Mixing ram and bleed air in a dual entry turbine system

Patent metadata

Field	Value
Publication number	US-11511867-B2
Application number	US-201715604481-A
Country	US
Kind code	B2
Filing date	May 24, 2017
Priority date	May 26, 2016
Publication date	Nov 29, 2022
Grant date	Nov 29, 2022

Abstract

An air cycle machine is provided. The air cycle machine can be included an environmental control system of an aircraft. The air cycle machine can include a turbine comprising a plurality of inlet gas flow paths, a compressor driven by the turbine from a shaft, and a fan driven by the turbine from the shaft.

First claim

What is claimed is:

1. An air cycle machine comprising:
a turbine comprising a first nozzle that receives a bleed air flow from an aircraft turbine engine and a second nozzle that receives a fresh air flow;
a shaft;
a compressor driven by the turbine via the shaft and that receives and compresses the fresh air flow;
a power turbine connected to the shaft and that receives cabin discharge air from an aircraft cabin after the discharge air has been heated in a heat exchanger by the fresh air flow after it leaves the compressor; and
a fan driven by the shaft,
wherein the bleed air flow enters the first nozzle of the turbine and the fresh air flow enters the second nozzle of the turbine after the fresh air flow leaves the compressor, wherein the fresh air flow is mixed with the bleed air flow in the turbine to create a mixed airflow that exits the turbine and enters the aircraft cabin.

2. The air cycle machine of claim 1 , wherein the turbine is located on a first end of the shaft.

3. The air cycle machine of claim 2 , wherein the fan is located on a second end of the shaft.

4. The air cycle machine of claim 3 , wherein the compressor is located on the shaft between the turbine and the fan.

5. The air cycle machine of claim 1 , wherein the power turbine is located between the fan and compressor.

6. The air cycle machine of claim 1 , wherein the power turbine is located between the turbine and the fan.

7. An air conditioning system comprising:
a first turbine comprising a first nozzle that receives a bleed air flow from an aircraft turbine engine and a second nozzle that receives a fresh air flow;
a shaft;
a compressor driven by the first turbine via the shaft and that receives and compresses the fresh air flow;
a fan turbine;
a power turbine connected to the shaft and that receives cabin discharge air from an aircraft cabin after the discharge air has been heated in a heat exchanger by the fresh air flow after it leaves the compressor; and
a fan driven by the fan turbine,
wherein the bleed air flow enters the first nozzle of the first turbine and fresh air flow enters the second nozzle of the first turbine after the fresh air flow leaves the compressor, wherein the fresh air flow is mixed with the bleed air flow in the first turbine to create a mixed airflow that exits the first turbine and enters the aircraft cabin.

8. The air conditioning system of claim 7 , wherein the first turbine is located on a first end of the shaft.

9. The air conditioning system of claim 8 , wherein the compressor is located on a second end of the shaft.

10. The air conditioning system of claim 8 , wherein the power turbine is located on a second end of the shaft.

11. The air condition system of claim 10 , wherein the compressor is located between the first turbine and the power turbine.

12. The air conditioning system of claim 7 , wherein the fan turbine and the fan are an integral rotor.

13. The air conditioning system of claim 7 , further comprising:
a second shaft coupling the fan and the fan turbine.

14. An air conditioning system, comprising:
a turbine comprising a first nozzle that receives a bleed air flow from an aircraft turbine engine and a second nozzle that receives a fresh air flow;
a shaft;
a compressor driven by the turbine via the shaft and that receives and compresses the fresh air flow;
a power turbine connected to the shaft and that receives cabin discharge air from an aircraft cabin after the discharge air has been heated in a heat exchanger by the fresh air flow after it leaves the compressor;
a motor; and
a fan driven by the motor,
wherein the bleed air flow enters the first nozzle of the turbine and the fresh air flow enters the second nozzle of the turbine after the fresh air flow leaves the compressor, wherein the fresh air flow is mixed with the bleed air flow in the turbine to create a mixed airflow that exits the turbine and enters the aircraft cabin.

15. The air conditioning system of claim 14 , wherein the turbine is located on a first end of the shaft.

16. The air conditioning system of claim 15 , wherein the compressor is located on a second end of the shaft.

17. The air conditioning system of claim 14 , wherein the power turbine is located on a first end of the shaft.

18. The air conditioning system of claim 14 wherein the power turbine is located on a second end of the shaft.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Bruno Louis J
• Hipsky Harold W

Classifications

• B64D13/02 Primary

  the air being pressurised · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• B64D2013/0688

  with means for recirculating cabin air · CPC title

• B64D13/06

  the air being conditioned (pressurising B64D13/02) · CPC title

• F04D25/045

  the pump wheel carrying the fluid driving means, e.g. turbine blades · CPC title