Conference Paper Intercooled and Recuperated Jet Engine Using Airfoil Heat Exchangers

伊藤, 優  ,  ITO, Yutaka  ,  猪倉, 直也  ,  Inokura, Naoya  ,  長崎, 孝夫  ,  NAGASAKI, TAKAO

Aviation engines are strongly de-sired to reduce CO2, carbon dioxide, emission in the worldwide trend of CO2 reduction. Gas turbine engines are bound to remain as aviation en-gines by 2040 at least because of its high power density and no alter-native engine. Then, the aviation gas turbines definitely have to en-hance their efficiency and to reduce fuel consumption. One of the likely solutions is an ICR, intercooled and recuperated, jet engine. Some re-searchers have confirmed that the SFC, specific fuel consumption per thrust, certainly decreases by em-ploying an intercooler and a recu-perator; however, the fuel burnt, fuel consumption per flight, rises because of weight increase. There-fore, to decrease an ICR engine weight, the authors proposed a new concept of an ICR jet engine using existing airfoils, such as compres-sor stators and guide vanes, as heat exchangers. Their outer shapes are airfoils for working air in a gas turbine, and their inner shapes are circular for heat transport refrig-erant. Some airfoil heat exchangers are installed in a hot section (a compressor or a core nozzle), and the other heat exchangers are in-stalled in a cold section (a bypass duct or a combustor inlet). The re-frigerant transports heat between a pair of the heat exchangers. In this concept, the intercooler and recu-perator require no additional space except connecting tubes for the re-frigerant between the heat exchang-ers. Furthermore, an air flow path can remain at almost the same posi-tion as that in a baseline engine. To evaluate feasibility of this con-cept, the authors have experimental-ly investigated heat transfer per-formance of the airfoil heat ex-changers. In the previous studies, the authors revealed heat transfer rates for air, heat transfer rates for refrigerant, and thermal re-sistance of the airfoil heat ex-changer. In this paper, using this information, a new ICR jet engine will be designed, and its perfor-mance, weight, and feasibility will be theoretically evaluated.

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