TY - JOUR
T1 - Mild Hybridization of Turboprop Engine With High-Power-Density Integrated Electric Drives
AU - Chen, Yuzheng
AU - Yang, Tao
AU - Khowja, Muhammad Raza
AU - Rocca, Antonino La
AU - Nasir, Usman
AU - Chowdhury, Shajjad
AU - Evans, Dean
AU - Kember, Dafydd
AU - Klonowski, Thomas
AU - Arnaud, Yohan
AU - Apostin, Lucie
AU - Liger, Thierry
AU - Cossart, Gregory
AU - Vakil, Gaurang
AU - Gerada, Chris
AU - Bozhko, Serhiy
AU - Detry, Sebastien
AU - Diette, Christophe
AU - Wheeler, Patrick
N1 - Publisher Copyright:
© 2015 IEEE.
PY - 2022/12/1
Y1 - 2022/12/1
N2 - This article shares with the aerospace community a case study of turboprop mild hybridization using a recently developed integrated drive system in the University of Nottingham, U.K., within the ACHIEVE project under EU H2020 CleanSky 2 program (project No. 737814). The developed drive system enables the green taxiing of a turboprop aircraft while on the ground with its engine OFF and as an electrical generator when the turboprop is in the air. The entire system is designed to be able to integrate within the power auxiliary gearbox (PAGB) of a turboprop aircraft. Some of the key features of the developed system include a high-speed permanent magnet machine (up to 14200 rpm) with a dual-three-phase design, silicon carbide (SiC)-based high power density (11.8 kW/L for the power converter, and 35.3 kW/L and 7.2 kW/kg for the machine active parts), integrated cooling design for high-temperature operation (>130 °C ambient temperature), fault tolerance consideration with dual-channel operation capabilities, and sensorless control for entire operational conditions. This article is giving an overview of the design process of the electrical machine, power converters, and the cooling of the entire drive. The numerical analysis [finite element method (FEM) and computational fluid dynamics (CFD)] and some experimental results are presented to demonstrate the effectiveness and the desired performance of the developed integrated drive system.
AB - This article shares with the aerospace community a case study of turboprop mild hybridization using a recently developed integrated drive system in the University of Nottingham, U.K., within the ACHIEVE project under EU H2020 CleanSky 2 program (project No. 737814). The developed drive system enables the green taxiing of a turboprop aircraft while on the ground with its engine OFF and as an electrical generator when the turboprop is in the air. The entire system is designed to be able to integrate within the power auxiliary gearbox (PAGB) of a turboprop aircraft. Some of the key features of the developed system include a high-speed permanent magnet machine (up to 14200 rpm) with a dual-three-phase design, silicon carbide (SiC)-based high power density (11.8 kW/L for the power converter, and 35.3 kW/L and 7.2 kW/kg for the machine active parts), integrated cooling design for high-temperature operation (>130 °C ambient temperature), fault tolerance consideration with dual-channel operation capabilities, and sensorless control for entire operational conditions. This article is giving an overview of the design process of the electrical machine, power converters, and the cooling of the entire drive. The numerical analysis [finite element method (FEM) and computational fluid dynamics (CFD)] and some experimental results are presented to demonstrate the effectiveness and the desired performance of the developed integrated drive system.
KW - Dual-three-phase machine
KW - mild-hybridization
KW - permanent magnet machine
KW - sensorless control
KW - silicon carbide (SiC) power conversion
KW - turboprop aircraft
UR - http://www.scopus.com/inward/record.url?scp=85126514529&partnerID=8YFLogxK
U2 - 10.1109/TTE.2022.3160153
DO - 10.1109/TTE.2022.3160153
M3 - Article
AN - SCOPUS:85126514529
SN - 2332-7782
VL - 8
SP - 4148
EP - 4162
JO - IEEE Transactions on Transportation Electrification
JF - IEEE Transactions on Transportation Electrification
IS - 4
ER -
