ENGINE BLEED AIR SYSTEM

An engine bleed air system (3) has one or more taps in the compressor section of an aircraft engine, for example a low pressure tap (19) and a high pressure tap (20). The low pressure tap (19) is fluidly connected to the compressor (21) of a turbo-compressor and the high pressure tap (20) is fluidly...

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Bibliographische Detailangaben
Hauptverfasser:	DREW, Diane G, ZYWIAK, Thomas M, BRUNO, Louis J, HIPSKY, Harold W, HUGHES, Daniel L, DEFRANCESCO, Gregory L
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	An engine bleed air system (3) has one or more taps in the compressor section of an aircraft engine, for example a low pressure tap (19) and a high pressure tap (20). The low pressure tap (19) is fluidly connected to the compressor (21) of a turbo-compressor and the high pressure tap (20) is fluidly connected to the turbine (22) of the turbo-compressor. A bypass line (30) connects the high pressure air to the outlet (32) of the compressor (21), with a heat exchanger (31) used to remove excess heat from the bypass line (30). An additional heat exchanger (37) is used to remove any excess heat from the compressed air, dumping the heat to a fan stream (33) or to the expanded air exiting the turbine (22). The system is controlled to minimize the amount of high pressure air extracted from the engine.