Compound engine assembly with bleed air
First Claim
1. An auxiliary power unit for an aircraft, the auxiliary power unit comprising:
- at least one internal combustion engine in driving engagement with an engine shaft, the at least one internal combustion engine having at least one combustion chamber of varying volume;
a bleed conduit having an end configured for connection with a pneumatic system of the aircraft;
a compressor having an outlet in fluid communication with both an inlet of the at least one internal combustion engine and the bleed conduit;
a bleed air valve, the bleed conduit in fluid communication with the outlet of the compressor through the bleed air valve, the bleed air valve selectively opening and closing the fluid communication between the outlet of the compressor and the end of the bleed conduit configured for connection to the pneumatic system, the outlet of the compressor in fluid communication with the inlet of the at least one internal combustion engine independently of the bleed air valve; and
a turbine section having an inlet in fluid communication with an outlet of the at least one internal combustion engine, the turbine section having a turbine shaft configured to compound power with the engine shaft.
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Accused Products
Abstract
A compound engine assembly for use as an auxiliary power unit for an aircraft and including an engine core with internal combustion engine(s), a compressor having an outlet in fluid communication with an engine core inlet, a bleed conduit in fluid communication with the compressor outlet through a bleed air valve, and a turbine section having an inlet in fluid communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in fluid communication with the engine core outlet and a second stage turbine having an inlet in fluid communication the first stage turbine outlet. A method of providing compressed air and electrical power to an aircraft is also discussed.
161 Citations
23 Claims
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1. An auxiliary power unit for an aircraft, the auxiliary power unit comprising:
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at least one internal combustion engine in driving engagement with an engine shaft, the at least one internal combustion engine having at least one combustion chamber of varying volume; a bleed conduit having an end configured for connection with a pneumatic system of the aircraft; a compressor having an outlet in fluid communication with both an inlet of the at least one internal combustion engine and the bleed conduit; a bleed air valve, the bleed conduit in fluid communication with the outlet of the compressor through the bleed air valve, the bleed air valve selectively opening and closing the fluid communication between the outlet of the compressor and the end of the bleed conduit configured for connection to the pneumatic system, the outlet of the compressor in fluid communication with the inlet of the at least one internal combustion engine independently of the bleed air valve; and a turbine section having an inlet in fluid communication with an outlet of the at least one internal combustion engine, the turbine section having a turbine shaft configured to compound power with the engine shaft. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. An auxiliary power unit for an aircraft, the auxiliary power unit comprising:
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at least one internal combustion engine in driving engagement with a common shaft, the at least one internal combustion engine having at least one combustion chamber of varying volume; a generator in driving engagement with the common shaft to provide electrical power for the aircraft; a bleed conduit having an end configured for connection to a pneumatic system of the aircraft; a compressor having a same outlet in fluid communication with both an inlet of the at least one internal combustion engine and the bleed conduit; a bleed air valve, the bleed air valve selectively opening and closing the fluid communication between the end of the bleed conduit and the outlet of the compressor, the outlet of the compressor in fluid communication with the inlet of the at least one internal combustion engine independently of the bleed air valve; 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 first and second stage turbines has a turbine shaft configured to compound power with the common shaft. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19, 20)
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21. A method of providing compressed air and electrical power to an aircraft, the method comprising:
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flowing compressed air from an outlet of a compressor simultaneously to both an inlet of at least one internal combustion engine of an auxiliary power unit and to a bleed conduit in communication with a pneumatic system of the aircraft, the at least one internal combustion engine having at least one combustion chamber of varying volume; driving at least one generator providing electrical power to the aircraft with an engine shaft of the at least one internal combustion engine; and providing electrical power to the aircraft with at least one turbine of the auxiliary power unit including compounding power from a turbine shaft of the at least one turbine with power from the engine shaft. - View Dependent Claims (22, 23)
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Specification