Conference Paper Rough Weight Estimation for Intercooled and Recuperated Aviation Gas Turbine Using Airfoil Heat Exchangers

伊藤, 優  ,  ITO, Yu

Aviation engines are strongly desired to reduce CO2, carbon dioxide, emission in the worldwide trend of CO2 reduction. Gas turbine engines are bound to remain as aviation engines by 2040 at least because of its high power density and no alternative engine. Then, the aviation gas turbines definitely have to enhance their efficiency and to reduce fuel consumption. One of the likely solutions is an ICR, intercooled and recuperated, jet engine. Some researchers have confirmed that the SFC, specific fuel consumption per thrust, certainly decreased by employing an intercooler and a recuperator; however, the fuel burnt, fuel consumption per flight, rose because of weight increase. Therefore, to decrease an ICR engine weight, Ito proposed a new concept of an ICR jet engine using existing airfoils, such as compressor 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 HTM, heat transport medium. Some airfoil heat exchangers are installed in a hot section (a compressor or a core nozzle), and the other heat exchangers are installed in a cold section (a bypass duct or a combustor inlet). The HTM transports heat between a pair of the heat exchangers. In this concept, the intercooler and recuperator require no additional space except connecting tubes for the HTM between the heat exchangers. Furthermore, an airflow path can remain at almost the same position as that in a baseline engine. To evaluate feasibility of this concept, the authors have experimentally investigated heat transfer performance of the airfoil heat exchangers. In the previous studies, the authors revealed heat transfer rates on air-contact surfaces, heat transfer rates on HTM-contact surfaces, and thermal resistance of the airfoil heat exchanger. In this paper, using this information, a new ICR jet engine will be designed, and its performance, weight, and feasibility will be theoretically evaluated.

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