Environmental control system utilizing shoestring cycle to maximize efficiency

1. An environmental control system of an aircraft that utilizes recirculation air, comprising:

an inlet configured to supply bleed air at a first energy from a source to the environmental control system,

wherein the environmental control system supplies the bleed air at a second energy to a chamber; and

an air cycle machine comprising a compressor and a turbine,

wherein the air cycle machine receives the recirculation air from the chamber,

wherein the recirculation air is bleed air at a third energy flowing from the chamber to the air cycle machine,

wherein, during a ground operation of the aircraft, the bleed air drives the air cycle machine and the compressor receives the recirculation air flowing from the chamber to the air cycle machine, and

wherein, during a flight operation of the aircraft, a first portion of the recirculation air drives the air cycle machine and the compressor receives a second portion of the recirculation air,

wherein the first portion of the recirculation air expands across the turbine to drive the air cycle machine,

wherein the second portion of the recirculation air received by the compressor is compressed based on the first portion of the recirculation expanding across the turbine to produce compressed recirculation air, and

wherein the environmental control system passes the compressed recirculation air back to the chamber,

wherein the environmental control system passes the first portion of the recirculation air to an outlet after the first portion of the recirculation air expands across the turbine,

wherein the environmental control system passes the compressed recirculation air from the compressor to a second heat exchanger, from the second heat exchanger to a second turbine of the air cycle machine, and from the second turbine back to the chamber.

2. The environmental control system of claim 1 ,

wherein the bleed air expands across the turbine to drive the air cycle machine,

wherein the recirculation air received by the compressor is compressed based on the bleed air expanding across the turbine to produce the compressed recirculation air.

3. The environmental control system of claim 1 ,

wherein the recirculation air drives the air cycle machine, and

wherein the compressor receives the bleed air.

4. The environmental control system of claim 3 ,

wherein the recirculation air expands across the turbine to drive the air cycle machine,

wherein the bleed air received by the compressor is compressed based on the recirculation air expanding across the turbine to produce compressed bleed air, and

wherein the environmental control system provides the compressed bleed air to the chamber.

5. The environmental control system of claim 4 ,

wherein the environmental control system passes the recirculation air to an outlet after the expanding of the recirculation air across the turbine.

6. The environmental control system of claim 1 , wherein the air cycle machine further comprises a dual spool cycle configuration that includes:

a turbine of a first spool configured to receive the bleed air; and

a compressor of a second spool configured to receive the recirculation air.

7. The environmental control system of claim 1 ,

wherein the bleed air is drawn from a low pressure location of the engine,

wherein the first energy is a first pressure,

wherein the second energy is a second pressure, and

wherein a value of the first pressure is the same or close to a value of the second pressure.

8. The environmental control system of claim 1 ,

wherein the chamber is a cabin of the aircraft.