Gas turbine engine with axial movable fan variable area nozzle

1. A nacelle assembly for a high-bypass gas turbine engine comprising:

a core nacelle defined about an engine centerline axis;

a fan nacelle mounted at least partially around said core nacelle to define an annular fan bypass flow path; and

a fan variable area nozzle in communication with said fan bypass flow path, said fan variable area nozzle having a first fan nacelle section and a second fan nacelle section, said second fan nacelle section axially movable relative said first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, said auxiliary port no more forward than 0.1 DEL_X/L_DUCT from a maximum radius of said annular fan bypass flow path, wherein DEL_X is the axial distance from said maximum radius to a forward most point of said auxiliary port and L DUCT is the axial length of said annular fan bypass flow path.

2. The assembly as recited in claim 1 , wherein said second fan nacelle section defines an auxiliary port entrance angle, said auxiliary port entrance angle relative to said first fan nacelle section less than 20 degrees.

3. The assembly as recited in claim 1 , wherein an outer surface of said second fan nacelle section defines an R_ARC/CHORD greater than 0.7 where R_ARC is a radial distance from said engine axis to a radial outer wall surface of said second fan nacelle section and CHORD is the chord length of said second fan nacelle section.

4. The assembly as recited in claim 1 , wherein said second fan nacelle section defines an auxiliary port entrance angle, said auxiliary port entrance angle relative to said first fan nacelle section less than 20 degrees, and an outer surface of said second fan nacelle section defines an R_ARC/CHORD greater than 0.7 where R_ARC is a radial distance from said engine axis to a radial outer wall surface of said second fan nacelle section and CHORD is the chord length of said second fan nacelle section.

5. The assembly as recited in claim 1 , wherein said second fan nacelle section includes a first segment defined between a pylon and a lower bifi and a second segment defined between said pylon and said lower bifi.

6. The assembly as recited in claim 1 , wherein said second fan nacelle section defines a trailing edge of said fan variable area nozzle.

7. The assembly as recited in claim 1 , wherein said second fan nacelle section is subdivided into a multiple of independently operable sectors, each of said multiple of independently operable sectors axially movable relative said the first fan nacelle section to define an asymmetric fan nozzle exit area.

8. A nacelle system for a high-bypass gas turbine engine comprising:

a core engine defined about an axis;

a gear system driven by said core engine;

a turbofan driven by said gear system about said axis;

a core nacelle defined at least partially about said core engine;

a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path; and

a fan variable area nozzle in communication with said fan bypass flow path, said fan variable area nozzle having a first fan nacelle section and a second fan nacelle section, said second fan nacelle section axially movable relative said first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, said auxiliary port no more forward than 0.1 DEL_X/L_DUCT from a maximum radius of said annular fan bypass flow path, wherein DEL_X is the axial distance from said maximum radius to a forward most point of said auxiliary port and L_DUCT is the axial length of said annular fan bypass flow path.

9. The system as recited in claim 8 , wherein said second fan nacelle section defines an auxiliary port entrance angle, said auxiliary port entrance angle relative to said first fan nacelle section less than 20 degrees.

10. The system as recited in claim 8 , wherein an outer surface of said second fan nacelle section defines an R_ARC/CHORD greater than 0.7 where R_ARC is a radial distance from said engine axis to a radial outer wall surface of said second fan nacelle section and CHORD is the chord length of said second fan nacelle section.

11. The system as recited in claim 8 , wherein said second fan nacelle section defines an auxiliary port entrance angle, said auxiliary port entrance angle relative to said first fan nacelle section less than 20 degrees, and an outer surface of said second fan nacelle section defines an R_ARC/CHORD greater than 0.7 where R_ARC is a radial distance from said engine axis to a radial outer wall surface of said second fan nacelle section and CHORD is the chord length of said second fan nacelle section.

12. The system as recited in claim 8 , further comprising a controller in communication with an actuator system to axially move said second fan nacelle section relative to said first fan nacelle section to vary said fan nozzle exit area in response to a flight condition.

13. The system as recited in claim 12 , wherein said second fan nacelle section is aligned with said first fan nacelle section about said axis to define a closed position of said fan nozzle exit area.

14. The system as recited in claim 13 , wherein said second fan nacelle section is axially offset relative said first fan nacelle section along said track to define an open position of said fan nozzle exit area.

15. The system as recited in claim 8 , wherein said second fan nacelle section axially movable generally along said track to vary a fan nozzle exit area to adjust fan bypass airflow such that an angle of attack of turbofan fan blades are maintained close to design incidence.