Air input structure for an aircraft nacelle

Patent metadata

Field	Value
Publication number	US-10676203-B2
Application number	US-201715834605-A
Country	US
Kind code	B2
Filing date	Dec 7, 2017
Priority date	Dec 20, 2016
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment.

First claim

The invention claimed is:

1. An air input structure for a nacelle of an aircraft, said air input structure comprising:
an air input lip with U-shaped section open to the rear and ensuring the distribution of the air between an internal face and an external face; and
a front reinforcement frame placed inside the air input lip and secured to the air input lip in an internal junction zone on the side of the internal face and an external junction zone on the side of the external face, the front part of the air input lip having a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having a first thickness, each segment having a first edge, a second edge, an internal edge and an external edge, at least the internal edge and the external edge of each segment having a thickness equal to the first thickness and rest of the segment having a second thickness smaller than the first thickness,
the air input lip having, between the internal junction zone and the first thickness of the internal edge, an internal portion having a thickness equal to the first thickness, and between the external junction zone and the first thickness of said external edge, an external portion having a thickness equal to the first thickness,
wherein the internal edge and the external edge are unitary with the rest of the segment, and are made of a same material as that of the rest of the segment.

2. The air input structure according to claim 1 , wherein, each segment comprises a predefined cutting line, identifiable from outside of the segment and running in the middle of each of regions of at least the internal edge and the external edge having first thickness.

3. A nacelle for an aircraft engine, said nacelle having an air input structure according to claim 1 .

4. An aircraft comprising at least one nacelle according to claim 3 .

5. A method for repairing an air input structure according to claim 2 , said repair method comprising:
a cutting step during which an affected segment is cut along the cutting line,
a placement step during which a replacement segment identical to the cut segment is fitted in place of the cut segment, and
a fixing step during which the replacement segment is fixed by splices fixed by screwing or riveting from the outside of the segment on the regions having first thickness.

6. The repair method according to claim 5 , wherein the placement step comprises:
a prepositioning substep during which a template showing traces of holes to be produced is placed around the replacement segment and the air input lip,
a drilling substep during which holes are drilled at the appropriate points defined by the template, and
a placement substep during which screws or rivets are placed in the holes thus produced.

Assignees

• Airbus Operations Sas
• Airbus Sas

Inventors

• Porte Alain
• Oberle Patrick
• Albet Gregory

Classifications

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• B64F5/40

  Maintaining or repairing aircraft · CPC title

• B64D33/02 Primary

  of combustion air intakes · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F05D2230/80

  Repairing, retrofitting or upgrading methods · CPC title