Investigation about Partial Turboelectric Propulsion System using Airframe Integrated Conceptual Design

被引：0

作者：

Yamada S. ^{[1
]}

Himeno T. ^{[1
]}

Watanabe T. ^{[1
]}

机构：

[1] Department of Aeronautics and Astronautics, The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo

来源：

International Journal of Gas Turbine, Propulsion and Power Systems | 2024年 / 15卷 / 02期

关键词：

Conceptual design;

D O I：

10.38036/jgpp.15.2_68

中图分类号：

学科分类号：

摘要：

Despite the COVID-19 pandemic, the demand of global aviation is expected to increase in the long run. At the same time, however, there is an urgent need to reduce the emissions of carbon dioxide. Numerous researchers and companies are proposing advanced technologies globally. In our laboratory, research about all turboelectric has been conducted but it revealed a stringent demand for electrical components. Therefore, the objective of this research was to advance this research and find the feasible solution. The research about Partial Turboelectric (PTeDP) was conducted. By operating with less peak power during takeoff, the weight of electrical components such as motors and generators, which are proportional to the peak power, was reduced. PTeDP turned out to have a potential to reduce 1% to 2% Mission Fuel Burn compared to Turbofan. Copyright ©2024 Soichiro Yamada, Takehiro himeno and Toshinori Watanabe.

引用

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页码：68 / 75

页数：7

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