Aircraft pneumatic system

Patent metadata

Field	Value
Publication number	US-10450074-B2
Application number	US-201615205648-A
Country	US
Kind code	B2
Filing date	Jul 8, 2016
Priority date	Aug 7, 2015
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

An aircraft pneumatic system includes a main gas turbine engine including a main compressor, a recuperated auxiliary gas turbine engine including a core compressor having an inlet in fluid communication with a main compressor bleed of the main gas turbine engine and an environmental control system inlet in fluid communication with the main compressor bleed of the main gas turbine engine. The environmental control system includes a compressor driveable by power provided by the auxiliary gas turbine engine.

First claim

The invention claimed is:

1. An aircraft pneumatic system comprising:
a main gas turbine engine comprising a main compressor;
a recuperated auxiliary gas turbine engine comprising a core compressor, a combustor, and a recuperator, the core compressor including an inlet in fluid communication with a main compressor bleed of the main gas turbine engine, and the recuperator including a heat exchanger that is configured to recycle waste heat from an exhaust of the recuperated auxiliary gas turbine engine to an auxiliary gas turbine engine flow prior to the combustor; and
an environmental control system inlet in fluid communication with the main compressor bleed of the main gas turbine engine, the environmental control system inlet comprising a compressor drivable by power provided by the recuperated auxiliary gas turbine engine.

2. The system in accordance with claim 1 , wherein the inlet of the core compressor is in direct fluid communication with the main compressor bleed of the main gas turbine engine.

3. The system in accordance with claim 1 , wherein the inlet of the core compressor is in fluid communication with the main compressor bleed of the main gas turbine engine via a cabin air exhaust.

4. The system according to claim 1 , wherein the recuperated auxiliary gas turbine engine comprises a variable area turbine.

5. The system according to claim 1 , wherein the inlet of the core compressor is in fluid communication with one or more of a lower pressure main compressor customer bleed port, a higher pressure main compressor customer bleed port, a fan outlet of the main gas turbine engine, and a compressor handling bleed port.

6. The system according to claim 1 , further comprising a valve moveable between a first position, in which at least one of the environmental control system inlet and the inlet of the core compressor is in fluid communication with a fan outlet of the main gas turbine engine, and a second position in which at least one of the environmental control system inlet and the inlet of the core compressor is in fluid communication with a compressor bleed of the main compressor.

7. The system according to claim 1 , wherein the recuperated auxiliary gas turbine engine comprises a load driven by a turbine of the recuperated auxiliary gas turbine engine, the load comprising at least one of an electrical generator, a load compressor, a main gas turbine engine fluid pump, a main gas turbine engine shaft, and an air cycle machine compressor.

8. The system according to claim 7 , wherein the load compressor is configured to provide air to an inlet of the air cycle machine compressor.

9. The system according to claim 8 , wherein the system comprises a selectable bypass arrangement configured to provide air to the air cycle machine compressor directly from the main gas turbine engine compressor when operated in a bypass mode, and from the load compressor when in a non-bypass mode.

10. The system according to claim 7 , wherein the electrical generator is electrically connectable to an electric motor and the air cycle machine compressor is drivable by the electric motor.

11. The system according to claim 10 , wherein the air cycle machine comprises a first compressor driven by the electric motor, and a second compressor driven by the air cycle machine turbine.

12. The system according to claim 1 , wherein the environmental control system comprises an air cycle machine comprising, in fluid flow sequence, a compressor, a heat exchanger and a turbine, the compressor being drivable by the turbine.

13. The system according to claim 1 , wherein the recuperated auxiliary gas turbine engine is located either within a main gas turbine engine nacelle or within an aircraft fuselage.

14. The system according to claim 13 , wherein the recuperated auxiliary gas turbine engine comprises a propelling exhaust nozzle, which is located within the main gas turbine engine nacelle.

15. An aircraft pneumatic system comprising:
a main gas turbine engine comprising a main compressor;
a recuperated auxiliary gas turbine engine comprising a core compressor, a combustor, and a recuperator, the core compressor including an inlet in fluid communication with a main compressor bleed of the main gas turbine engine, and the recuperator including a heat exchanger that is configured to recycle waste heat from an exhaust of the recuperated auxiliary gas turbine engine to an auxiliary gas turbine engine flow prior to the combustor;
an environmental control system inlet in fluid communication with the main compressor bleed of the main gas turbine engine, the environmental control system inlet comprising a compressor drivable by power provided by the recuperated auxiliary gas turbine engine; and
a pre-cooler that provides pre-cooled air to be combined with an air flow from the recuperated auxiliary gas turbine engine.

16. An aircraft pneumatic system comprising:
a main gas turbine engine comprising a main compressor;
a recuperated auxiliary gas turbine engine comprising a core compressor, a recuperator, and a turbine, the core compressor including an inlet in fluid communication with a main compressor bleed of the main gas turbine engine, the recuperator including a heat exchanger having a first recuperator flow passage and a second recuperator flow passage, the recuperator being arranged such that fluid flows in series into the core compressor, through the recuperator first fluid flow passage, through a combustor, through the turbine, through the recuperator second fluid flow passage, and out an exhaust, such that exhaust heat downstream of the turbine is transferred to combustor inlet air; and
an environmental control system inlet in fluid communication with the main compressor bleed of the main gas turbine engine, the environmental control system inlet comprising a compressor drivable by power provided by the recuperated auxiliary gas turbine engine.

Assignees

• Rolls Royce Plc

Inventors

• Stieger Rory D
• Popovic Ivan

Classifications

• B64D2013/064

  comprising more than one system, e.g. dual systems · CPC title

• B64D2013/0618

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

• F05D2220/323

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

• B64D2013/0611

  combined with auxiliary power units (APU's) · CPC title

• F02C7/08

  Heating air supply before combustion, e.g. by exhaust gases · CPC title