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US 2008/0156930 A1Published application
Engine Mount For an Aircraft, to be Placed Between an Engine and an Engin Mounting Structure
AssigneeAirbus France
InventorsVirginie Audart-Noel, Pascal Gardes
Life of this patent
Estimating the term…
Abstract
An aircraft engine attachment configured to be inserted between an engine and an EMS, the attachment including a clevis connected to a first fixing device including an end fitting with two arms and a pin passing through the clevis and the two arms, in each of which an orifice is formed including a first ring and a second ring respectively holding the pin. The first ring includes a bottom acting as a stop for a first end of the pin, and the first attachment device includes a mechanism to stop the pin in translation cooperating with a second end of the pin.
Claims16
1-15. (canceled)
16:
- An aircraft engine attachment configured to be inserted between an engine and an EMS for the engine, the attachment comprising:
- a clevis connected to a first fixing device including an end fitting with two arms and a pin passing through the clevis and the two arms, in each of which an orifice is formed including a first ring and a second ring respectively holding the pin, wherein the first ring includes a bottom acting as a stop for a first end of the pin, and wherein the first attachment device includes means for stopping the pin in translation, cooperating with a second end of the pin.
17:
- An engine attachment according to claim 16, wherein the pin translation stop means is installed on the second ring.
18:
- An engine attachment according to claim 16, wherein the pin translation stop means includes a nut and a locking nut screwed onto the second ring.
19:
- An engine attachment according to claim 18, wherein the pin translation stop means also includes at least one spring-washer bearing in contact with the nut and in contact with the second end.
20:
- An engine attachment according to claim 19, wherein the nut is bearing in contact with a shoulder formed in the second ring.
21:
- An engine attachment according to claim 20, wherein the translation stop means also includes a safety rod passing transversely through the second ring.
22:
- An engine attachment according to claim 16, further comprising a ball joint inserted between the pin and the clevis.
23:
- An engine attachment according to claim 16, wherein the clevis is triangular.
24:
- An engine attachment according to claim 23, wherein the triangular clevis is also connected to a second fixing device identical to the first fixing device, the first and second fixing devices being located close to two vertices of the triangular clevis.
25:
- An engine attachment according to claim 24, forming two half-attachments each configured to resist forces applied along a transverse direction and along a vertical direction of the engine.
26:
- An engine attachment according to claim 25, further comprising a third fixing device close to a third vertex of the triangular clevis, the third fixing device configured to be rigidly fixed to the EMS.
27:
- An assembly for an aircraft comprising:
- an engine;
- an EMS;
- and
- a plurality of engine attachments inserted between the EMS and the engine, wherein the plurality of engine attachments comprise at least one engine attachment according to claim 16.
2 more elements
28:
- An assembly according to claim 27, wherein the engine attachment is a forward attachment.
29:
- An assembly according to claim 28, wherein the clevis is parallel to a transverse direction of the engine, and inclined such that a distance from a fan casing of the engine increases in the aft direction.
30:
- An assembly according to claim 29, wherein the end fitting on each of the first two fixing devices is rigidly fixed onto the engine, symmetrically about a vertical plane passing through a longitudinal axis of the engine.