Pnuematic system for an aircraft
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United States of America Patent
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Jan 30, 2018
Issued Date -
N/A
app pub date -
Oct 15, 2014
filing date -
Nov 6, 2013
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Abstract
A pneumatic system 131 for use with gas turbine engines 10 and aircraft 100. The pneumatic system 131 comprises a first engine core compressor bleed offtake in the form of an engine handling bleed offtake 140, and a second engine core compressor bleed offtake in the form of first and second cabin bleed offtake 132, 134, the handling bleed being configured to supply higher pressure air than the cabin offtakes 132, 134. The system 131 comprises a turbocompressor 144 comprising an air compressor 148 driven by a turbine 146. The handling bleed offtake 140 is in fluid communication with the turbocompressor air turbine 146 to thereby drive the air turbine 146, and the cabin bleed offtakes 132, 134 are in fluid communication with the turbocompressor air compressor 148 such that air from the offtakes 132, 134 is compressed by the turbocompressor air compressor 148.
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