Air cycle machine pack system and method for improving low inlet pressure cooling performance

Patent metadata

Field	Value
Publication number	US-9656755-B2
Application number	US-201314105184-A
Country	US
Kind code	B2
Filing date	Dec 13, 2013
Priority date	Dec 13, 2013
Publication date	May 23, 2017
Grant date	May 23, 2017

Abstract

An air cycle machine (ACM) pack system for an aircraft with an improved low inlet pressure cooling performance is provided. The ACM pack system has an air cycle machine (ACM) with at least one compressor mechanically coupled to at least one turbine in series on an ACM shaft. The ACM pack system further has a pack heat exchanger coupled to and in fluid communication with the at least one compressor of the ACM. The ACM system further has a bypass air flow assembly coupled in a parallel operation path to the ACM and has a bypass air flow regulating element. The bypass air flow assembly transfers energy extracted by the bypass air flow assembly to the ACM to aid the ACM pack system in cooling performance at a low inlet pressure, resulting in an improved low inlet pressure cooling performance of the ACM pack system.

First claim

What is claimed is:

1. An air cycle machine (ACM) pack system for an aircraft, the system having an improved low inlet pressure cooling performance, the system comprising:
an air cycle machine (ACM) comprising at least one compressor mechanically coupled to at least one turbine in series on an ACM shaft;
a primary heat exchanger and a secondary heat exchanger coupled to and in fluid communication with the at least one compressor of the ACM, the at least one compressor receiving outlet air from the primary heat exchanger, and the at least one compressor discharging compressor outlet air to the secondary heat exchanger; and,
a bypass air flow assembly coupled in parallel to the ACM, the bypass air flow assembly having a bypass air flow regulating element, the bypass air flow assembly being coupled to the ACM via one of, a mechanical drive element, a parallel turbine valve assembly, or a turbo-compressor assembly,
wherein the bypass air flow assembly transfers energy extracted by the bypass air flow assembly to the ACM to aid the air cycle machine (ACM) pack system in cooling performance, the extracted energy transferred via one of, the mechanical drive element, the parallel turbine valve assembly, or the turbo-compressor assembly.

2. The system of claim 1 wherein the bypass air flow assembly comprises a parallel turbine mechanically coupled to a turbine shaft and the mechanical drive element connecting the turbine shaft to the ACM shaft to drive the at least one turbine and the parallel turbine in parallel.

3. The system of claim 2 wherein the mechanical drive element has a first end connected to the turbine shaft and a second end connected to the ACM shaft to drive the at least one turbine and the parallel turbine in parallel and to transfer mechanical energy from the bypass air flow assembly to the ACM.

4. The system of claim 3 wherein the mechanical drive element comprises a mechanical shaft or a geared shaft.

5. The system of claim 3 wherein the bypass air flow regulating element comprises a parallel turbine valve coupled to the parallel turbine.

6. The system of claim 1 wherein the bypass air flow assembly comprises the turbo-compressor assembly coupled to a regeneration heat exchanger and a check valve, all coupled to the ACM, and the flow regulating element comprises a parallel turbine valve coupled to the turbo-compressor assembly.

7. The system of claim 1 wherein the at least one turbine comprises a first turbine and a second turbine mechanically coupled in series on the ACM shaft.

8. The system of claim 7 wherein the bypass air flow regulating element comprises a parallel turbine valve coupled between the first turbine and the second turbine.

9. The system of claim 8 wherein the bypass air flow assembly comprises the parallel turbine valve assembly coupled to the ACM, the parallel turbine valve assembly comprising a compressor bypass valve, an isolation valve, a check valve, and the parallel turbine valve.

10. The system of claim 1 wherein the bypass air flow assembly is either a mechanical energy transfer bypass air flow assembly or a pneumatic energy transfer bypass air flow assembly.

11. An aircraft comprising:
one or more aircraft engines each having a bleed air system for generating bleed air;
a fuselage defining an interior volume having an aircraft cabin and a pack bay separate from the aircraft cabin; and,
an aircraft air conditioning system positioned in the pack bay and in fluid communication with the aircraft cabin, the aircraft air conditioning system having an air cycle machine (ACM) pack system comprising:
an air cycle machine (ACM) comprising at least one compressor mechanically coupled to at least one turbine in series on an ACM shaft;
a primary heat exchanger and a secondary heat exchanger coupled to and in fluid communication with the at least one compressor of the ACM, the at least one compressor receiving outlet air from the primary heat exchanger, and the at least one compressor discharging compressor outlet air to the secondary heat exchanger; and,
a bypass air flow assembly coupled in parallel to the ACM, the bypass air flow assembly having a parallel turbine valve, the bypass air flow assembly being coupled to the ACM via one of, a mechanical drive element, a parallel turbine valve assembly, or a turbo-compressor assembly,
wherein the bypass air flow assembly transfers energy extracted by the bypass air flow assembly to the ACM to aid the ACM pack system in cooling performance, the extracted energy transferred via one of, the mechanical drive element, the parallel turbine valve assembly, or the turbo-compressor assembly.

12. The aircraft of claim 11 wherein the mechanical drive element comprises a mechanical shaft or a geared shaft.

13. The aircraft of claim 12 wherein the bypass air flow assembly comprises a parallel turbine coupled to a turbine shaft and the mechanical drive element connecting the turbine shaft to the ACM shaft to drive the at least one turbine and the parallel turbine in parallel and to transfer mechanical energy from the bypass air flow assembly to the ACM.

14. The aircraft of claim 11 wherein the bypass air flow assembly comprises the turbo-compressor assembly coupled to a regeneration heat exchanger and a check valve, all coupled to the ACM, and the parallel turbine valve is coupled to the turbo-compressor assembly, the turbo-compressor assembly transferring pneumatic energy from the bypass air flow assembly to the ACM.

15. The aircraft of claim 11 wherein the at least one turbine comprises a first turbine and a second turbine mechanically coupled in series on the ACM shaft, and wherein the parallel turbine valve is coupled between the first turbine and the second turbine.

16. The aircraft of claim 15 wherein the bypass air flow assembly comprises the parallel turbine valve assembly coupled to the ACM, the parallel turbine valve assembly comprising a compressor bypass valve, an isolation valve, a check valve, and the parallel turbine valve, the parallel turbine valve assembly transferring mechanical energy from the bypass air flow assembly to the ACM.

17. A method for improving low inlet pressure cooling performance of an air cycle machine (ACM) pack system, the method comprising the steps of:
installing an air cycle machine (ACM) pack system in an aircraft air conditioning system of an aircraft, the ACM pack system comprising:
an air cycle machine (ACM) comprising at least one compressor mechanically coupled to at least one turbine in series on an ACM shaft;
a primary heat exchanger and a secondary heat exchanger coupled to and in fluid communication with the at least one compressor of the ACM, the at least one compressor receiving outlet air from the primary heat exchanger, and the at least one compressor discharging compressor outlet air to the secondary heat exchanger; and,
a bypass air flow assembly configured for coupling to the ACM and having a bypass air flow regulating element,

coupling the bypass air flow assembly and the ACM in parallel, the bypass air flow assembly being coupled to the ACM via one of, a mechanical drive element, a parallel turbine valve assembly, or a turbo-compressor assembly;
using the bypass air flow assembly to divert an amount of bleed air from a bleed air system of an aircraft engine of the aircraft to the bypass air flow assembly, the bleed air comprising a bypass air flow flowing across the bypass air flow assembly, and the bypass air flow assembly extracting energy from the bypass air flow to obtain extracted energy; and,
transferring the extracted energy from the

Assignees

• Boeing Co

Inventors

• Durbin Richard R
• Fiterman Charles J
• Sullivan Daniel J

Classifications

• Y02T50/50

  On board measures aiming to increase energy efficiency · CPC title

• B64D13/08 Primary

  the air being heated or cooled · CPC title

• B64D2013/0618

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

• Y02T50/56

  Cross-Sectional Technologies · mapped topic