Thrust reverser cascade with offset vane leading edges
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.
1. 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 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 thrust reverser cascade is fixed to the fixed structure;
the thrust reverser cascade including a plurality of vanes and a plurality of rails;
the plurality of vanes arranged in a plurality of longitudinally extending arrays, the plurality of vanes comprising a first vane and a second vane, a leading edge of the first vane disposed on the cascade inner face, and a leading edge of the second vane recessed radially into the thrust reverser cascade from the cascade inner face;
the plurality of rails extending longitudinally along and connected to the plurality of vanes, the plurality of rails comprising a first rail with a first radial height, and the first radial height of the first rail decreasing as the first rail extends longitudinally from the cascade forward end to the cascade aft end, wherein each of the plurality of arrays is arranged between a respective laterally neighboring or adjacent pair of rails; 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,
wherein:
a trailing edge of the first vane is disposed on the cascade outer face; and
a trailing edge of the second vane is spaced radially from the cascade outer face.
2. The apparatus of claim 1 , wherein a plane of the cascade inner face has a straight sectional geometry as the thrust reverser cascade extends longitudinally from the cascade forward end to the cascade aft end.
3. The apparatus of claim 1 , wherein a leading edge of each of the plurality of rails is disposed on the cascade inner face.
4. The apparatus of claim 1 , wherein
the first rail extends radially to a rail leading edge;
the leading edge of the first vane is radially aligned with the rail leading edge; and
the leading edge of the second vane is spaced radially from the rail leading edge.
5. The apparatus of claim 1 , wherein the first vane is longitudinally forward of the second vane.
6. The apparatus of claim 1 , wherein the first vane is longitudinally aft of the second vane.
7. The apparatus of claim 1 , wherein a radial height of the first vane is different than a radial height of the second vane.
8. The apparatus of claim 1 , wherein
the plurality of vanes further comprise a third vane; and
a leading edge of the third vane is disposed on the cascade inner face.
9. The apparatus of claim 8 , wherein the second vane is longitudinally between the first vane and the third vane.
10. The apparatus of claim 1 , wherein
the plurality of vanes further comprise a third vane; and
a leading edge of the third vane is recessed radially into the thrust reverser cascade from the cascade inner face.
11. The apparatus of claim 10 , wherein
the leading edge of the second vane is disposed a second vane distance from the cascade inner face; and
the leading edge of the third vane is disposed a third vane distance from the cascade inner face that is equal to the second vane distance.
12. The apparatus of claim 10 , wherein
the leading edge of the second vane is disposed a second vane distance from the cascade inner face; and
the leading edge of the third vane is disposed a third vane distance from the cascade inner face that is different than the second vane distance.
13. The apparatus of claim 10 , wherein the second vane is longitudinally between the first vane and the third vane.
14. The apparatus of claim 10 , wherein the first vane is longitudinally between the second vane and the third vane.
15. The apparatus of claim 1 , wherein the thrust reverser cascade is exposed to the flowpath when the thrust reverser door is in the stowed position.
16. The apparatus of claim 1 , wherein the second portion of the thrust reverser door is configured to move radially into the flowpath when the thrust reverser door pivots from the stowed position into the deployed position.
17. The apparatus of claim 1 , wherein
the leading edge of the first vane is upstream of the trailing edge of the first vane along the axial centerline; and
the first vane includes a non-linear cross-sectional geometry along the axial centerline such that a portion between the leading edge of the first vane and the trailing edge of the first vane is aft of the leading edge of the first vane and aft of the trailing edge of the first vane.
18. The apparatus of claim 17 , wherein
the leading edge of the second vane is upstream of the trailing edge of the second vane along the axial centerline; and
the second vane includes a non-linear cross-sectional geometry along the axial centerline such that a portion between the leading edge of the second vane and the trailing edge of the second vane is aft of the leading edge of the second vane and aft of the trailing edge of the second vane.
19. 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.
20. 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.