A gas turbine engine includes a fan, a compressor section having at least two sequential compressors, a combustor section fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. The turbine section includes at least a first turbine, a second turbine and a third turbine. One of the first turbine, the second turbine and the third turbine is a fan-drive turbine. An environmental control system air supply includes at least a first compressor bleed and a second compressor bleed. Each of the first compressor bleed and the second compressor bleed are positioned upstream of a highest pressure compressor of the at least two compressors.
Compressor bleed air supply for an aircraft environmental control system
04.12.2018
Patent
Elektronische Ressource
Englisch
COMPRESSOR BLEED AIR SUPPLY FOR AN AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM
Europäisches Patentamt | 2016
|Simplified engine bleed supply with low pressure environmental control system for aircraft
Europäisches Patentamt | 2018
|Simplified engine bleed supply with low pressure environmental control system for aircraft
Europäisches Patentamt | 2020
|