Aircraft engine assembly comprising a junction aerodynamic fairing mounted on two separate elements

• US 8,162,254 B2
• Filed: 07/10/2007
• Issued: 04/24/2012
• Est. Priority Date: 07/11/2006
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus Operations SAS (Airbus SE)
• Inventors: Roche, Frederic
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US12/307,142
• Publication Number:
  US 20090283631A1
• Time in Patent Office: 1,750 Days
• Field of Search: 244/53.B, 244/54, 602/261
• US Class Current: 244/54
• CPC Class Codes: B64C 7/02 Nacelles
• CPC Class Codes: B64D 27/402 comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
• CPC Class Codes: B64D 29/08 Inspection panels for power plants

Abstract

An aircraft engine assembly including an engine, an engine mounting structure, and a nacelle surrounding the engine and including an air intake and fan cowls. The assembly further includes a cradle supporting the fan cowls, fixedly mounted on the mounting structure or else on an entity including a fan case and the air intake attached to the case. The engine assembly further includes a junction aerodynamic fairing including a first mounting mechanism mounted on the cradle, and including a second mounting mechanism mounted on the other of the elements from among the mounting structure and the entity.

Claims

1. An aircraft engine assembly comprising:

an engine;

an engine mounting structure;

a nacelle surrounding the engine and comprising an air intake and fan cowls;

a cradle on which the fan cowls are movably mounted, the cradle being fixedly mounted on one of the engine mounting structure and a fan assembly comprising a fan case for the engine and the air intake attached to the fan case;

a cradle aerodynamic cowling housing said cradle, and

a junction aerodynamic fairing extending longitudinally with said cradle aerodynamic cowling along a longitudinal axis X of the engine mounting structure, said junction aerodynamic fairing comprising first mounting means mounted on the cradle and second mounting means mounted on the other of the engine mounting structure and the fan assembly.

2. An engine assembly according to claim 1, wherein the first and second mounting means comprising of the junction aerodynamic fairing are respectively arranged in a vicinity of a forward end and an aft end of the junction aerodynamic fairing, or conversely.

3. An engine assembly according to claim 1, wherein the cradle is fixedly mounted on a rigid structure of the engine mounting structure, the cradle forming an integral part of a forward aerodynamic structure of the mounting structure, and wherein the second mounting means of the junction aerodynamic fairing is mounted on the air intake.

4. An engine assembly according to claim 3, wherein the junction aerodynamic fairing provides an aerodynamic junction between the air intake and said cradle aerodynamic cowling.

5. An engine assembly according to claim 4, wherein the junction aerodynamic fairing is positioned between the air intake and the cradle aerodynamic cowling.

6. An engine assembly according to claim 3, wherein the second mounting means comprises an attachment configured to transmit loads exerted in a longitudinal direction of the engine, in a transverse direction of the engine, and in a vertical direction of the engine.

7. An engine assembly according to claim 1, wherein the cradle is fixedly mounted on the fan case, and wherein the second mounting means or the aerodynamic junction fairing is mounted on a fillet fairing of the engine mounting structure.

8. An engine assembly according to claim 7, wherein the junction aerodynamic fairing provides an aerodynamic junction between the fairing and said cradle aerodynamic cowling.

9. An engine assembly according to claim 7, wherein the first mounting means comprises an attachment configured to transmit loads exerted in a longitudinal direction of the engine, in a transverse direction of the engine, and in a vertical direction of the engine.

10. An aircraft comprising at least one engine assembly according to claim 2, assembled on a wing or an aft portion of the fuselage of the aircraft.