Pressure optimized sourcing of cabin pressurization and component air cooling

Patent metadata

Field	Value
Publication number	US-10934007-B2
Application number	US-201816029084-A
Country	US
Kind code	B2
Filing date	Jul 6, 2018
Priority date	Jul 6, 2018
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

An environmental control system (ECS) for an aircraft includes at least one cooling turbine, and a turbine bypass valve disposed fluidly upstream of the at least one cooling turbine. The turbine bypass valve is configured to direct a first portion of an ECS output airflow to a first air load at a first pressure via a first outlet passage, and direct a second portion of the ECS output airflow across a cooling turbine of the at least one cooling turbine and to a second air load at a second pressure lower than the first pressure for cooling thereof.

First claim

What is claimed is:

1. An environmental control system (ECS) for an aircraft comprising:
at least one cooling turbine; and
a valve disposed fluidly upstream of a first air load, the valve configured to:
direct a first portion of an ECS output airflow from the valve to the first air load at a first pressure via a first outlet passage; and
direct a second portion of the ECS output airflow across a cooling turbine of the at least one cooling turbine via a turbine inlet passage and to a second air load at a second pressure lower than the first pressure for cooling thereof;

wherein the at least one cooling turbine includes a first cooling turbine and a second cooling turbine of the ECS, with the valve configured to:
direct the first portion of an ECS output airflow from the first cooling turbine to the first air load; and
direct the second portion of the ECS output airflow across the second cooling turbine and to the second air load;

wherein a compressor is arranged on a common shaft with the first cooling turbine; and
wherein the compressor is fluidly coupled to an outlet of a primary heat exchanger and an inlet of a secondary heat exchanger of the ECS.

2. The environmental control system of claim 1 , further comprising an outlet heat exchanger disposed fluidly downstream of the at least one cooling turbine.

3. The environmental control system of claim 2 , wherein the first portion of the ECS output airflow and the second portion of the ECS output airflow are directed through the outlet heat exchanger to cool the first portion of the ECS output airflow.

4. The environmental control system of claim 1 , further comprising a condensing heat exchanger disposed on a fluid pathway between the first cooling turbine and the second cooling turbine.

5. The environmental control system of claim 1 , wherein the first air load is an aircraft cabin.

6. An environmental control system (ECS), comprising:
a primary heat exchanger;
a secondary heat exchanger;
an air cycle machine including a compressor and two or more cooling turbines, the compressor fluidly coupled to an outlet of the primary heat exchanger and an inlet of the secondary heat exchanger, and an outlet of the secondary heat exchanger fluidly coupled to a first cooling turbine or the two or more cooling turbines; and
a valve disposed fluidly downstream of the first cooling turbine, the valve configured to:
direct a first portion of an ECS output airflow to a first air load at a first pressure via a first outlet passage; and
direct a second portion of the ECS output airflow across a second cooling turbine of the two or more cooling turbines and to a second air load at a second pressure less than the first pressure for cooling thereof.

7. The environmental control system of claim 6 , further comprising an outlet heat exchanger disposed fluidly downstream of the second cooling turbine.

8. The environmental control system of claim 7 , wherein the first portion of the ECS output airflow and the second portion of the ECS output airflow are directed through the outlet heat exchanger to cool the first portion of the ECS output airflow.

9. The environmental control system of claim 6 , wherein first cooling turbine and the second cooling turbine are connected by a fluid pathway.

10. The environmental control system of claim 9 , further comprising a condensing heat exchanger disposed on the fluid pathway between the first cooling turbine and the second cooling turbine.

11. The environmental control system of claim 6 , wherein the compressor, the first cooling turbine and the second cooling turbine are arranged on a common shaft.

12. The environmental control system of claim 6 , wherein the first air load is an aircraft cabin.

13. A method of operating an environmental control system (ECS) of an aircraft, comprising:
flowing a bleed airflow through a primary heat exchanger;
flowing the bleed airflow from the primary heat exchanger into a compressor of an air cycle machine;
flowing the bleed airflow from the compressor into a first cooling turbine of the air cycle machine to cool the bleed airflow;
outputting a first portion of the bleed airflow as a first portion of an ECS output airflow to a first air load at a first pressure via a valve and a first outlet passage by bypassing a second cooling turbine of the air cycle machine; and
flowing a second portion of the bleed airflow across the second cooling turbine, thereby expanding the second portion of the bleed airflow; and
outputting the second portion of the bleed airflow as a second portion of the ECS output airflow to a second air load at a second pressure less than the first pressure via a second outlet passage.

Assignees

• Hamilton Sundstrand Corp
• Hamilton Sunstrand Corp

Inventors

• Ho Tony
• Retersdorf Alan

Classifications

• Y02T50/50

  On board measures aiming to increase energy efficiency · CPC title

• B64D2013/0614

  with subsystems for cooling avionics · CPC title

• B64D13/08 Primary

  the air being heated or cooled · CPC title

• B64D13/04

  Automatic control of pressure · CPC title

• B64D2013/0618

  with arrangements for reducing or managing bleed air, using another air source, e.g. ram air · CPC title