Variable area fan nozzle

Patent metadata

Field	Value
Publication number	US-10041442-B2
Application number	US-81364610-A
Country	US
Kind code	B2
Filing date	Jun 11, 2010
Priority date	Jun 11, 2010
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle in communication with a fan bypass flow path. An actuator assembly is operable to move a second fan nacelle section relative to a first fan nacelle section to vary a fan nozzle exit area and adjust fan bypass airflow, the actuator assembly extends at least partially into the fan bypass flow path.

First claim

What is claimed is:

1. A nacelle assembly for a gas turbine engine comprising:
a core nacelle defined about an engine centerline axis;
a fan nacelle mounted at least partially around said core nacelle such that a fan bypass flow path is defined by an inner diameter of the fan nacelle and an outer diameter of the core nacelle, and wherein the fan bypass flow path is radially uninterrupted along at least a majority of the fan bypass flow path;
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; and
an actuator assembly including an actuator operable to move said second fan nacelle section relative to said first fan nacelle section to vary a fan nozzle exit area and adjust fan bypass airflow, and a tear drop shaped actuator fairing enclosing said actuator, and said actuator assembly extends at least partially into said fan bypass flow path from a radially inward surface of said first fan nacelle section and a radially inward surface of said second fan nacelle section.

2. The nacelle assembly as recited in claim 1 , wherein said actuator assembly extends radially inward toward said engine centerline axis.

3. The nacelle assembly as recited in claim 1 , wherein said actuator fairing extends radially inward toward said engine centerline axis.

4. The nacelle assembly as recited in claim 1 , wherein said second fan nacelle section is axially movable relative to said first fan nacelle section.

5. The nacelle assembly as recited in claim 4 , wherein said second fan nacelle section defines a trailing edge of said first fan nacelle section.

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

7. The nacelle assembly as recited in claim 1 , further comprising an actuator fairing which encloses said actuator assembly, said actuator fairing extends radially inward toward said engine centerline axis.

8. The nacelle assembly as recited in claim 1 , further comprising a fan within said fan nacelle, said fan driven by a core engine within said core nacelle.

9. The nacelle assembly as recited in claim 8 , wherein said fan is driven by said core engine through a gear train.

10. The nacelle assembly as recited in claim 1 , wherein said second fan nacelle section is movable relative to said first fan nacelle section between an open position and a closed position, said open position displaces said second fan nacelle section relative to said first fan nacelle section to define an auxiliary port through said fan nacelle between said second fan nacelle section and said first fan nacelle section, said closed position locates said second fan nacelle section adjacent to said first fan nacelle section to close said auxiliary port.

11. A gas turbine engine comprising:
a core engine defined about an axis;
a gear system driven by said core engine;
a fan 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 such that a fan bypass flow path is defined by an inner diameter of the fan nacelle and an outer diameter of the core nacelle;
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; and
a multiple of actuator assemblies, each actuator assembly including an actuator operable to move said second fan nacelle section relative to said first fan nacelle section to vary a fan nozzle exit area and adjust fan bypass airflow and including a teardrop shaped actuator fairing at least partially enclosing the actuator, each of the multiple of actuator assemblies extends at least partially into said fan bypass flow path from a radially inward surface of said first fan nacelle section and a radially inward surface of said second fan nacelle section.

12. The gas turbine engine as recited in claim 11 , wherein said multiple of actuator assemblies are distributed about an inner diameter of said fan nacelle.

13. The gas turbine engine as recited in claim 12 , wherein said second fan nacelle section defines a first sector and a second sector.

14. The gas turbine engine as recited in claim 13 , wherein each of said first sector and said second sector are defined between a pylon and a lower bifurcating splitter.

15. The gas turbine engine as recited in claim 11 , wherein said second fan nacelle section is movable relative to said first fan nacelle section between an open position and a closed position, said open position displaces said second fan nacelle section relative to said first fan nacelle section to defines an auxiliary port through said fan nacelle between said second fan nacelle section and said first fan nacelle section, said closed position locates said second fan nacelle section adjacent to said first fan nacelle section to close said auxiliary port.

16. A nacelle assembly for a gas turbine engine comprising:
a variable area fan nozzle in communication with a fan bypass flow path, said variable area fan nozzle having a first fan nacelle section and a second fan nacelle section to vary a fan nozzle exit area and adjust a fan bypass airflow through said fan bypass flow path, said second fan nacelle section axially movable relative to said first fan nacelle section between an open position and a closed position, said open position displaces said second fan nacelle section relative to said first fan nacelle section to define an auxiliary port through said fan nacelle between said second fan nacelle section and said first fan nacelle section, said closed position locates said second fan nacelle section adjacent to said first fan nacelle section to close said auxiliary port;
an actuator assembly including an actuator operable to move said second fan nacelle section relative to said first fan nacelle section and including a teardrop shaped actuator fairing which encloses said actuator, said actuator fairing extends radially inward at least partially into said fan bypass flow path from a radially inward surface of said first fan nacelle section and a radially inward surface of said second fan nacelle section; and
wherein the fan bypass flow path is defined by an inner diameter of the fan nacelle and an outer diameter of a core nacelle.

17. The nacelle assembly as recited in claim 16 , wherein said second fan nacelle section defines a trailing edge of said first fan nacelle section.

Assignees

• Murphy Michael J
• United Technologies Corp

Inventors

• Murphy Michael J

Classifications

• F02K1/15

  Control or regulation · CPC title

• F02K3/06

  with front fan · CPC title

• F02K1/06 Primary

  Varying effective area of jet pipe or nozzle (by using fluid jets to influence the jet flow F02K1/30) · CPC title

• F02K1/08

  by axially moving or transversely deforming an internal member, e.g. the exhaust cone · CPC title