Nacelle for a high bypass ratio engine with multiple flow paths

Patent metadata

Field	Value
Publication number	US-9623976-B2
Application number	US-201313951229-A
Country	US
Kind code	B2
Filing date	Jul 25, 2013
Priority date	Jul 25, 2012
Publication date	Apr 18, 2017
Grant date	Apr 18, 2017

Abstract

Nacelle air management systems for a high bypass ratio engine are provided. The nacelles air management systems may include an outer cowl and an inner cowl that are configured to provide dual bypass flow channels around an engine core. These systems may be employed to accommodate larger engine fans. The nacelle air management system may also include one or more blocker doors are configured to at least partial obstruct and/or direct air from the dual bypass flow channels to create reverse thrust.

First claim

What is claimed is:

1. A nacelle comprising:
a first cowl configured to at least partially enclose an engine core to define a bypass flow path for receiving a flow of bypass air;
a fan configured to rotate within the first cowl; and
a second cowl radially offset from the first cowl, the second cowl being configured to separate the bypass flow path into at least a first flow path and a second flow path, the first flow path being disposed radially outward of the second cowl and the second flow path being disposed between the first flow path and a volume configured to receive the engine core,
wherein the second cowl comprises a blocker door configured to move between at least a first configuration and a second configuration, and
the blocker door is configured to divert exhaust air from an engine core.

2. The nacelle of claim 1 , wherein the fan comprises a pre-splitter feature configured to at least partially divide the flow of bypass air into the first flow path and the second flow path forward of the second cowl.

3. The nacelle of claim 1 , wherein the second cowl is disposed at least partially within the first cowl.

4. The nacelle of claim 1 , wherein the blocker door is configured to at least partially obstruct the flow of bypass air through the first cowl and the second cowl.

5. The nacelle of claim 1 , wherein the blocker door is configured to divert the flow of bypass air through the second cowl to create reverse thrust.

6. The nacelle of claim 1 , wherein the blocker door is rotatably coupled to the second cowl.

7. The nacelle of claim 1 , wherein a diameter of the second cowl is at least 30 percent smaller than the diameter of the first cowl.

8. A flow splitter system, comprising:
an outer cowl configured to at least partially enclose an aircraft engine core to define a bypass flow path;
a splitter cowl at least partially enclosed by the outer cowl, the splitter cowl annularly spaced within the bypass flow path; and
a fan disposed within the outer cowl and configured to conduct an airflow through a portion of the outer cowl and the splitter cowl, wherein the fan is driven by the aircraft engine core,
wherein the splitter cowl is configured to split the bypass flow path into a first flow path disposed radially outward from the splitter cowl and a second flow path disposed radially inward from the splitter cowl,
the splitter cowl comprises a blocker door,
a fore-most portion of the blocker door is configured to obstruct the first flow path, and
an aft-most portion of the blocker door is configured to obstruct the second flow path.

9. The flow splitter system of claim 8 , wherein the aircraft engine core is enclosed by an inner fixed surface.

10. The flow splitter system of claim 9 , wherein the inner fixed surface is at least partially enclosed by the splitter cowl to define a flow passage.

11. The flow splitter system of claim 10 , wherein the inner fixed surface comprises a blocker door that is configured to divert an airflow through the flow passage to create a reverse thrust.

12. A thrust reverser system, comprising:
a first cowl configured to define a first bypass flow passage;
a second cowl disposed within the first cowl and configured to define a second bypass flow passage, the second cowl comprising a plurality of blocker doors, wherein a fan of an aircraft engine is configured to conduct air through the first bypass flow passage and the second bypass flow passage in response to the aircraft engine operating,
wherein the first bypass flow passage is located radially outward from the second cowl,
the second bypass flow passage is located radially inward from the second cowl,
the plurality of blocker doors are deployable from the second cowl to divert air from the second bypass flow passage to create a reverse thrust, and
a fore-most portion of each of the plurality of blocker doors extends at least partially into the first bypass flow passage in response to the plurality of blocker doors being deployed.

13. The thrust reverser system of claim 12 , wherein the plurality of blocker doors are configured to obstruct at least a portion of the first bypass flow passage.

14. The thrust reverser system of claim 12 , wherein the fan comprises a pre-splitter feature configured to at least partially divide the air between the first bypass flow passage and the second bypass flow passage.

15. The thrust reverser system of claim 12 , wherein the plurality of blocker doors are disposed on an aft end of the second cowl.

Assignees

• Rohr Inc

Inventors

• James Norman J
• Ritchie Keith
• Scott Thomas W

Classifications

• B64D29/00 Primary

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title