Patent ID: 7690189
Filing Date: 2010-04-06
Classification: F02C,F05D

Abstract:
1. A power generation system for propelling, and generating electrical power in, an aircraft, the system comprising: a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft open to the atmosphere and an inlet duct with a duct wall thereabout that is curved along its extent in extending from the air inlet along a curved path leading to an air compressor in the gas turbine engine followed therein by a combustor, the air compressor having a compressor air transfer duct extending therefrom so as to be capable of providing compressed air therein and to the combustor; an internal combustion engine provided as an intermittent combustion engine in the aircraft having an air intake coupled to combustion chambers therein, a rotatable output shaft also coupled to those combustion chambers for generating force, and a fuel system for providing fuel to those combustion chambers, the compressor air transfer duct being connected to the air intake to transfer compressed air thereto, and an inlet duct manifold positioned adjacent to the duct wall of the inlet duct on the air compressor side of a curve therein so as to permit drawing air therein that has previously entered the inlet duct and with the inlet duct manifold having an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake such air can be selectively drawn from the inlet duct into that intermittent combustion engine air intake.