AIRCRAFT POWER PLANT

There is disclosed a cooling system (201) for a liquid cooled internal combustion aircraft power plant (200) for an aircraft having a tail cone (T). The cooling system (201) has: an air inlet (202a) defined through a wall (T2) of the tail cone (T) and fluidly connected to an environment (E) outside...

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Bibliographische Detailangaben
1. Verfasser:	DIONNE, Luc
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HELICOPTERS PARACHUTES PERFORMING OPERATIONS TRANSPORTING
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Beschreibung
Zusammenfassung:	There is disclosed a cooling system (201) for a liquid cooled internal combustion aircraft power plant (200) for an aircraft having a tail cone (T). The cooling system (201) has: an air inlet (202a) defined through a wall (T2) of the tail cone (T) and fluidly connected to an environment (E) outside the aircraft; a heat exchanger (126) having at least one first conduit (126b) fluidly connected to the environment (E) via the air inlet (202a) and at least one second conduit (126a) in heat exchange relationship with the at least one first conduit (126b) and fluidly connectable to a coolant circuitry (112c) of the liquid cooled internal combustion aircraft power plant (200); a blower (214) fluidly connected to the environment (E) via the air inlet (208a, 202a); and an air outlet (C1) fluidly connected to the blower (214) and defined through a wall (T2, C2) of the aircraft upstream of the air inlet (208a, 202a) relative to a direction of an airflow (D2) along the aircraft.