초록 ▼

An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween. The inner nacelle includes a nacelle wall and at least one access panel, which is adapted to at least parti

An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween. The inner nacelle includes a nacelle wall and at least one access panel, which is adapted to at least partially cover an aperture in the nacelle wall. The outer nacelle axially overlaps the access panel.

대표청구항 ▼

1. An assembly for a turbine engine with an axial centerline, the assembly comprising: an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween;the inner nacelle including a nacelle wall, at least one first access panel adapted to at least partially cover a first aperture i

1. An assembly for a turbine engine with an axial centerline, the assembly comprising: an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween;the inner nacelle including a nacelle wall, at least one first access panel adapted to at least partially cover a first aperture in the nacelle wall, and at least one second access panel adapted to at least partially cover a second aperture in the nacelle wall;wherein the outer nacelle axially overlaps the access panel;wherein the first access panel extends circumferentially to a top panel side, and the first access panel is hinged to the nacelle wall at the top panel side; andwherein the second access panel extends circumferentially to a bottom panel side, and the second access panel is hinged to the nacelle wall at the bottom panel side. 2. The assembly of claim 1, further comprising: a bifurcation extending radially between the outer nacelle and the inner nacelle;wherein the outer nacelle, the inner nacelle and the bifurcation form an O-duct through which the bypass flowpath axially extends. 3. The assembly of claim 1, wherein the nacelle wall has an outer surface that extends axially along and at least three hundred and twenty degrees around the centerline. 4. The assembly of claim 1, wherein the nacelle wall extends axially along the centerline; andthe first aperture extends axially within and radially through the nacelle wall. 5. The assembly of claim 1, wherein the nacelle wall extends axially along the centerline; andthe first aperture extends circumferentially within and radially through the nacelle wall. 6. An assembly for a turbine engine with an axial centerline, the assembly comprising: an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween;the inner nacelle including a nacelle wall and an access panel adapted to at least partially cover an aperture in the nacelle wall;wherein the outer nacelle includes a thrust reverser cascade that axially overlaps the access panel;wherein the outer nacelle axially overlaps the access panel; andwherein the access panel is removably fastened to the nacelle wall. 7. The assembly of claim 1, further comprising a third access panel attached to the nacelle wall, the third access panel adapted to at least partially cover a third aperture in the nacelle wall, wherein the third access panel extends circumferentially to a panel side, and the third access panel is hinged to the nacelle wall at the panel side. 8. The assembly of claim 1, wherein the outer nacelle includes a sleeve adapted to move axially between a forward position and an aft position; andthe sleeve axially overlaps the access panel in the forward position. 9. The assembly of claim 8, wherein the first aperture in the inner nacelle is substantially axially aligned with an aperture in the outer nacelle that extends axially between a fixed portion of the outer nacelle and the sleeve in the aft position. 10. The assembly of claim 1, wherein the outer nacelle includes a thrust reverser cascade that axially overlaps the access panel. 11. An assembly for a turbine engine with an axial centerline, the assembly comprising: an outer nacelle and an inner nacelle with a bypass flowpath radially therebetween;the inner nacelle including a nacelle wall, a first access panel adapted to at least partially cover a first aperture in the nacelle wall, and a second access panel adapted to at least partially cover a second aperture in the nacelle wall;wherein the first access panel is on a first side of the nacelle and is configured to slide to at least partially expose the first aperture;wherein the second access panel is on a second side of the nacelle, which is opposite the first side of the nacelle, and is configured to slide to at least partially expose the second aperture; andwherein the outer nacelle axially overlaps the first aperture and the second aperture.