Patent ID: 7770840
Filing Date: 2010-08-10
Classification: B64D

Abstract:
1. An engine assembly for aircraft comprising: a turboshaft engine having a longitudinal axis defining a longitudinal direction perpendicular to a vertical direction and to a transversal direction, said longitudinal, vertical and transversal directions being orthogonal to each other; an attachment strut; and a plurality of engine mounts interposed between the attachment strut and the turboshaft engine; the plurality of engine mounts comprising first and second forward mounts each configured to transmit forces from said engine to said attachment strut along said transversal direction of the turboshaft engine, the first and second forward mounts being arranged in a staggered manner in relation to each other in a vertical direction of the turboshaft engine, wherein the first forward mount is configured to transmit forces from said engine to said attachment strut only along the transversal direction of the turboshaft engine and not along the longitudinal nor the vertical directions, whereas the second forward mount is configured to transmit forces from said engine to said attachment strut only along the transversal and vertical directions and not along the longitudinal direction, and wherein the first and second forward mounts are configured to transmit a moment load about the longitudinal axis from said engine to said attachment strut via forces transmitted along said transversal direction of said turboshaft engine.