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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Bibliographic Details
Main Authors DREW, Diane G, ZYWIAK, Thomas M, BRUNO, Louis J, HIPSKY, Harold W, HUGHES, Daniel L, DEFRANCESCO, Gregory L
Format Patent
LanguageEnglish
French
German
Published 17.07.2019
Subjects
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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Summary: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.
Bibliography:Application Number: EP20150187401