US 11,440,670 B2Granted

Suspension device

AssigneeSafran Aircraft Engines

InventorsAntoine Elie Hellegouarch, Marc Patrick Tesniere

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Abstract

The invention concerns a suspension device (4) for a turbomachine comprising a body (15) intended to be fixed to a fixed part of an aircraft, extending along a longitudinal axis (A) intended to be parallel to a driving shaft axis of the turbomachine once the suspension device (4) is connected to the turbomachine, a first connecting rod (28) and a second connecting rod (29) located in the same transverse plane (P) perpendicular to the longitudinal axis (A) of the body, each comprising a first end articulated with respect to the body (15), and a second end intended to be articulated to a first part of the turbomachine, a third connecting rod (37) articulated on the body (15) between the first ends of the first and second connecting rods (28, 29) and intended to be articulated on a first part of the turbomachine between the second ends of the first and second connecting rods (28, 29), the suspension device (4) being characterised in that it further comprises a rudder (45) articulated on the body (15) and a fourth connecting rod (59) and a fifth connecting rod (60) each extending along an axis of extension (L1, L2) and each comprising a first end (61, 62) articulated on the rudder (45) and a second end (63, 64) intended to be articulated on a second part of the turbomachine.

Claims20

Dependent claims

Suspension device for a turbomachine, comprising:

a body intended to be attached to a fixed part of an aircraft, extending along a longitudinal axis intended to be parallel to a driving shaft axis of the turbomachine once the suspension device is connected to the turbomachine,
a first connecting rod and a second connecting rod located in a transverse plane perpendicular to the longitudinal axis, each rod comprising a first end articulated with respect to the body and a second end to be articulated on a first part of the turbomachine,
a third connecting rod articulated on the body between the first ends of the first and second connecting rods, to be articulated on the first part of the turbomachine between the second ends of the first and second connecting rods,
the suspension device being characterised in that it further comprises:
a rudder hinged to the body,
a fourth connecting rod and a fifth connecting rod, each extending along an axis of extension and each comprising a first end articulated on the rudder and a second end intended to be articulated on a second part of the turbomachine,
the points of intersection between the extension axes of the fourth and fifth connecting rods and the transverse plane being located between the first connecting rod and the second connecting rod and on either side of the third connecting rod in a transverse direction.

4 more elements

Dependencies are inferred from the claim text.

Facts

Application: 16/956,494Filed 14 Dec 2018
Priority: FR 176266320 Dec 2017
Published: US 2021/0094695 A11 Apr 2021
Granted: 13 Sep 2022
Term ends: Not estimatedThe source records don’t support an estimate.

Classification5 codes

B64D 27/404
Arrangements for mounting power plants in aircraft: suspension arrangements specially adapted for supporting vertical loads
B64D 27/406
Arrangements for mounting power plants in aircraft: suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links
B64D 27/10
Aircraft characterised by the type or position of power plants: of gas-turbine type
B64D 27/16
Aircraft characterised by the type or position of power plants: of jet type

Family

US 2021/0094695 A1Pre-grant publication · published 1 Apr 2021
US 11,440,670 B2This patent

From the US filing history. Foreign family members aren’t listed.

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