Patent ID: 8967958
Filing Date: 2015-03-03
Classification: F02C,F02K,Y02T

Abstract:
1. A bypass axial turbomachine, comprising: an axial compressor, the compressor being traversed by a flow referred to as primary of the turbomachine; an annular wall surrounding the compressor and delineating an internal surface of a flow referred to as secondary of the turbomachine; a passage configured to generate a discharge flow rate controlled from the primary flow in the compressor toward the secondary flow, the passage opening into the wall delineating the internal surface of the secondary flow, the discharge flow rate forming an exit flow of the passage; an oil lubrication and cooling circuit for lubricating and cooling elements of the turbomachine; and a heat exchanger configured to cool the oil of the lubrication circuit and arranged at least partially directly in the discharge flow rate of the primary flow, the heat exchanger being arranged in the annular secondary flow, on the annular wall, directly downstream of the junction of the passage of the discharge flow rate with the annular wall, the heat exchanger comprising a flow guiding wall extending on the upstream side, the upstream side of the flow guiding wall partially encountering the exit flow of the discharge flow rate, the flow guiding wall being configured to extend partially over the passage.