Gas turbine engine with noise attenuating variable area fan nozzle
A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.
1. A nacelle assembly for a 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 a fan bypass flow path; and
a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan 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 at a non-closed position, wherein said acoustic system comprises an outer face sheet; to vary a fan nozzle exit area and adjust fan bypass airflow, said second fan nacelle section having a leading edge region with an acoustic system which provides an acoustic impedance when said second fan nacelle section is positioned at said non-closed position.
2. The assembly as recited in claim 1 , wherein said acoustic system further comprises a forward acoustic system and an aft acoustic system, said forward acoustic system different than said aft acoustic system.
3. The assembly as recited in claim 1 , wherein said acoustic system comprises a perforated inner face sheet.
4. A nacelle assembly for a 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 a fan bypass flow path; and a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan 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 at a non-closed position to vary a fan nozzle exit area and adjust fan bypass airflow, said second fan nacelle section having a leading edge region with an acoustic system which provides an acoustic impedance when said second fan nacelle section is positioned at said non-closed position, wherein said acoustic system further comprises a forward acoustic system and an aft acoustic system, said forward acoustic system comprises said leading edge of said second fan nacelle section and said aft acoustic system comprises at least a portion of an upper surface of said second fan nacelle section.
5. A nacelle assembly for a 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 a fan bypass flow path; and a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan 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 at a non-closed position to vary a fan nozzle exit area and adjust fan bypass airflow, said second fan nacelle section having a leading edge region with an acoustic system which provides an acoustic impedance when said second fan nacelle section is positioned at said non-closed position, wherein said acoustic system comprises a perforated inner face sheet and a perforated outer face sheet supported by a structure.
6. A nacelle assembly for a 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 a fan bypass flow path; and
a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan 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 second fan nacelle section comprises an acoustic system having an acoustic impedance, said acoustic system comprises a forward acoustic system in fluid communication with an aft acoustic system, said forward acoustic system comprises a bulk absorbing material and said aft acoustic system comprises a perforated outer face sheet along at least a portion of an upper surface of said second fan nacelle section.
7. The assembly as recited in claim 6 , wherein said second fan nacelle section defines a trailing edge of said variable area fan nozzle.
8. The assembly as recited in claim 6 , 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.
9. 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 variable area fan nozzle in communication with said fan bypass flow path, said variable area fan 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 at a non-closed position, wherein said acoustic system comprises a perforated inner face sheet and a perforated outer face sheet supported by a structure to vary a fan nozzle exit area and adjust fan bypass airflow, said second fan nacelle section having a leading edge region with an acoustic system which provides an acoustic impedance when said second fan nacelle section is positioned at said non-closed position.
10. The engine as recited in claim 9 , wherein said acoustic system comprises a bulk absorbing material.
11. The engine as recited in claim 9 , wherein said second fan nacelle section defines a trailing edge of said variable area fan nozzle.
12. A method of reducing a total effective perceived noise level of a gas turbine engine with a variable area fan nozzle comprising:
axially moving a second fan nacelle section between a closed position in which the second fan nacelle section is in sequential alignment with a first fan nacelle section in response to a cruise flight condition and an open positioning in which the second fan nacelle section is aftward of the first fan nacelle section to define a auxiliary port in response to a non-cruise flight condition, the second fan nacelle section having a leading edge region with an acoustic system which provides an acoustic impedance when the second fan nacelle section is positioned at a non-closed position.
13. A method as recited in claim 12 , further comprising:
generating the acoustic impedance with at least a portion of an upper surface of the second fan nacelle section.