Challenges and Opportunities of Very Light High-Performance Electric Drives for Aviation

Henke, Markus; Narjes, Gerrit; Hoffmann, J.; Wohlers, Constantin; Urbanek, Stefan; Heister, Christian; Steinbrink, J.; Canders, W.‐R.; Ponick, Bernd

doi:10.3390/en11020344

Cited by 62 publications

(44 citation statements)

References 29 publications

(37 reference statements)

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“…When designing a low weight machine, flux density and current density have to be balanced properly [9]. With a conventional non-superconducting design, a flux density in the air gap of 1.0 to 1.2 T may be achieved while the current density is limited by the copper losses.…”

Section: Electromagnetic Aspectsmentioning

confidence: 99%

Cooling Technologies for High Power Density Electrical Machines for Aviation Applications

2019

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This paper is aimed at giving an overview of possible cooling technologies for electrical machines and their assessment for aviation applications, e.g., fan or propeller drives. The most important demand for aircraft is the minimization of the drive system weight comprising electrical machine, power electronics, and the cooling system. The potential of aluminum winding an overview about several cooling technologies with the Rankine or Brayton cycle or utilizing the phase change of the cooling fluid is given. As an alternative approach, the cooling structure inside the machine is studied. A very interesting potential was discovered with direct slot cooling (DSC) removing the heat where it is produced and, thus, simplifying the cooling system effort and its weight. Since it is one of the most promising approaches, this cooling method is studied in depth. Furthermore, it can also be combined with one of the cooling technologies discussed above.In the overview paper [6], focus is set on the most recent progress in thermal management of electric motors for aviation. Besides air cooling, oil bath cooling, water jacket cooling, heat pipe cooling, intra winding cooling channels with a thermal conductive polymer [7], and direct winding cooling with tube-like conductors are cited. In this case, the problem of large pressure drops in the cooling ducts of six bars or more occurs. As experimental results, current densities of 24.7 A/mm 2 and transient current density of more than 40 A/mm 2 with class F insulation were achieved. With class H insulation even higher, values up to 58 A/mm 2 could be possible. By using conductors with integrated cooling channels, current densities possibly reaching 130 A/mm 2 were anticipated. However, the losses increase with the square of the current density and are linear with the volume of the winding even though the temperature is within the limits of the insulation system. The extremely high copper losses will increase weight and size of the cooling system and the reduced efficiency also requires an increase of the on-board power supply (generators and prime movers, fuel tank or energy storages, wiring, switchgear).The weight advantages of such machines can be quickly overcompensated by the weight of the cooling system and the increased power supply. Therefore, an accurately balanced design of the drive system is necessary. A proposal for the improvement of this approach is given in Section 5.A reduction of the winding temperature level by lowering the coolant temperature below standard ambient temperature promises a reduction of the copper losses in the electrical machine and a longer lifetime of the insulation. The higher effort for such cooling systems may be compensated by the higher efficiency of the drive. Due to the usually high temperature drop between winding and cooling fluid, this requires low ambient temperatures-as given in high cruising altitudes-or the use of refrigerant cooling systems, which allow coolant temperatures below ambient temperatures. In a literature study, no pap...

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Section: Electromagnetic Aspectsmentioning

confidence: 99%

Cooling Technologies for High Power Density Electrical Machines for Aviation Applications

2019

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“…This paper addresses the design of electrical machine which is directly attached onto a low-pressure spool (LPS) of a turbofan engine. The design initialization is carried out in the first section where the anticipated perspectives and objectives for MEE [1]- [3] are faced to the recognized challenges and opportunities [4]- [7]. The aim is exploring several design aspects and specifying four generator topologies for further study.…”

Section: 3384/ecp19162009mentioning

confidence: 99%

“…The evolution of the electric generation and power system perspective in context of MEA and MEE can be shortly summarized based on a few publications where the system development challenges [4] and some of the achievements [5] are reviewed. An extensive review of an electrical generator development is given in [6] and the generator development perspectives are collected in [7]. As the EM operates not only in generating operation but also motoring when starting up the engine, the engine architecture development gives both opportunities and challenges to electrical machine engineering to contribute to system efficiency, functionality and reliability.…”

Section: Jet-engine Generator Arrangementmentioning

confidence: 99%

Aerospace Electric Generator Specification and Selection - Opportunities and Challenges

Reinap¹

2019

Proceedings of the 10th Aerospace Technology Congress, October 8-9, 2019, Stockholm, Sweden

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The goal of this work is to specify and investigate suitability of a number of selected permanent magnet synchronous machine (PMSM) topologies to be mounted directly on a low pressure shaft (LPS) of a geared turbofan engine. The starting point of the work is to explore the status of electrical machines for more electric engine in order to study different design aspects when identifying and defining the designs. Even though the high flexibility and power density is anticipated from the system electrification the reliability is one of the most important aspects for the machine topology development and faultlessness can compromise desired performance. Large inner diameter of LPS and wide speed range are challenging the selection and specification of PMSM. The design initialisation is carried out by looking for more fault tolerant arrangements between machine windings and power converter topologies and appropriate rotor layouts that can provide excitation and constructional stability. Design space exploration is carried out on surface mounted Halbach array PMSM with distributed winding in the stator as one of the machine types that is best suited for high power density and high-speed application. Machine design aspects on modular design for faultlessness and cooling integration for enhanced thermal management and higher power density are the arguments behind the sensitivity study carried out on interior permanent magnet synchronous machine with nonoverlapping concentrated winding. Six different magnetic core materials are compared to demonstrate that thin FeSi electromagnetic steel grades improve efficiency and FeCo materials mainly torque density but the machine may remain unsatisfactory in power and efficiency.

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“…By maximizing the tractive force between the wheels and rail, a traction controller prevents the wheel from slipping [2][3]. The induction motors have been widely applied as the traction motor because of the low maintenance, low cost [4]. Advances in power electronics and microprocessor technology make it feasible to use the induction motors in place of DC motor and synchronous motors in a wide range of servo applications.…”

Section: Introductionmentioning

confidence: 99%

Black-box Identification and Validation of an Induction Motor in an Experimental Application

Fathabadi¹,

Molavi²

2019

EJEE

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This article presents a simple approach to identify an induction motor model which is used in a traction control system for the purpose of slip prevention. In this study, an identified model has been extracted by real and identified parameters of the induction motor in the MATLAB, Simulink; as the purpose of this study is to identify a linear model for the induction motor, the speed control loops have been opened, therefore d-q voltages have been designed as the exiting inputs. After several considerations and examination, ARMAX model has been selected as a mathematical model in the identification process, then the open loop identified model has been replaced in the closed-loop structure, and by using the real data measurements, obtained from the closed-loop system in the Advanced Motion Control Laboratory, the open loop extracted model is verified.

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Challenges and Opportunities of Very Light High-Performance Electric Drives for Aviation

Cited by 62 publications

References 29 publications

Cooling Technologies for High Power Density Electrical Machines for Aviation Applications

Cooling Technologies for High Power Density Electrical Machines for Aviation Applications

Aerospace Electric Generator Specification and Selection - Opportunities and Challenges

Black-box Identification and Validation of an Induction Motor in an Experimental Application

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