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A cooling system for a hybrid aircraft includes an inlet which extends through the body to communicate airflow to a powerplant subsystem and out through an exhaust within a rotor duct. In a hover mode, there is a significant low-pressure area created inside the rotor duct by the rotor system. The lo

A cooling system for a hybrid aircraft includes an inlet which extends through the body to communicate airflow to a powerplant subsystem and out through an exhaust within a rotor duct. In a hover mode, there is a significant low-pressure area created inside the rotor duct by the rotor system. The low-pressure area within the rotor duct assists in drawing air through the inlet and over the engine via the exhaust. A cooling fan is located adjacent the inlet to augment cooling-air flow. The cooling fan is smaller than conventional practice because it does not have to provide the entire pressure difference to force air-cooling flow over the engine. In a transition mode, the low-pressure area created inside the rotor duct decreases but ram air pressure through the inlet increases. In a forward flight mode, the pressure inside the rotor duct is approximately atmospheric but significant ram air is provided from the inlet due to forward flight speed.

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A cooling system for a hybrid aircraft includes an inlet which extends through the body to communicate airflow to a powerplant subsystem and out through an exhaust within a rotor duct. In a hover mode, there is a significant low-pressure area created inside the rotor duct by the rotor system. The lo

A cooling system for a hybrid aircraft includes an inlet which extends through the body to communicate airflow to a powerplant subsystem and out through an exhaust within a rotor duct. In a hover mode, there is a significant low-pressure area created inside the rotor duct by the rotor system. The low-pressure area within the rotor duct assists in drawing air through the inlet and over the engine via the exhaust. A cooling fan is located adjacent the inlet to augment cooling-air flow. The cooling fan is smaller than conventional practice because it does not have to provide the entire pressure difference to force air-cooling flow over the engine. In a transition mode, the low-pressure area created inside the rotor duct decreases but ram air pressure through the inlet increases. In a forward flight mode, the pressure inside the rotor duct is approximately atmospheric but significant ram air is provided from the inlet due to forward flight speed. 9188, 19901100, Schobi; US-4977595, 19901200, Ohta et al.; US-4984270, 19910100, LaBounty; US-4985615, 19910100, Iijima; US-4987593, 19910100, Chaum; US-4993068, 19910200, Piosenka et al.; US-4995081, 19910200, Leighton et al.; US-4996711, 19910200, Chaum; US-5001753, 19910300, Davio et al.; US-5003594, 19910300, Shinagawa; US-5005200, 19910400, Fischer; US-5010239, 19910400, Mita; US-5012074, 19910400, Masada; US-5012076, 19910400, Yoshida; US-5014312, 19910500, Lisimaque et al.; US-5016274, 19910500, Micali et al.; US-5038025, 19910800, Kodera; US-5068894, 19911100, Hoppe; US-5093862, 19920300, Scwartz; US-5097115, 19920300, Ogasawara et al.; US-5120939, 19920600, Claus et al.; US-5128997, 19920700, Pailles et al.; US-5131038, 19920700, Puhl et al.; US-5142578, 19920800, Matyas et al.; US-5146499, 19920900, Geffrotin; US-5148481, 19920900, Abraham et al.; US-5161231, 19921100, Iijima; US-5162989, 19921100, Matsuda, 364/401; US-5163098, 19921100, Dahbura; US-5164988, 19921100, Matyas et al.; US-5165043, 19921100, Miyahara et al.; US-5166503, 19921100, Mizuta; US-5175416, 19921200, Mansvelt et al.; US-5180901, 19930100, Hiramatsu; US-5191193, 19930300, Le Roux; US-5191608, 19930300, Geronimi; US-5200999, 19930400, Matyas et al.; US-5201000, 19930400, Matyas et al.; US-5202922, 19930400, Iijima; US-5214702, 19930500, Fischer; US-5224162, 19930600, Okamoto et al.; US-5243175, 19930900, Kato; US-5247578, 19930900, Pailles et al.; US-5293577, 19940300,