspects are directed to a first array of cascades, a second array of cascades, and a sleeve configured to selectively block or unblock the first and second arrays of cascades. The sleeve may be configured such that when the thrust reverser is stowed a first portion of an interface associated with the sleeve is at a first axial location and a second portion of the interface is at a second axial location that is different from the first axial location. The first axial location may substantially coincide with a first circumferential positioning of the first array of cascades and the second axial location may substantially coincide with a second circumferential positioning of the second array of cascades.