Multifunction power system for an aircraft
AssigneeLockheed Corporation
InventorMichael J. Cronin
Life of this patent
Estimating the term…
Abstract
The multifunction power system is a combination auxiliary power unit, environmental control system, engine start system, and emergency power system for an aircraft. The system is essentially a four-wheel auxiliary power unit comprising two compressors driven by one turbine by means of a common shaft and in addition a free turbine. The pressurized flow from the second compressor can be directed to parallel combustors and thereafter to the two turbines. A starter-generator and motor are coupled to the compressor drive shaft and the free turbine is used to power a generator and for engine starting. Ducts, heat exchangers, valves, etc., are so arranged as to provide the four functions by proper selection and routing of air.
Claims10
A multifunction power system for an aircraft, the aircraft having at least one engine and at least one compartment requiring conditioned air, the system comprising:
- a drive shaft;
- a compressor means coupled to said drive shaft, said compressor means having an inlet coupled to the exterior of the aircraft and an outlet;
- a first turbine coupled to said drive shaft for driving said compressor means;
- an electric motor coupled to said drive shaft;
- a starter-generator coupled to said drive shaft;
- a first duct assembly having a first end coupled to said outlet of said compressor means and a bifurcated second end with one leg thereof coupled overboard and a second leg thereof coupled to said at least one compartment, said first duct assembly mounting a first outside air-cooled heat exchanger means, a first combustor, and a second turbine in series, and further mounting a second outside air-cooled heat exchanger means in said second leg;
- a second duct assembly having a first end coupled to said outlet of said compressor means and a bifurcated second end with a first leg thereof coupled to said first duct assembly and a second leg thereof coupled overboard, said second duct assembly coupling a second combustor and said first turbine in series;
- a third duct assembly having a first end coupled to said compartment and a second end having a first leg coupled to said first duct assembly, a second leg coupled to said second duct assembly, and a third leg coupled overboard;
- a first control valve means for controlling the flow from said outlet of said compressor means to said first and second duct assemblies;
- a second control valve means mounted in said first duct assembly for controlling the flow to and between said first and second legs thereof;
- a third control valve means coupled to said second duct assembly for controlling flow to and between said first and second legs thereof;
- a fourth control valve means for controlling the flow in said first duct assembly and from said first leg of said third duct assembly;
- a fifth control valve means for controlling the flow in said second duct assembly and from said second leg of said third duct assembly;
- and
- a sixth control valve means for controlling the flow in said third leg of said third duct assembly.
Dependencies are inferred from the claim text.