System and method for heat recovery in a gas turbine engine

A system (10) includes an anti-icing heat recovery system (50), which includes a first heat exchanger (54), a second heat exchanger (58), and a variable speed fan (56). The first heat exchanger (54) is configured to receive a working fluid from an exhaust section (24) of a gas turbine engine (12) an...

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Main Authors Mendez, Jesus Ellios Almendarez, Watkins, Richard Michael, Baten, Robert Allen, Zhang, Jingmei, Jones, Douglas Alan, Contreras, Gerardo Plata, Velarde, Victor Gerardo Cabal
Format Patent
LanguageEnglish
French
German
Published 28.03.2018
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
ENGINE PLANTS IN GENERAL
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Summary:A system (10) includes an anti-icing heat recovery system (50), which includes a first heat exchanger (54), a second heat exchanger (58), and a variable speed fan (56). The first heat exchanger (54) is configured to receive a working fluid from an exhaust section (24) of a gas turbine engine (12) and to transfer heat from the working fluid to a cooled intermediate heat transfer medium to generate a heated intermediate heat transfer medium. The second heat exchanger (58) is configured to receive the heated intermediate heat transfer medium from the first heat exchanger (54) and to transfer heat from the heated intermediate heat transfer medium to air entering the gas turbine engine (12). The variable speed fan (56) is configured to urge the working fluid from the exhaust section (24) of the gas turbine engine (12) through the first heat exchanger (54).
Bibliography:Application Number: EP20130167160