Patent ID: 8061649
Filing Date: 2011-11-22
Classification: B64D,F01D,F02C,Y02T

Abstract:
1. An aircraft engine assembly, comprising: an engine; an engine suspension pylon, the pylon including a rigid structure that includes a box and a structural block installed fixed on the box between the box and the and the engine, and the pylon including a mounting system inserted between the engine and the rigid structure, the mounting system including an aft engine suspension, the structural block including an attachment interface for the aft engine suspension; a heat exchanger system including an exchanger to which a hot fluid inlet, a cold air inlet, a first outlet communicating with the hot fluid inlet, and at least one second outlet communicating with the cold air inlet are connected, the hot fluid inlet being provided on a hot air duct connected to the exchanger and passing through the structural block in a longitudinal direction of the rigid structure, and each second outlet from the heat exchanger system being located between the box and the engine; wherein each second outlet is located aft from the aft engine suspension, and wherein the exchanger in the heat exchanger system is at least partially arranged inside an aft aerodynamic fairing of the suspension pylon, the aft aerodynamic fairing being located entirely aft from the aft engine suspension.