AIRCRAFT ENGINE WITH TURBINE HEAT EXCHANGER BYPASS
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United States of America Patent
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Issued Date -
Dec 5, 2013
app pub date -
Mar 13, 2013
filing date -
Mar 16, 2012
priority date (Note) -
Abandoned
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Abstract
An aircraft engine, in particular a helicopter engine, having a one or multi-stage compressor system (V), a combustion chamber (BK) connected downstream therefrom, and a one- or multi-stage turbine system (HT, NT) connected downstream therefrom, a compressor heat exchanger system (WV), a turbine heat exchanger system (WT), and a bypass means for optionally guiding the working medium through or past at least one turbine heat exchanger (WT) of the turbine heat exchanger system.
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