Compressor temperature control system and method

1. A system for preventing overheating of a compressor in an aircraft environmental system, the system including a source of bleed air; a compressor configured to receive the bleed air from the source, compress the bleed air, thus elevating the air temperature, and release the air from a compressor outlet; a condenser and a water extractor arranged to accept air from the compressor and extract water, a turbine configured to receive the air from an outlet from the water extractor, and expand the air resulting in a decreased air temperature, the expanded air being released from a turbine outlet and then being introduced into a cabin of the aircraft; and a control valve positioned between the source of bleed air, the turbine outlet, and the cabin; the control valve being capable of varied levels of openness, and being positioned to divert bleed air from the source, bypass the compressor, and direct the bleed air into the cabin, wherein the improvement comprises:

a processor configured to modulate an extent of openness of the control valve to enable a portion of the bleed air to bypass the compressor based at least in part on a temperature reading taken in the system based on a plurality of air-temperature measurements taken from one or more of: (i) an outlet conduit of the water extractor; (ii) a compressor outlet conduit; or (iii) a conduit located between the turbine outlet and the cabin, thus the system maintaining a compressor operating temperature.

2. The system of claim 1 , wherein a first air temperature measurement is made using a sensor positioned at the water extractor outlet.

3. The system of claim 2 , wherein a second air temperature measurement is made using a sensor positioned at the compressor outlet.

4. The system of claim 3 , wherein a third air temperature measurement is made using a sensor positioned prior to the entrance into the cabin of the aircraft.

5. The system of claim 4 , wherein a turbine inlet temperature is measured by a sensor positioned at the turbine inlet.

6. The system of claim 1 , further comprising a second valve being positioned between the compressor outlet and the turbine inlet to allow compressed air to increase the temperature of the air entering the turbine.

7. The system of claim 1 wherein the control valve is a low limit control valve.

8. A system comprising:

a source of bleed air from an engine;

an air-conditioning system between the engine and an aircraft cabin, the air-conditioning system including:

a compressor configured to receive the bleed air from the source, compress the bleed air, thus elevating the air temperature, and release the air from a compressor outlet;

a turbine configured to receive the air from the compressor, and expand the air resulting in a decreased air temperature, the expanded air being released from a turbine outlet, and then being introduced into a cabin of the aircraft;

a flow-control valve positioned between the source of bleed air, the turbine outlet, and the cabin;

a plurality of sensors positioned in different locations in the air-conditioning system between the engine and cabin, the sensors being positioned to read temperatures reflective of a compressor temperature condition; and

a processor configured to receive readings from the plurality of sensors to continually and dynamically change the extent of openness of the flow-control valve to enable varying portions of the bleed air to bypass the compressor, the processor also configured to dynamically operate the flow-control valve such that compressor operating temperatures are maintained below a maximum to prevent overheating of the compressor.

9. The system of claim 8 wherein the flow-control valve is a low limit control valve.

10. The system of claim 8 wherein the processor is configured to modulate the extent of openness by dynamically compensating for each of a plurality of readings received from the plurality of sensors.

11. The system of claim 10 , wherein the plurality of sensors are located at: (i) an outlet conduit of the water extractor; (ii) a compressor outlet conduit; and (iii) a conduit located between the turbine outlet and the cabin.

12. The system of claim 10 wherein the processor is configured to modulate the extent of openness using all of the plurality of readings received from the plurality of sensors.

13. A system comprising:

a source of bleed air;

a compressor configured to receive the bleed air from the source, compress the bleed air, thus elevating the air temperature, and release the air from a compressor outlet;

a turbine configured to receive the air from the compressor, and expand the air resulting in a decreased air temperature, the expanded air being released from a turbine outlet, and then being introduced into a cabin of the aircraft;

a low-limit control valve positioned between the source of bleed air, the turbine outlet, and the cabin, the flow control valve enabling a bypass flow around the compressor and turbine and into the cabin;

a plurality of sensors positioned in different locations in said system, the sensors being positioned to read temperatures directly reflective of a compressor temperature condition; and

a control system configured to dynamically receive the temperature from the plurality of sensors to continually and dynamically compensate using the low-limit control valve for the compressor temperature condition by modulating the amount of bypass flow versus a remaining amount of bleed air flow.