Assembly for an aircraft comprising an engine of the “open rotor puller” type and means for attaching the latter to the rigid structure of an attachment pylon

Patent metadata

Field	Value
Publication number	US-10647440-B2
Application number	US-201715823890-A
Country	US
Kind code	B2
Filing date	Nov 28, 2017
Priority date	Nov 29, 2016
Publication date	May 12, 2020
Grant date	May 12, 2020

Abstract

To allow the attachment of an engine of the “Open Rotor Puller” type to the rigid structure of an attachment pylon, an attachment structure comprises a first attachment structure shifted forwards with respect to the center of gravity of the engine and connected to the rigid structure through a pyramid, a second attachment structure laid out at the rear with respect to the first attachment structure and extending in a plane of a first stringer of the rigid structure, and a third attachment structure laid out at the rear with respect to the second attachment structure. The second attachment structure comprises two engine attachments for recovering the moment along the axis of the engine, laid out on either side of a horizontal symmetry plane of the engine.

First claim

The invention claimed is:

1. An assembly for an aircraft, comprising:
a part of an aircraft airframe,
an engine comprising a gas generator and a receiver with a pair of contrarotating unducted rotors positioned forward of the gas generator and centered along an axis of the engine,
an attachment pylon comprising a rigid structure in the form of a box section which has a proximal end connected to the aircraft airframe part and a distal end laterally separated from the proximal end,
attachment means for attaching the engine to the attachment pylon,

in which:
the rigid structure comprises a rear closure stringer and a first stringer set out forward of the rear closure stringer,
the engine has a center of gravity shifted forward with respect to the rigid structure,
the attachment means comprise first attachment means shifted forward with respect to the center of gravity, second attachment means laid out to the rear with respect to the first attachment means and extending in a plane of the first stringer, and third attachment means laid out to the rear with respect to the second attachment means,
the attachment pylon comprises a pyramid connecting the first attachment means to the rigid structure, and
the second attachment means comprise two engine attachments, which are positioned one on each side of a horizontal plane of symmetry of the engine.

2. An assembly for an aircraft according to claim 1 , in which the first attachment means comprise a first frame borne by the pyramid and bearing each engine attachment of the first attachment means.

3. An assembly for an aircraft according to claim 1 , in which the first attachment means comprise two engine attachments for reacting thrust forces which are laid out diametrically opposite one another about the axis of the engine and symmetrically with respect to the horizontal plane of symmetry of the engine.

4. The assembly for an aircraft according to claim 1 , in which the second attachment means comprise a second frame borne by the distal end of the rigid structure and bearing the two engine attachments for reacting moment about the axis of the engine.

5. An assembly for an aircraft according to claim 2 , in which the first attachment means comprise two first engine attachments for reacting forces in vertical and transverse directions of the engine, these being arranged one on each side of the horizontal plane of symmetry of the engine.

6. The assembly for an aircraft according to the combination of claim 2 , in which the attachment means comprise two first bars respectively connecting two first regions of the first frame, to which the two engine attachments that react thrust forces are respectively connected, to two second regions of the second frame.

7. The assembly for an aircraft according to claim 6 , in which the attachment means comprise two second bars respectively connecting the two first regions to two third regions of the second frame and arranged between the two second regions in a continuation of the first stringer.

8. The assembly for an aircraft according to claim 7 , in which the attachment means comprise two third bars respectively connecting the two second regions of the second frame to the third attachment means.

9. The assembly for an aircraft according to claim 8 , in which the rigid structure comprises an intermediate stringer arranged between the rear closure stringer and the first stringer, and
in which the attachment means comprise two fourth bars respectively connecting the two second regions of the second frame to a region of the distal end of the rigid structure arranged in the continuation of the intermediate stringer.

10. An assembly for an aircraft, comprising:
a part of an aircraft airframe;
an engine comprising a gas generator and a receiver with a pair of contrarotating unducted rotors positioned forward of the gas generator and centered along an axis of the engine;
an attachment pylon comprising a rigid structure in the form of a box section which has a proximal end connected to the aircraft airframe part and a distal end laterally separated from the proximal end;
attachment means for attaching the engine to the attachment pylon,

in which:
the rigid structure comprises a rear closure stringer and a first stringer set out forward of the rear closure stringer;
the engine has a center of gravity shifted forward with respect to the rigid structure;
the attachment means comprise first attachment means shifted forward with respect to the center of gravity, second attachment means laid out to the rear with respect to the first attachment means and extending in a plane of the first stringer, and third attachment means laid out to the rear with respect to the second attachment means; and
the second attachment means comprise two engine attachments, which are positioned one on each side of a horizontal plane of symmetry of the engine, wherein the third attachment means comprise two second engine attachments arranged one on each side of the horizontal plane of symmetry of the engine.

11. An assembly for an aircraft according to claim 1 , wherein the second attachment means and the third attachment means are laid out to the rear with respect to the center of gravity.

Assignees

• Airbus Operations Sas

Inventors

• Bouchet Eric
• Colmagro Jérôme
• Nanda Rohan
• Hernandez Perez Misael

Classifications

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title

• B64D27/26 Primary

  Operations & Transport · mapped topic

• B64D2027/268

  Operations & Transport · mapped topic

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• F01D17/085 Primary

  to temperature · CPC title