A helicopter is driven by means of a rotor that is connected with an internal-combustion engine. The air-cooled internal-combustion engine has a horizontally opposed construction and is arranged within walls of a cabin of the helicopter. In order to supply the internal-combustion engine with cooling air and intake air, air inlet openings are provided at the side walls of the cabin. For the discharge of the cooling air, outlet openings are arranged at the underside of the cabin.
A rotary wing aircraft with rotor blades mounted on a rotor head and with reaction drive. The rotor blades have hollow interiors and are provided on their trailing edge with at least one outlet opening for compressed air supplied via the rotor head. Such rotor head may include an air suction region in which there is mounted a suction device having a pressure side connected to the hollow interiors of the rotor blades.
A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separately within a nacelle. The system includes the auxiliary power unit housed within the nacelle of the aircraft, an engine exhaust opening defined in the aft portion of the nacelle and communicating with the gas turbine engine, at least a first air inlet duct communicating with a second opening defined in said nacelle and with said compressor portion and the oil cooler is located within a second duct communicating with an opening other than the engine exhaust opening of said nacelle and with the engine exhaust opening. Exterior cooling air and engine exhaust ejected through said engine exhaust opening entrain cooling air through said second duct to said oil cooler, and thus provide engine oil cooling. An exhaust eductor is also provided.
A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separately within a nacelle. The system includes the auxiliary power unit housed within the nacelle of the aircraft, an engine exhaust opening defined in the aft portion of the nacelle and communicating with the gas turbine engine, at least a first air inlet duct communicating with a second opening defined in said nacelle and with said compressor portion and the oil cooler is located within a second duct communicating with an opening other than the engine exhaust opening of said nacelle and with the engine exhaust opening. Exterior cooling air and engine exhaust ejected through said engine exhaust opening entrain cooling air through said second duct to said oil cooler, and thus provide engine oil cooling. An exhaust eductor is also provided.
A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separately within a nacelle. The system includes the auxiliary power unit housed within the nacelle of the aircraft, an engine exhaust opening defined in the aft portion of the nacelle and communicating with the gas turbine engine, at least a first air inlet duct communicating with a second opening defined in said nacelle and with said compressor portion and the oil cooler is located within a second duct communicating with an opening other than the engine exhaust opening of said nacelle and with the engine exhaust opening. Exterior cooling air and engine exhaust ejected through said engine exhaust opening entrain cooling air through said second duct to said oil cooler, and thus provide engine oil cooling. An exhaust eductor is also provided.
An exhaust silencer assembly comprising a casing having an exhaust gas entrance opening, an exhaust gas exit opening, and a cooling air inlet opening, and an acoustic-attenuating porous liner disposed within an interior chamber of the casing, thereby dividing the interior chamber into an inner region located between the exhaust gas entrance opening and the exhaust gas exit opening, and an outer region located between the acoustic-attenuating porous liner and the casing, where the cooling air inlet opening is located at the outer region.
