Combination engines for aircraft
AssigneeUnited Technologies Corporation
InventorsFrederick M. Schwarz, Brian M. Fentress, Andrew P. Berryann, Charles E. Lents, Jorn A. Glahn
Life of this patent
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Abstract
An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto.
Claims21
An engine combination for generating forces, the engine combination comprising:
- a gas turbine engine having an air inlet open to the atmosphere, an air compressor, a combustor, a turbine and an exhaust exit nozzle open to the atmosphere all positioned along a fluids flow path passing therethrough for generating force, the air compressor having an air transfer duct extending therefrom so as to be capable to provide compressed air in that air transfer duct at one end thereof;
- and
- an internal combustion engine provided as an intermittent combustion engine having an air intake coupled to combustion chambers therein and a rotatable output shaft also coupled to those combustion chambers for generating force, the air transfer duct being connected to the air intake at an opposite end to be capable of transferring compressed air thereto.
A method of generating force and electrical power using an engine combination of a gas turbine engine having an air inlet open to the atmosphere, an air compressor, a combustor, a turbine and an exhaust exit nozzle open to the atmosphere all positioned along a fluids flow path passing therethrough and of an internal combustion engine provided as an intermittent combustion engine having an air intake coupled to combustion chambers therein, a fuel system coupled to those combustion chambers and a rotatable output shaft also coupled to those combustion chambers, there being an air transfer duct extending from the air compressor to the air intake to transfer compressed air to the air intake from the air compressor, the method comprising:
- operating the gas turbine engine to establish a combustion products flow out the exhaust exit nozzle;
- and
- distributing air compressed in the air compressor of the gas turbine engine to the air intake of the intermittent combustion engine.
A power generation system for propelling, and generating electrical power in, an aircraft, the system comprising:
- a turbofan engine in an engine compartment in the aircraft with an air inlet in the aircraft open to the atmosphere and leading to an air compressor in the turbofan engine followed by a combustor, the air compressor having an 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 air transfer duct being connected to the air intake to transfer compressed air thereto, and
- a primary electrical generator in the aircraft having a rotatable input shaft mechanically coupled through a coupler to the intermittent combustion engine output shaft and having an output conductor with the output conductor being electrically energized in response to rotation of the input shaft.
Dependencies are inferred from the claim text.