초록

A gas turbine engine nacelle includes an inner skin surrounded by a radially outer skin. The inner skin terminates at an exhaust outlet. The outer skin terminates at a recess in the inner skin extending into a closed cavity under the outer skin.

대표청구항 ▼

1. A gas turbine engine nacelle comprising:an inner skin terminating at an exhaust outlet; and a radially outer skin surrounding said inner skin, and terminating at a recess in said inner skin extending into a closed cavity under said outer skin. 2. A nacelle according to claim 1 wherein said outer

1. A gas turbine engine nacelle comprising:an inner skin terminating at an exhaust outlet; and a radially outer skin surrounding said inner skin, and terminating at a recess in said inner skin extending into a closed cavity under said outer skin. 2. A nacelle according to claim 1 wherein said outer and inner skins converge aft and are axially interrupted by said recess therebetween.3. A nacelle according to claim 2 wherein said cavity converges aft to said recess.4. A nacelle according to claim 3 wherein said cavity includes a radial frame bridging said inner and outer skins forward of said recess.5. A nacelle according to claim 2 wherein said inner skin is generally cylindrical under said recess.6. A nacelle according to claim 5 wherein said recess blends into said inner skin aft thereof, and said outer and inner skins are axially coextensive across said recess in a common convergence thereacross.7. A nacelle according to claim 2 wherein said recess extends in axial length over a minor portion of the distance to said exhaust outlet.8. A nacelle according to claim 7 wherein said recess axial length is about 12 percent of the distance between the aft ends of said inner and outer skins.9. A nacelle according to claim 2 wherein said cavity has an arcuate inlet at the aft end of said outer skin, with a flow area being a minor portion of the flow area for said exhaust outlet.10. A nacelle according to claim 9 wherein said flow area for said cavity inlet is less than or equal to about 10 percent of the flow area for said exhaust outlet.11. A nacelle according to claim 2 comprising a short nacelle surrounding a forward portion of a core engine to define a fan bypass duct therebetween terminating at said exhaust outlet disposed upstream from a separate outlet of said core engine.12. A nacelle according to claim 2 comprising a long nacelle surrounding a core engine to define a common exhaust outlet at the aft end thereof for both core exhaust and fan bypass exhaust.13. A gas turbine engine nacelle comprising:an inner skin terminating at a converging boattail portion thereof having a nozzle outlet at an aft end thereof; and a radially outer skin surrounding said inner skin forward of said boattail portion, and converging to a recess in said inner skin disposed upstream from said nozzle outlet, with said recess extending forward into a closed cavity under said outer skin. 14. A nacelle according to claim 13 wherein said cavity includes a radial frame bridging said inner and outer skins forward of said recess.15. A nacelle according to claim 14 wherein said inner skin is generally cylindrical under said recess.16. A nacelle according to claim 15 wherein said recess blends into said boattail portion aft thereof, and said outer and inner skins are axially coextensive across said recess in a common convergence thereacross.17. A nacelle according to claim 16 wherein said recess extends in axial length over a minor portion of the distance to said exhaust outlet.18. A nacelle according to claim 17 wherein said cavity has an arcuate inlet at the aft end of said outer skin, with a flow area being a minor portion of the flow area for said exhaust outlet.19. A nacelle according to claim 18 wherein said recess axial length is about 12 percent of the distance between the aft ends of said inner and outer skins.20. A nacelle according to claim 19 wherein said flow area for said cavity inlet is less than or equal to about 10 percent of the flow area for said exhaust outlet.