Dual function cascade integrated variable area fan nozzle and thrust reverser

Patent metadata

Field	Value
Publication number	US-9759158-B2
Application number	US-201113332529-A
Country	US
Kind code	B2
Filing date	Dec 21, 2011
Priority date	Oct 12, 2006
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

A gas turbine engine system according to an exemplary aspect of the present disclosure may include a core engine defined about an axis, a fan driven by the core engine about the axis to generate bypass flow, and at least one integrated mechanism in communication with the bypass flow. The bypass flow defines a bypass ratio greater than about six (6). The at least one integrated mechanism includes a variable area fan nozzle (VAFN) and thrust reverser, and a plurality of positions to control bypass flow.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a core engine defined about an axis;
a fan driven by said core engine about said axis to generate bypass flow;
at least one integrated mechanism in communication with the bypass flow, the integrated mechanism configured such that axial movement of the integrated mechanism exposes a cascade section, the cascade section including a first set of apertures angled in an aft direction and a second set of apertures angled in a forward direction, the at least one integrated mechanism including a variable area fan nozzle (VAFN) and a thrust reverser, the integrated mechanism movable between a plurality of axial positions to selectively expose the first and second sets of apertures, wherein the thrust reverser includes a blocker door moveable between a stowed position and a deployed position, and wherein the thrust reverser includes a link slidably connected to the blocker door; and
wherein the blocker door includes a slot having a T-shaped cross section, the slot slidably receiving the link.

2. The gas turbine engine of claim 1 , wherein the bypass flow is arranged to communicate with an exterior environment when the integrated mechanism is in a deployed position.

3. The gas turbine engine of claim 2 , wherein the integrated mechanism includes a plurality of apertures to enable the communication of the bypass flow with the exterior environment when the integrated mechanism is in the deployed position.

4. The gas turbine engine of claim 3 , wherein the integrated mechanism includes a single actuator set to move between the plurality of positions.

5. The gas turbine engine of claim 4 , wherein, when in the deployed position, the thrust reverser diverts the bypass flow in a thrust reversing direction.

6. The gas turbine engine of claim 5 , wherein the at least one integrated mechanism is arranged to change a pressure ratio across the fan.

7. The gas turbine engine system as recited in claim 5 , wherein the first set of apertures are angled in the aft direction by a first set of airfoil shaped vanes, and wherein the second set of apertures are angled in the forward direction by a second set of airfoil shaped vanes.

8. The gas turbine engine as recited in claim 7 , wherein there are a greater number of circumferential rows of the second set of apertures than a number of circumferential rows of the first set of apertures.

9. The gas turbine engine as recited in claim 8 , wherein there are two circumferential rows of the first set of apertures and at least three circumferential rows of the second set of apertures.

10. The gas turbine engine system as recited in claim 1 , wherein:
when the integrated mechanism is in a first axial position, the integrated mechanism completely covers the cascade section and the thrust reverser is in a stowed position;
when the integrated mechanism is in a second axial position, the integrated mechanism exposes the first set of apertures of the cascade section and covers the second set of apertures; and
when the integrated mechanism is in a third axial position, the integrated mechanism exposes both the first set of apertures and the second set of apertures, and the thrust reverser is in the deployed position.

11. The gas turbine engine as recited in claim 1 , wherein the integrated mechanism includes a hollow sleeve-like structure extending about the cascade section, the hollow sleeve-like structure moveable between a plurality of positions to selectively expose the first and second sets of apertures.

12. The gas turbine engine as recited in claim 11 , further comprising:
a nacelle extending circumferentially around the fan;
at least one actuator mounted within one of the nacelle and the cascade section; and
a controller, the at least one actuator configured to selectively move the hollow sleeve-like structure in response to instructions from the controller.

13. The gas turbine engine as recited in claim 12 , wherein the link is pivotally connected to an inner cowl of the gas turbine engine.

14. The gas turbine engine as recited in claim 13 , wherein the blocker door is pivotally connected to the hollow sleeve-like structure.

15. The gas turbine engine as recited in claim 14 , wherein the connection between the link and blocker door provides a range of lost motion such that, within the range of lost motion, movement of the hollow sleeve-like structure does not cause the blocker door to move into the deployed position.

16. A gas turbine engine comprising:
a core engine defined about an axis, said core engine including at least a low pressure turbine;
a fan couple to be driven by said core engine about said axis to generate a bypass flow;
at least one integrated mechanism in communication with the bypass flow, the at least one integrated mechanism including a variable area fan nozzle (VAFN) and a thrust reverser, the at least one integrated mechanism configured such that axial movement of the at least one integrated mechanism exposes a cascade section, the cascade section including a first set of apertures angled in an aft direction and a second set of apertures angled in a forward direction, the integrated mechanism movable between a plurality of axial positions to selectively expose the first and second sets of apertures, wherein the integrated mechanism includes a section common to the thrust reverser and VAFN, wherein the thrust reverser includes a blocker door moveable between a stowed position and a deployed position, and wherein the thrust reverser includes a link slidably connected to the blocker door; and
wherein the blocker door includes a slot having a T-shaped cross section, the slot slidably receiving the link.

17. The gas turbine engine of claim 16 , wherein the integrated mechanism includes at least one actuator set to move between the plurality of positions.

18. The gas turbine engine of claim 17 , wherein, when in the deployed position, the thrust reverser diverts the bypass flow in a thrust reversing direction.

19. The gas turbine engine of claim 16 , wherein the common section is moveable between a plurality of axial positions and has a plurality of apertures providing a flow path for the bypass flow to reach an exterior environment of the gas turbine engine.

20. The gas turbine engine as recited in claim 19 , wherein the common section is a hollow sleeve-like structure, and wherein the connection between the link and blocker door provides a range of lost motion such that, within the range of lost motion, movement of the hollow sleeve-like structure does not cause the blocker door to move into the deployed position.

21. The gas turbine engine of claim 16 , wherein the link has one end slidably connected to the blocker door and an opposite end connected to a support.

22. A gas turbine engine comprising:
a core engine defined about an axis, said core engine including at least a low pressure turbine;
a fan couple to be driven by said core engine about said axis to generate a bypass flow;
at least one integrated mechanism in communication with the bypass flow, the at least one integrated mechanism including a variable area fan nozzle (VAFN) and a thrust reverser, the integrated mechanism including a plurality of positions to control bypass flow, wherein the integrated mechanism includes a section common to the thrust reverser and VAFN;
wherein the thrust reverser includes a blocker door moveable between a stowed position and a deployed position and a link having one end connected to

Assignees

• Marshall Richard M
• United Technologies Corp

Inventors

• Marshall Richard M

Classifications

• F02K1/42

  the means being movable into an inoperative position · CPC title

• F02K1/09 Primary

  by axially moving an external member, e.g. a shroud (F02K1/12 takes precedence) · CPC title

• F02K1/72

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title