초록

A variable area fan nozzle for a gas turbine engine includes a radially outer wall and a radially inner wall. At least one of the radially outer wall and the radially inner wall includes a wall thickness distribution that has local thick portions and local thin portions.

대표청구항 ▼

1. A gas turbine engine, comprising: a core engine including at least a compressor section, a combustor section and a turbine section disposed along a central axis;a fan coupled to be driven by the turbine section; a core nacelle around the core engine;a fan nacelle around the fan, the fan nacelle a

1. A gas turbine engine, comprising: a core engine including at least a compressor section, a combustor section and a turbine section disposed along a central axis;a fan coupled to be driven by the turbine section; a core nacelle around the core engine;a fan nacelle around the fan, the fan nacelle and the core nacelle defining a bypass passage there between; anda variable area fan nozzle (VAFN) extending at least partially around the central axis and defining an exit area of the bypass passage, the VAFN being selectively movable to vary the exit area, the VAFN including a body defining an airfoil cross-sectional shape, the body including a radially outer wall and a radially inner wall, at least one of the radially outer wall and the radially inner wall including a wall thickness distribution having local thick portions and local thin portions, the radially outer wall and the radially inner wall comprising a fiber-reinforced polymer matrix composite material. 2. The gas turbine engine as recited in claim 1, wherein the local thin portions have a minimum thickness and the local thick portions have a maximum thickness, and the minimum thickness is 90% or less of the maximum thickness. 3. The gas turbine engine as recited in claim 2, wherein the minimum thickness is 80% or less of the maximum thickness. 4. The gas turbine engine as recited in claim 2, wherein the minimum thickness is 70% or less of the maximum thickness. 5. The gas turbine engine as recited in claim 2, wherein the minimum thickness is 60% or less of the maximum thickness. 6. The gas turbine engine as recited in claim 1, wherein the radially inner wall has a first wall thickness distribution and the radially outer wall has a second wall thickness distribution that is different than the first wall thickness distribution. 7. The gas turbine engine as recited in claim 1, wherein the fiber-reinforced polymer matrix composite material includes a multi-layer structure of cross-oriented fiber layers. 8. The gas turbine engine as recited in claim 1, wherein the radially inner wall is radially-inwardly spaced apart from the radially outer wall. 9. The gas turbine engine as recited in claim 1, wherein the VAFN is a hollow structure. 10. The gas turbine engine as recited in claim 1, wherein the VAFN includes supports extending between the radially inner wall and the radially outer wall. 11. The gas turbine engine as recited in claim 1, wherein the local thick portions and local thin portions are different in at least one of fiber density, fiber volume percent, area weight of polymer and number of sub-layers of the fiber-reinforced polymer matrix composite material. 12. The gas turbine engine as recited in claim 11, wherein the local thick portions and local thin portions are different in fiber density of the fiber-reinforced polymer matrix composite material. 13. The gas turbine engine as recited in claim 11, wherein the local thick portions and local thin portions are different in fiber volume percent of the fiber-reinforced polymer matrix composite material. 14. The gas turbine engine as recited in claim 11, wherein the local thick portions and local thin portions are different in area weight of polymer of the fiber-reinforced polymer matrix composite material. 15. The gas turbine engine as recited in claim 11, wherein the local thick portions and local thin portions are different in number of sub-layers of the fiber-reinforced polymer matrix composite material. 16. The gas turbine engine as recited in claim 1, wherein the local thick portions and local thin portions are selected according to one or more flutter characteristics of the VAFN. 17. The gas turbine engine as recited in claim 1, wherein the local thin portions have a minimum thickness and the local thick portions have a maximum thickness, the minimum thickness and the maximum thickness being selected to influence one or more flutter characteristics of the VAFN, and the minimum thickness is 90% or less of the maximum thickness. 18. A variable area fan nozzle, comprising: a body defines an airfoil cross-section shape extending at least partially around an axis of the variable area fan nozzle, the body including a radially outer wall and a radially inner wall relative to the axis, at least one of the radially outer wall and the radially inner wall including a wall thickness distribution having local thick portions and local thin portions, the radially outer wall and the radially inner wall comprising a fiber-reinforced polymer matrix composite material. 19. The variable area fan nozzle as recited in claim 18, wherein the local thin portions have a minimum thickness and the local thick portions have a maximum thickness, and the minimum thickness is 90% or less of the maximum thickness. 20. The variable area fan nozzle as recited in claim 19, wherein the minimum thickness is 80% or less of the maximum thickness. 21. The variable area fan nozzle as recited in claim 18, wherein the radially inner wall has a first wall thickness distribution and the radially outer wall has a second wall thickness distribution that is different than the first wall thickness distribution.