초록 ▼

The invention is an ECS system designed to utilize an induction motor (12) and a cabin compressor (14) for providing pressurized air that serves as a source of energy for heating, cooling, pressurizing and other air needs of modern aircraft. An aircraft engine driven generator, preferably a permanen

The invention is an ECS system designed to utilize an induction motor (12) and a cabin compressor (14) for providing pressurized air that serves as a source of energy for heating, cooling, pressurizing and other air needs of modern aircraft. An aircraft engine driven generator, preferably a permanent-magnet generator (of the samarium-cobalt, SmCo, type), furnishes variable-voltage/variable frequency, VV/VF, power to the motor (12). The electric motor itself in the preferred embodiment is a highly reliable squirrel-cage induction motor (12) powered directly from the VV/VF supply, with the result that its speed is proportional to the generator frequency, which in turn is dependent on the aircraft engine speed. The main cabin compressor (14) and a secondary (auxiliary) supercharging compressor (18) are both mounted on the motor shaft. The motor-compressor configuration is further characterized in that the ac motor has pole-changing winding (typically two), which permits two speed operation, while the cabin compressor is provided with inlet guide vanes (16). The interactive combination of these two features makes it possible to furnish the requisite air mass flow and pressurization levels over the conditions of variable air density and variable atmospheric pressure, as the airplane operates throughout its flight envelope.

대표청구항 ▼

1. In an aircraft having at least one variable speed aircraft engine and an environmental control system, the improvements comprising: an induction motor, said motor having an axially aligned drive shaft exiting opposite ends thereof; a main cabin compressor arranged to be directly driven by sai

1. In an aircraft having at least one variable speed aircraft engine and an environmental control system, the improvements comprising: an induction motor, said motor having an axially aligned drive shaft exiting opposite ends thereof; a main cabin compressor arranged to be directly driven by said drive shaft on a first end of said motor, said main cabin compressor having an inlet connected to a first outside or ram air inlet and adapted to pressurize the cabin of said aircraft; a supercharger compressor arranged to be driven by said motor through a clutch on the opposite end of said motor, said supercharger compressor having an inlet coupled to a second outside or ram air inlet and an outlet coupled to said main cabin compressor; valve means having a first position isolating said supercharging compressor from said main cabin compressor and a second position coupling said supercharging compressor in series to said main cabin compressor and isolating said first outside or ram air inlet from said main cabin compressor; and at least one generator driven by said at least one aircraft engine for providing variable voltage/variable frequency power to said motor, said at least one generator being directly driven by said at least one engine. 2. In an aircraft having at least one variable speed aircraft engine and an environmental control system, the improvements comprising: at least one generator driven by said at least one aircraft engine; a two-speed induction motor arranged to receive power from said at least one generator; a main cabin compressor arranged to be directly driven by said induction motor, said main cabin compressor having an inlet connected to a first outside or ram air inlet and adapted to pressurize the cabin of said aircraft; a supercharging compressor arranged to be driven by said induction motor, said supercharging compressor having an inlet connected to a second outside or ram air inlet and an outlet coupled to said inlet of said main cabin compressor; valve means having a first position isolating said supercharging compressor from said main cabin compressor and a second position coupling said supercharging compressor in series to said main cabin compressor and isolating said first outside or ram air inlet from said main cabin compressor; and an expansion cooling turbine having an inlet coupled to the outlet of said main cabin compressor and an outlet coupled to said cabin arranged to be driven by said induction motor. 3. An aircraft as in claim 2, wherein said supercharger compressor is driven through an electromagnetic clutch. 4. An aircraft as in claim 2, wherein said at least one generator is a synchronous ac generator of a permanent magnet type. 5. An aircraft as in claim 4, wherein said at least one generator is as samarium-cobalt generator. 6. An aircraft as in claim 2, wherein said at least one generator is a wound-field type generator. 7. An aircraft as in claim 2, wherein said induction motor is a squirrel-cage rotor type motor. 8. An aircraft as in claim 2, wherein said induction motor is a wound rotor type motor having speed control means. 9. An aircraft as in claim 7, wherein the stator of said motor is wound with alternative electromagnetic pole configurations to permit step-changes of speed. 10. An aircraft as in claim 2, wherein said cabin compressor includes inlet guide vanes and a turbine which is adapted to be used as an expansion cooling turbine. 11. An aircraft as in claim 7, wherein the stator of said motor carries two electromagnetic pole configurations to permit selectable speed changes. 12. An aircraft as in claim 11 including a logic assembly arranged to receive flight station/cockpit inputs and sensor data from said at least one engine, the cabin interior, and environmental control system ducts. 13. An aircraft as in any one of claims 2, 8, 9, 10, or 12 including a plurality of bypass valves, louvered shutters, and heat exchangers adapted to modulate the degree of heat transfer to and from the air mass flow into the aircraft cabin. 14. An aircraft as in any one of claims 8, 9 or 11 in which said motor speeds are changed by different magnetic pole configurations, said cabin compressor including inlet guide vanes, whereby said inlet guide vanes and motor speed changes are adapted to maintain a conditioned environment in the aircraft cabin, as the outside air density, atmospheric pressure change with operation of the airplane through its ground and flight envelope. 15. An aircraft as in claim 2, including an electromagnetic disconnect clutch for mechanically isolating said supercharger compressor. 16. An aircraft as in any one of claims 8, 9, or 11, including a logic assembly, said cabin compressor including inlet guide vanes, said logic assembly being adapted to adjust said inlet guide vanes and motor speed changes whereby the requirements of said environmental control system over the ground, climb, cruise, and descent flight conditions of said aircraft when the speed of said at least one engine varies over a speed range. 17. An aircraft as in claim 15, wherein said supercharger compressor is arranged to be brought on line by activation (opening) of said clutch via a logic assembly to maintain aircraft cabin pressurization when said at least one engine operates at lower speeds during idle descent let down of said aircraft, when said aircraft descends into higher density air and higher atmospheric pressures.