Internal structure of a primary exhaust duct having a separator of which the geometry varies depending on the temperature

Patent metadata

Field	Value
Publication number	US-11519302-B2
Application number	US-202117181566-A
Country	US
Kind code	B2
Filing date	Feb 22, 2021
Priority date	Feb 24, 2020
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

An internal structure of a primary exhaust duct of a turbomachine, which has a primary wall allowing air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin arranged inside the primary wall, and at least one separator of which a first edge region is attached to the interior skin and which has two geometries. A change from the first geometry to the second takes place when the temperature of the separator exceeds a first temperature, and the change from the second to the first takes place when the temperature of the separator drops below a second temperature. The coefficient of expansion of the separator is greater than that of the interior skin. The variation in the geometry of the separators depending on the temperature of the engine eases assembly at ambient temperature due to the compression of the separators.

First claim

The invention claimed is:

1. An internal structure of a primary exhaust duct of a turbomachine, said internal structure comprising:
a primary wall comprising a plurality of holes and a surface of revolution about a longitudinal axis, allowing air to pass through the plurality of holes and forming an internal surface of the primary exhaust duct,
an interior skin comprising a surface of revolution about the longitudinal axis, arranged inside the primary wall, and
a separator having a first edge, the separator attached only to the interior skin and only by a region along the first edge, the separator capable of changing from a first geometry to a second geometry,
wherein a change from the first geometry to the second geometry takes place when a temperature of the separator exceeds a first temperature, and a change from the second geometry to the first geometry takes place when the temperature of the separator drops below a second temperature less than or equal to the first temperature,
wherein a coefficient of expansion of the separator is greater than that of the interior skin,
wherein, in the first geometry, the separator is wound on itself,
wherein, in the second geometry, the separator is unwound and fully extends so as to bring a second edge of the separator adjacent to the primary wall, and
wherein a gap is maintained between the separator and the primary wall at all times.

2. The internal structure according to claim 1 , further comprising two attachments attaching the region along the first edge of the separator to the interior skin, wherein each of the two attachments allows rotation of the separator about an axis perpendicular to the interior skin.

3. The internal structure according to claim 2 , wherein at least one of the two attachments forms a respective guide, wherein each guide, guides the separator with respect to the interior skin, which allows a movement of the first edge over the interior skin.

4. The internal structure according to claim 3 , wherein each guide is formed as a bolt that sandwiches the separator and the interior skin through a first orifice passing through the separator and a second orifice passing though the interior skin, and wherein one of the orifice passing through the separator or the orifice passing through the interior skin has a shape allowing a movement of the bolt.

5. A turbomachine having a primary exhaust duct bounded outwardly by a primary nozzle and inwardly by an internal structure of the primary exhaust duct of the turbomachine, said internal structure comprising:
a primary wall comprising a plurality of holes and a surface of revolution about a longitudinal axis, allowing air to pass through the plurality of holes and forming an internal surface of the primary exhaust duct,
an interior skin comprising a surface of revolution about the longitudinal axis, arranged inside the primary wall, and
a separator having a first edge, the separator attached only to the interior skin and only by a region along the first edge, the separator capable of changing from a first geometry to a second geometry,
wherein a change from the first geometry to the second geometry takes place when a temperature of the separator exceeds a first temperature, and a change from the second geometry to the first geometry takes place when the temperature of the separator drops below a second temperature less than or equal to the first temperature,
wherein a coefficient of expansion of the separator is greater than that of the interior skin,
wherein, in the first geometry, the separator is wound on itself,
wherein, in the second geometry, the separator is unwound and fully extends so as to bring a second edge of the separator adjacent to the primary wall, and
wherein a gap is maintained between the separator and the primary wall at all times.

6. An aircraft having a turbomachine having a primary exhaust duct bounded outwardly by a primary nozzle and inwardly by an internal structure of the primary exhaust duct of the turbomachine, said internal structure comprising:
a primary wall comprising a plurality of holes and a surface of revolution about a longitudinal axis, allowing air to pass through the plurality of holes and forming an internal surface of the primary exhaust duct,
an interior skin comprising a surface of revolution about the longitudinal axis, arranged inside the primary wall, and
a separator having a first edge, the separator attached only to the interior skin and only by a region along the first edge, the separator capable of changing from a first geometry to a second geometry,
wherein a change from the first geometry to the second geometry takes place when a temperature of the separator exceeds a first temperature, and a change from the second geometry to the first geometry takes place when the temperature of the separator drops below a second temperature less than or equal to the first temperature,
wherein a coefficient of expansion of the separator is greater than that of the interior skin,
wherein, in the first geometry, the separator is wound on itself,
wherein, in the second geometry, the separator is unwound and fully extends so as to bring a second edge of the separator adjacent to the primary wall, and
wherein a gap is maintained between the separator and the primary wall at all times.

Assignees

• Airbus Operations Sas

Inventors

• Andre Sandrine
• Trocellier Vincent
• Ferreira Julien
• Kilkenny Michael

Classifications

• F05D2260/963

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• B64D33/06

  Silencing exhaust or propulsion jets · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/04

  Mounting of an exhaust cone in the jet pipe · CPC title

• F02K1/827 Primary

  Sound absorbing structures or liners · CPC title