Presentation Information
[AP4-01-INV]Rotation Test of 2 MW Superconducting Motor
*Itaru Abe1, Ryo Fuchimoto1, Tomoyuki Takahashi1, Takeshi Kanasaki1, Keita Nakama1, Kei Koyanagi1, Maia Okayasu1, Tsutomu Shimonosono1, Toru Kuriyama1, Masahiko Takahashi1, Norikazu Takagi1, Masafumi Fujita1, Takaaki Hirose1, Yasuo Kabata1, Hiroshi Hatano1, Tadahiro Nakayama2, Keiko Okamoto2, Teppei Yano1, Mikio Kakiuchi1, Shinji Uemoto1, Hiroshi Mochikawa1, Hideyuki Nakamura1, Hitoshi Katayama1, Taizo Tosaka1, Fumitoshi Mizutani1, Kyohei Shibata1 (1. Toshiba Energy Systems & Solutions Corporation (Japan), 2. Toshiba Corporation (Japan))
Keywords:
superconducting motor,high-temperature superconducting (HTS),REBCO,conduction cooling
[Purpose]
The objective of this study is to systematically identify practical engineering challenges in the development of a 2 MW superconducting motor for aircraft electrification. The focus is not only on achieving high power density but also on addressing a broader range of technical considerations.
[Method]
A prototype 2 MW synchronous superconducting motor was designed and manufactured, featuring superconducting coils on the rotor and normal-conducting coils on the stator. The rotor includes a cryostat cooled by circulating gaseous helium. The field coil is a racetrack-type high-temperature superconducting (HTS) coil wound with REBCO tape, conductively cooled via the coil shaft and operated below 30 K. Voltage–current characteristics of the HTS coil were evaluated in liquid nitrogen at each stage of rotor assembly. After final assembly, rotational testing was conducted to assess cryogenic cooling performance, mechanical tolerance against centrifugal forces, and robustness against electromagnetic forces.
[Results]
The prototype motor was successfully developed with an outer diameter of approximately 500 mm and a total length of approximately 700 mm. Experimental evaluations confirmed the integrity of the HTS coils, the effectiveness of the cryogenic cooling system, and the mechanical robustness of the rotor under high-speed rotation and electromagnetic stress.
[Consideration]
Rotational testing demonstrated that the cooling system successfully maintained cryogenic temperatures, validating the effectiveness of the thermal management design. The rotor showed sufficient mechanical tolerance against centrifugal and electromagnetic forces, confirming the structural integrity of the design. These findings provide valuable insights into the technical challenges and solutions associated with applying superconducting technology to electric propulsion systems for aircraft.
[Conclusion]
The development and testing of the 2 MW superconducting motor prototype validated key design elements and operational stability. The results contribute to the advancement of superconducting motor technology and support its potential application in future electrified aircraft systems.
The objective of this study is to systematically identify practical engineering challenges in the development of a 2 MW superconducting motor for aircraft electrification. The focus is not only on achieving high power density but also on addressing a broader range of technical considerations.
[Method]
A prototype 2 MW synchronous superconducting motor was designed and manufactured, featuring superconducting coils on the rotor and normal-conducting coils on the stator. The rotor includes a cryostat cooled by circulating gaseous helium. The field coil is a racetrack-type high-temperature superconducting (HTS) coil wound with REBCO tape, conductively cooled via the coil shaft and operated below 30 K. Voltage–current characteristics of the HTS coil were evaluated in liquid nitrogen at each stage of rotor assembly. After final assembly, rotational testing was conducted to assess cryogenic cooling performance, mechanical tolerance against centrifugal forces, and robustness against electromagnetic forces.
[Results]
The prototype motor was successfully developed with an outer diameter of approximately 500 mm and a total length of approximately 700 mm. Experimental evaluations confirmed the integrity of the HTS coils, the effectiveness of the cryogenic cooling system, and the mechanical robustness of the rotor under high-speed rotation and electromagnetic stress.
[Consideration]
Rotational testing demonstrated that the cooling system successfully maintained cryogenic temperatures, validating the effectiveness of the thermal management design. The rotor showed sufficient mechanical tolerance against centrifugal and electromagnetic forces, confirming the structural integrity of the design. These findings provide valuable insights into the technical challenges and solutions associated with applying superconducting technology to electric propulsion systems for aircraft.
[Conclusion]
The development and testing of the 2 MW superconducting motor prototype validated key design elements and operational stability. The results contribute to the advancement of superconducting motor technology and support its potential application in future electrified aircraft systems.