MICROCHANNEL HEAT EXCHANGERS FOR GAS TURBINE INTERCOOLING AND CONDENSING AS WELL AS CORRESPONDING METHOD

A gas turbine engine (100) heat exchange system (200) includes a first microchannel heat exchanger (MCHX) (108, 118, 300) configured to transfer heat between a first air stream (114, 122, 208, 210, 322) and a working fluid (330). The first MCHX (108, 118, 300) includes a plurality of air-passage lay...

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Bibliographische Detailangaben
Hauptverfasser:	Dejulio, Emil R, Loebig, James C
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OFGENERAL APPLICATION GAS-TURBINE PLANTS HEAT EXCHANGE IN GENERAL HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS,IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine (100) heat exchange system (200) includes a first microchannel heat exchanger (MCHX) (108, 118, 300) configured to transfer heat between a first air stream (114, 122, 208, 210, 322) and a working fluid (330). The first MCHX (108, 118, 300) includes a plurality of air-passage layers (328, 700). Each of the air-passage layers (328, 700) includes a plurality of etched air-passage microchannels (320, 702) that are configured to allow passage of the first air stream (114, 208, 322) therethrough. The first MCHX (108, 118, 300) may include a plurality of working fluid layers (324, 500). Each working fluid layer (324, 500) includes a plurality of etched working fluid microchannels (402) that are configured to allow passage of the working fluid (330) therethrough.