Thrust reverser cascade with offset vane leading edges

An apparatus for an aircraft propulsion system, comprising:

• a propulsion system structure extending along an axial centerline including a nacelle having a fixed structure, a flowpath and a thrust reverser system, the flowpath extending within the propulsion system structure to an exhaust nozzle, and the thrust reverser system comprising a thrust reverser cascade and a thrust reverser door, the thrust reverser cascade fixed to the fixed structure;
• the thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end, the thrust reverser cascade extending laterally between a cascade first side and a cascade second side, the thrust reverser cascade extending radially between a cascade inner face and a cascade outer face which is angular offset from the cascade inner face in a reference plane, the cascade inner face configured with a straight sectional geometry in the reference plane as the cascade inner face extends longitudinally from the cascade forward end to the cascade aft end, and the cascade outer face configured with a straight sectional geometry in the reference plane as the cascade outer face extends longitudinally from the cascade forward end to the cascade aft end;
• the thrust reverser cascade including a plurality of vanes distributed longitudinally along the cascade inner face, the plurality of vanes comprising a first vane and a second vane, the first vane extending radially to a first vane leading edge, the second vane extending radially to a second vane leading edge, and the first vane leading edge and the second vane leading edge are radially misaligned along the cascade inner face;
• and
• the thrust reverser door configured to pivot between a stowed position and a deployed position, a first portion of the thrust reverser door radially outboard of and axially covering the thrust reverser cascade when the thrust reverser door is in the stowed position, and a second portion of the thrust reverser door forming a radial outer peripheral boundary of the flowpath between the thrust reverser cascade and the exhaust nozzle when the thrust reverser door is in the stowed position.

An apparatus for an aircraft propulsion system, comprising:

• a propulsion system structure extending along an axial centerline including a nacelle having a fixed structure, a flowpath and a thrust reverser system, the flowpath extending within the propulsion system structure to an exhaust nozzle, and the thrust reverser system comprising a thrust reverser cascade and a thrust reverser door, the thrust reverser cascade is fixed to the fixed structure;
• the thrust reverser cascade extending longitudinally between a cascade forward end and a cascade aft end, the thrust reverser cascade extending laterally between a cascade first side and a cascade second side, and the thrust reverser cascade extending radially between a cascade inner face and a cascade outer face, the cascade inner face and the cascade outer face radially converging towards one another as the cascade inner face and the cascade outer face extend longitudinally from cascade forward end to cascade aft end, and the thrust reverser cascade including a first rail, a second rail and a plurality of vanes laterally between and connected to the first rail and the second rail;
• the first rail extending radially to a rail leading edge;
• the plurality of vanes including a first vane and a second vane, the first vane extending radially to a first vane leading edge that is radially aligned with the rail leading edge, and the second vane extending radially to a second vane leading edge that is recessed into the thrust reverser cascade and radially spaced from the rail leading edge;
• and
• the thrust reverser door configured to pivot between a stowed position and a deployed position, a first portion of the thrust reverser door radially outboard of and axially covering the thrust reverser cascade when the thrust reverser door is in the stowed position, and a second portion of the thrust reverser door forming a radial outer peripheral boundary of the flowpath between the thrust reverser cascade and the exhaust nozzle when the thrust reverser door is in the stowed position.