Structure for fastening after-body parts of an aeroengine

Patent metadata

Field	Value
Publication number	US-10066581-B2
Application number	US-201314388895-A
Country	US
Kind code	B2
Filing date	Mar 28, 2013
Priority date	Mar 29, 2012
Publication date	Sep 4, 2018
Grant date	Sep 4, 2018

Abstract

The invention relates to an aeroengine after-body assembly comprising an exhaust casing made of metal having a plurality of arms extending radially between an inner shroud and an outer shroud. The assembly comprises at least one axisymmetric part made of composite material extending between an upstream end fastened to said exhaust casing and a downstream end that is free. In accordance with the invention, the axisymmetric part has an annular portion at its upstream end, which annular portion includes a plurality of slots defining between them a plurality of resilient fastener tabs. Each slot co-operates with an arm of the exhaust casing, which further includes fastener parts attached to the resilient fastening tabs.

First claim

The invention claimed is:

1. An after-body assembly for an aeroengine comprising an exhaust casing made of metal having a plurality of arms extending radially between an inner shroud and an outer shroud, said after-body assembly further comprising an axisymmetric part made of composite material extending between an upstream end fastened to said exhaust casing and a downstream end that is free,
wherein said axisymmetric part has an annular portion at its upstream end, which annular portion includes a plurality of first slots defining between them a plurality of resilient fastener tabs, each one of the plurality of first slots co-operating with a respective one of the plurality of arms, the exhaust casing further including fastener parts to which the plurality of resilient fastening tabs are attached,
wherein each one of the plurality of first slots extends from the upstream end of the axisymmetric part and presents dimensions that correspond to a portion of a respective one of the plurality of arms which a respective one of the plurality of first slots co-operates,
a plurality of second slots extending downstream from a downstream end of each of the plurality of first slots, wherein a trailing edge of a respective one of the plurality of arms abuts the downstream end of the respective one of the plurality of first slots.

2. The after-body assembly according to claim 1 , including an exhaust cone made of composite material fastened on the plurality of arms of the exhaust casing at intermediate positions between the inner shroud and the outer shroud of said exhaust casing, each of said plurality of arms including one of the fastener parts at the level of said intermediate position, with a respective one of the plurality of resilient fastener tabs of the annular portion situated at the upstream end of the exhaust cone being attached to the fastener parts at the level of said intermediate position.

3. The after-body assembly according to claim 1 , including an exhaust nozzle made of composite material fastened on the arms of the exhaust casing in positions close to the outer shroud of said casing, said outer shroud having the fastener parts attached to the resilient fastener tabs of the annular portion situated at the upstream end of the exhaust nozzle.

4. The after-body assembly according to claim 1 , wherein the axisymmetric part is made of composite material comprising fiber reinforcement made of refractory fibers densified by a matrix that is at least partially ceramic.

5. The after-body assembly according to claim 4 , wherein the matrix is a ceramic matrix selected from at least: an oxide; a nitride; a carbide; and a silicide.

6. The after-body assembly according to claim 4 , wherein the axisymmetric part is made of a composite material comprising fiber reinforcement made of silicon carbide fibers densified by a silicon carbide matrix including one or more self-healing phases.

7. The aeroengine including the after-body assembly according to claim 1 .

8. An aircraft fitted with at least one aeroengine according to claim 7 .

Assignees

• Herakles
• Safran Nacelles

Inventors

• Mecuson Gautier
• Conete Eric
• Carrere Benoit
• Philippe Eric

Classifications

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F02K1/78

  Other construction of jet pipes · CPC title

• F01D25/162

  Bearing supports · CPC title

• F01D25/16

  Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C) · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title