Aircraft nacelle including a rear frame inclined to the rear

Patent metadata

Field	Value
Publication number	US-9284060-B2
Application number	US-201113270536-A
Country	US
Kind code	B2
Filing date	Oct 11, 2011
Priority date	Oct 15, 2010
Publication date	Mar 15, 2016
Grant date	Mar 15, 2016

Abstract

An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery.

First claim

The invention claimed is:

1. An aircraft nacelle that comprises:
a lip;
an inside wall that delimits an inside pipe;
a surface of the lip that is in contact with aerodynamic streams extends inside the nacelle by the inside wall that delimits the inside pipe;
a junction zone that connects the inside pipe to a pipe of a power plant outside of the nacelle by an outside wall;
a front frame that connects the inside wall and the outside wall, delimiting an annular pipe with the lip;
a rear frame that connects the outside wall and the inside wall at the junction zone between the inside pipe and the pipe of the power plant, the rear frame comprising at least one opening to link zones that are located on either side of the rear frame, each opening comprising at least one door that is articulated relative to an edge of the opening, whereby said door is able to occupy a first state in which the door blocks the opening and another state in which the door clears the opening;
a point A corresponding to an intersection between the rear frame and the inside wall; and
a point B corresponding to an intersection between the rear frame and the outside wall, wherein point A and point B lie in a plane that contains a longitudinal axis of the nacelle, wherein the point B is offset toward the rear of the nacelle relative to the point A over more than 50% of a periphery of the rear frame.

2. The aircraft nacelle according to claim 1 , wherein the point B is offset toward the rear over the entire periphery of the rear frame.

3. The aircraft nacelle according to claim 1 , wherein the straight line AB defined between point A and point B forms an angle of between 20 and 45° relative to a straight line that passes through A perpendicular to the longitudinal axis.

4. The aircraft nacelle according to claim 2 , wherein a straight line AB defined between point A and point B forms an angle of between 20 and 45° relative to a straight line that passes through A perpendicular to the longitudinal axis.

5. The aircraft nacelle according to claim 1 , wherein the point B is offset toward the rear relative to the point A at an angular sector of the rear frame.

6. The aircraft nacelle according to claim 1 , wherein the rear frame has a wavy profile with the longitudinal axis being inserted between the point A and the point B.

7. The aircraft nacelle according to claim 1 , wherein the at least one opening comprises a plurality of openings that are distributed over a circumference of the rear frame.

8. The aircraft nacelle according to claim 1 , wherein the zones are isolated by the rear frame except during maintenance.

9. An aircraft nacelle that comprises:
a lip;
an inside wall that delimits an inside pipe;
a surface of the lip that is in contact with aerodynamic streams extends inside the nacelle by the inside wall that delimits the inside pipe;
a junction zone that connects the inside pipe to a pipe of a power plant outside of the nacelle by an outside wall;
a front frame that connects the inside wall and the outside wall, delimiting an annular pipe with the lip;
a rear frame that connects the outside wall and the inside wall at the junction zone between the inside pipe and the pipe of the power plant;
at least one opening to link zones that are located on either side of the rear frame, each opening comprising at least one door that is articulated relative to an edge of the opening, whereby said door is able to occupy a first state in which the door blocks the opening and another state in which the door clears the opening, and the zones are isolated by the rear frame except during maintenance;
a point A corresponding to an intersection between the rear frame and the inside wall; and
a point B corresponding to an intersection between the rear frame and the outside wall, wherein point A and point B line a plane that contains longitudinal axis of the nacelle, wherein the point B is offset toward the rear of the nacelle relative to the point A over more than 50% of a periphery of the rear frame.

10. The aircraft nacelle according to claim 9 , wherein the point B is offset toward the rear over the entire periphery of the rear frame.

11. The aircraft nacelle according to claim 9 , wherein a straight line AB defined between point A and point B forms an angle of between 20 and 45° relative to a straight line that passes through point A perpendicular to the longitudinal axis.

Assignees

• Porte Alain
• Lalane Jacques
• Chelin Frederic
• Airbus Operations Sas

Inventors

• Porte Alain
• Lalane Jacques
• Chelin Frederic

Classifications

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