Aircraft pneumatic system

Patent metadata

Field	Value
Publication number	US-2017106985-A1
Application number	US-201615205648-A
Country	US
Kind code	A1
Filing date	Jul 8, 2016
Priority date	Aug 7, 2015
Publication date	Apr 20, 2017
Grant date	—

Abstract

An aircraft pneumatic system comprises a main gas turbine engine ( 10 ) comprising a main compressor ( 14, 16 ), a recuperated auxiliary gas turbine engine ( 40 ) comprising a core compressor ( 42 ) having an inlet in fluid communication with a main compressor bleed ( 32 ) of the main gas turbine engine( 10 ) and an environmental control system inlet in fluid communication with the main compressor bleed ( 32 ) of the main gas turbine engine ( 10 ). The environmental control system comprises a compressor ( 68 ) driveable by power provided by the auxiliary gas turbine engine ( 40 ).

First claim

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 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 and comprising a compressor driveable by power provided by the auxiliary gas turbine engine.

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

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

4 . A system according to claim 1 , wherein the auxiliary gas turbine engine may comprise a variable area turbine.

5 . A system according to claim 1 , wherein the core compressor inlet of the auxiliary gas turbine engine 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 . A system according to claim 1 , wherein the system comprises a valve selectable between a first position, in which at least one of the environmental control system inlet and the auxiliary gas turbine engine core compressor inlet is in fluid communication with the fan outlet of the gas turbine engine, and a second position in which at least one of the environmental control system inlet and the auxiliary gas turbine engine core compressor inlet is in fluid communication with a compressor bleed of the gas turbine engine main compressor.

7 . A system according to claim 1 , wherein the auxiliary gas turbine engine comprises a load driven by a turbine of the auxiliary gas turbine engine 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 . A system according to claim 1 , wherein the environmental control system may comprise an air cycle machine comprising, in fluid flow sequence, a compressor, a heat exchanger and a turbine, the compressor being driveable by the turbine.

9 . A system according to claim 8 , wherein the auxiliary gas turbine load compressor is configured to provide air to an inlet of the air cycle machine compressor.

10 . A system according to claim 9 , wherein the system comprises a 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 auxiliary gas turbine load compressor when in a non-bypass mode.

11 . A system according to claim 7 , wherein the electrical generator is electrically connectable to an electric motor and the air cycle machine compressor is driveable by the electric motor.

12 . A system according to claim 11 , 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.

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

14 . A system according to claim 13 , wherein the auxiliary gas turbine engine comprised a propelling exhaust nozzle, which may be located within the main gas turbine engine nacelle.

Assignees

• Rolls Royce Plc

Inventors

• Stieger Rory D
• Popovic Ivan

Classifications

• B64D13/02

  the air being pressurised · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• B64D2013/0603

  Environmental Control Systems · CPC title

• F05D2220/50

  for auxiliary power units (APU's) · CPC title

• B64D13/06 Primary

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