Engine assembly with direct drive of generator
First Claim
1. An engine assembly for use as an auxiliary power unit for an aircraft, the engine assembly comprising:
- at least one internal combustion engine in driving engagement with an engine shaft;
a generator having a generator shaft in driving engagement with the engine shaft to provide electrical power for the aircraft, the generator and engine shafts being directly engaged to one another such as to be rotatable at a same speed;
a compressor having an outlet in fluid communication with an inlet of the at least one internal combustion engine; and
a turbine having an inlet in fluid communication with an outlet of the at least one internal combustion engine.
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Accused Products
Abstract
An engine assembly for use as an aircraft auxiliary power unit, having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.
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Citations
20 Claims
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1. An engine assembly for use as an auxiliary power unit for an aircraft, the engine assembly comprising:
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at least one internal combustion engine in driving engagement with an engine shaft; a generator having a generator shaft in driving engagement with the engine shaft to provide electrical power for the aircraft, the generator and engine shafts being directly engaged to one another such as to be rotatable at a same speed; a compressor having an outlet in fluid communication with an inlet of the at least one internal combustion engine; and a turbine having an inlet in fluid communication with an outlet of the at least one internal combustion engine. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. An engine assembly for use as an auxiliary power unit for an aircraft, the engine assembly comprising:
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at least one internal combustion engine in driving engagement with an engine shaft; a generator having a generator shaft in driving engagement with the engine shaft to provide electrical power for the aircraft, the generator and engine shafts being directly engaged to one another such as to be rotatable at a same speed; a compressor having an outlet in fluid communication with an inlet of the at least one internal combustion engine; a first stage turbine having an inlet in fluid communication with an outlet of the at least one internal combustion engine; and a second stage turbine having an inlet in fluid communication with an outlet of the first stage turbine; wherein at least one of the turbines is in driving engagement with the compressor. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19)
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20. A method of providing electrical power to an aircraft, the method comprising:
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flowing compressed air from an outlet of a compressor to an inlet of at least one internal combustion engine of an engine assembly; rotating an engine shaft with the at least one internal combustion engine; driving a generator providing electrical power to the aircraft with the engine shaft through a direct drive engagement between a shaft of the generator and the engine shaft causing the shaft of the generator and the engine shaft to rotate at a same speed; and driving a turbine of the engine assembly with exhaust from the at least one internal combustion engine.
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Specification