HEAT EXCHANGER FOR AIRCRAFT ENGINE

A heat exchanger (100) for an aircraft engine includes a core (1) and radiating fins (2). The radiating fins are configured such that a ratio y/Y of a height y from a surface (10) of the core to a formation position of a connecting portion (23) to a total height Y of each of the radiating fins (2) f...

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Bibliographische Detailangaben
Hauptverfasser:	NAGAMITSU, Sachio, UEDA, Tatsuya
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 LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A heat exchanger (100) for an aircraft engine includes a core (1) and radiating fins (2). The radiating fins are configured such that a ratio y/Y of a height y from a surface (10) of the core to a formation position of a connecting portion (23) to a total height Y of each of the radiating fins (2) from the surface of the core satisfies a relationship of 0.34 < y/Y < 0.64.