REGULATED OIL COOLING SYSTEM FOR A TURBINE ENGINE WITH DEICING OF THE NACELLE

摘要

The invention relates to an oil cooling system of a turbine engine installed in an aircraft comprising a circuit suitable for circulating the oil between the engine and at least one external heat exchanger placing the oil in thermal communication with a part of the lip of the nacelle, wherein it also comprises at least one air/oil heat exchanger placing the oil in thermal communication with the air circulating in the cold zone of the turbine engine, equipped with a device suitable for varying its oil cooling capacity, and with a control means for said cooling capacity variation device.

主权项

1. An assembly comprising a bypass turbine engine, a nacelle in which said turbine engine is installed, and an oil cooling system for said turbine engine comprising a circuit suitable for circulating the oil between the engine and at least one external heat exchanger consisting of oil pipelines of small diameter in contact with a metal skin constituting the surface of at least a part of the lip of the nacelle, wherein it also comprises at least one air/oil heat exchanger placing the oil in thermal communication with the air circulating in the bypass air stream of the turbine engine, equipped with a device suitable for varying its oil cooling capacity, and with a control means for said cooling capacity variation device.