초록 ▼

Aircraft systems including cascade thrust reversers are disclosed herein. An aircraft system in accordance with one embodiment includes a cascade thrust reverser having a fixed reverser ramp and a nozzle outer wall section at least partially aft of the fixed reverser ramp. The nozzle outer wall sect

Aircraft systems including cascade thrust reversers are disclosed herein. An aircraft system in accordance with one embodiment includes a cascade thrust reverser having a fixed reverser ramp and a nozzle outer wall section at least partially aft of the fixed reverser ramp. The nozzle outer wall section is movable between a deployed position and a stowed position. The nozzle outer wall section includes a forward portion with a leading edge section. The fixed reverser ramp has a portion forward of and adjacent to the nozzle outer wall section when the nozzle outer wall section is in the stowed position. The portion of the fixed reverser ramp has a first slope. The forward portion of the nozzle outer wall section that is aft of the leading edge section has a second slope different than the first slope.

대표청구항 ▼

We claim: 1. An aircraft system, comprising a cascade thrust reverser including: a fixed reverser ramp; a nozzle outer wall section at least partially aft of the fixed reverser ramp, the nozzle outer wall section being movable between a deployed position and a stowed position, the nozzle outer wall

We claim: 1. An aircraft system, comprising a cascade thrust reverser including: a fixed reverser ramp; a nozzle outer wall section at least partially aft of the fixed reverser ramp, the nozzle outer wall section being movable between a deployed position and a stowed position, the nozzle outer wall section including a forward portion with a radially inwardly facing inner surface having a leading edge section, wherein at least a segment of the inner surface of the forward portion is at least generally planar; and a blocker door coupled to the nozzle outer wall section, wherein in the stowed position of the nozzle outer wall section the blocker door is at least generally parallel to the inner surface, and in the deployed position of the nozzle outer wall section the blocker door is at least generally perpendicular to the inner surface; wherein in the stowed position of the nozzle outer wall section the fixed reverser ramp has a portion forward of and adjacent to the nozzle outer wall section, the portion of the fixed reverser ramp having a first slope; and wherein the forward portion of the nozzle outer wall section has a second slope aft of the leading edge section, the second slope being different than the first slope, and wherein the at least generally planar segment of the inner surface lies in a plane that intersects the reverser ramp. 2. The aircraft system of claim 1, further comprising a fan casing including a nozzle outer wall section having an aft portion with a third slope different than the first slope. 3. The aircraft system of claim 1, further comprising a fan casing including a nozzle outer wall section, wherein the forward portion of the nozzle outer wall section of the thrust reverser and the fixed reverser ramp define a pit that is recessed radially outward from the nozzle outer wall section of the fan casing. 4. The aircraft system of claim 1, further comprising a fan casing including a nozzle outer wall section having an aft portion with a third slope at least generally similar to the first slope. 5. The aircraft system of claim 1 wherein the leading edge section has a third slope different than the first slope. 6. The aircraft system of claim 1 wherein the leading edge section has a third slope at least generally the same as the first slope. 7. The aircraft system of claim 1, further comprising: a wing coupled to the thrust reverser; a fuselage attached to the wing; and a tail coupled to the fuselage. 8. An aircraft system, comprising: a thrust reverser including a nozzle outer wall section configured to move between a first position and a second position aft of the first position, the nozzle outer wall section including a radially inwardly facing inner surface having a forward portion with a first slope along an axis, wherein at least a segment of the forward portion is at least generally planar, and a blocker door, wherein in the first position of the nozzle outer wall section the blocker door is positioned at least generally parallel to the inner surface and in the second position of the nozzle outer wall section the blocker door is at least generally transverse to the inner surface; and a fan casing coupled to the thrust reverser, the fan easing including a nozzle outer wall section having an aft portion with a second slope along the axis, wherein the first slope is different than the second slope, and wherein the at least generally planar segment of the inner surface of the forward portion lies in a plane that intersects the aft portion of the nozzle outer wall section of the fan casing. 9. The aircraft system of claim 8 wherein: the forward portion of the nozzle outer wall section in the thrust reverser includes a leading edge; the thrust reverser further includes a fixed reverser ramp having a portion forward of and adjacent to the leading edge; and in the first position of the nozzle outer wall section the portion of the fixed reverser ramp has a third slope different than the first slope. 10. The aircraft system of claim 8 wherein: the thrust reverser further includes a fixed reverser ramp having a portion radially inward of the forward portion of the nozzle outer wall section; and the portion of the fixed reverser ramp and the forward portion of the nozzle outer wall section define a pit. 11. The aircraft system of claim 8, further comprising a fixed reverser ramp in the thrust reverser and aft of the fan casing. 12. The aircraft system of claim 8, further comprising a fixed reverser ramp having a forward section in the fan casing and an aft section in the thrust reverser. 13. The aircraft system of claim 8 wherein the forward portion of the nozzle outer wall section of the thrust reverser includes a leading edge section having a third slope different than the first slope, and wherein the first slope is the slope of a section of the forward portion aft of the leading edge section. 14. An aircraft system, comprising a cascade thrust reverser including: a fixed reverser ramp; and a nozzle outer wall section at least partially aft of the fixed reverser ramp, the nozzle outer wall section being movable between a deployed position and a stowed position, the nozzle outer wall section including a forward portion with a radially inwardly facing inner surface having a leading edge section, and a blocker door, wherein in the stowed position of the nozzle outer wall section the blocker door is positioned at least generally parallel to the inner surface and in the deployed position of the nozzle outer wall section the blocker door is at least generally perpendicular to the inner surface, wherein at least a segment of the inner surface of the forward portion is at least generally planar; wherein in the stowed position of the nozzle outer wall section, the forward portion of the nozzle outer wall section is positioned such that the at least generally planar segment of the inner surface of the forward portion lies in a plane that intersects the reverser ramp. 15. The aircraft system of claim 14 wherein the forward portion of the nozzle outer wall section has a first slope aft of the leading edge section, and wherein the system further comprises a fan casing including a nozzle outer wall section having an aft portion with a second slope at least generally similar to the first slope. 16. The aircraft system of claim 14 wherein the forward portion of the nozzle outer wall section has a first slope aft of the leading edge section, and wherein the system further comprises a fan casing including a nozzle outer wall section having an aft portion with a second slope different than the first slope. 17. The aircraft system of claim 14 wherein the forward portion of the nozzle outer wall section has a first slope aft of the leading edge section, and wherein the leading edge section has a second slope different than the first slope. 18. The aircraft system of claim 14 wherein the forward portion of the nozzle outer wall section has a first slope aft of the leading edge section, and wherein the leading edge section has an arcuate configuration and projects forwardly and outwardly.