Direct Drive Electric Motor for STARC-ABL Tail-Cone Propulsor

Yoon, Andy; Arastu, Faraz; Lohan, Danny; Xiao, Jianqiao; Haran, Kiruba S.

doi:10.2514/6.2019-4516

Cited by 7 publications

(4 citation statements)

References 1 publication

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“…Sadey et al [57] proposed a model for power system preliminary sizing, and Yoon et al [58] defined several motor concepts for the aft-fuselage fan. Kratz and Thomas [59] stated that neglecting system dynamics and control strategy could lead to an over-designed propulsion system, with a 3% excess in the high-pressure compressors stall margin.…”

Section: Accepted Manuscript N O T C O P Y E D I T E Dmentioning

confidence: 99%

Boundary Layer Ingestion Propulsion: A Review on Numerical Modeling

Menegozzo

Benini

2020

Journal of Engineering for Gas Turbines and Power

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The present paper focuses on the numerical modelling approaches adopted in Boundary Layer Ingestion (BLI) studies. Three driving aircraft concepts have been identified, namely Propulsive Fuselage Concept, Rear Engines Concept and Distributed Fans Concept. The affiliation to relevant research projects has been considered. Specifically, EU DisPURSAL, EU CENTRELINE, NASA STARC-ABL, NASA D8, ONERA NOVA, NASA N3-X and ONERA DRAGON have been examined, as well as other works. The methodologies adopted by the reviewed analyses have been investigated and summarized for each concept, in order to assess the main trends of BLI modelling strategies.

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Section: Accepted Manuscript N O T C O P Y E D I T E Dmentioning

confidence: 99%

Boundary Layer Ingestion Propulsion: A Review on Numerical Modeling

Menegozzo

Benini

2020

Journal of Engineering for Gas Turbines and Power

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“…For internal rotor machines this diameter is referred to as the rotor diameter [17], [28], while for external rotor machines it is referred to as the stator outer diameter [29]. In this research, external rotor machines are considered, since the design principles presented are inferred from earlier presented machines proposed for aerospace applications [31], [32], which has same topology.…”

Section: B Electrical Machines Sizingmentioning

confidence: 99%

“…For such external rotor topology, three main mechanical challenges are identified; the rotor radial expansion, installation feasibility and load transmission. In [31], the structural analysis and installation feasibility for such motor topology was performed. It was proposed to be installed by fastening the base structure to the aircraft, for a reliable transmission of the thrust to the aircraft.…”

Section: B Electrical Machines Sizingmentioning

confidence: 99%

Optimal Voltage and Current Selection for Turboelectric Aircraft Propulsion Networks

Ibrahim

Sampath

Nalianda

2020

IEEE Trans. Transp. Electrific.

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Deploying electrical systems for aircraft propulsion have been identified as a potential solution, for reducing the environmental impact of the increasing air transport usage. However, the implementation of this system needs to be done at a suitable voltage and current combination. The aim of this work is to propose a clear procedure, for deriving a suitable voltage and current for an electrical propulsion system, based on the aircraft dimensions and thrust requirement. The approach presented, considers feasibility and minimum mass as boundary and target respectively. The results show that the fan configuration and thrust requirement directly influence the choice of optimal voltage and current. This is due to the varied impact on device sizes and overall propulsion system performance. Major drivers of the selected voltage and current are the loading coefficient, speed and torque requirement of the fan. The knowledge of these is a requirement to arrive at an optimal voltage for the propulsion system.

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“…Superconducting motors will be required for large scale electric aircraft. Development targets currently call for 2 MW-3 MW motors with power to mass ratios of more than 20 kW/kg [39,100,106,125,126].…”

Section: Propulsion Motormentioning

confidence: 99%

Superconducting Electric Aircraft Powertrain Mass Reduction by Wireless Rotor Energisation

Hamilton¹

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The European Union have set an ambitious goal of reducing aviation emissions by 25% by 2050, as commercial aviation is currently responsible for 2% of carbon dioxide equivalent emissions globally. Electric vehicle propulsion is an effective method of reducing emissions and operating costs that has been applied in marine, rail, and road transportation. Electric propulsion of large commercial airliners is not possible with conventional electric motors due to the large mass of the required steel components. Superconducting motors can be constructed without steel, and are the only method of achieving sufficiently compact and lightweight motors to enable large scale electric aircraft propulsion. However, the superconducting components of these motors must be cryogenically cooled during operation, which both adds mass to the powertrain and reduces efficiency. The goal of the work presented in this thesis is to increase the effective power to mass ratio of superconducting motors by reducing the required cryogenic cooling power. A significant contributor to cryogenic loading is shown to be the rotor current supply leads. These leads supply constant electric current to the superconducting field coils, but also provide a low thermal resistance pathway for heat to enter the cryogenic envelope from the surrounding environment. Replacing these leads with wireless field coil energisation eliminates the thermal pathway, and removes electrically resistive components from the superconducting field coil circuit. As variations in efficiency and mass of any aircraft component effect overall efficiency and power per unit mass, component level digital powertrain models are built and combined with aircraft model to simulate domestic flights within New Zealand. Three types of hybrid aircraft powertrains are simulated, each with cryogenically cooled superconducting motors. Conventional fuel is simulated in the first and second models, with cooling supplied by mechanical cryocoolers in the first model, and by liquid cryogen in the second. The third model simulates a hydrogen fuelled powertrain where the liquid hydrogen fuel is also used as liquid cryogen for motor cooling. Using these models, wireless field coil energisation is shown to reduce powertrain mass and required power, even where this energisation method is as little as 5% efficient. Although the difference due to cryogenic load is only slight where cooling is provided by liquid cryogen, wireless field coil energisation both reduces powertrain mass and increases efficiency. This results from replacement of the field coil current supplies with lightweight wireless supplies, and mass reduction through removal of the copper supply leads. Practical characterisation of a demonstration wireless superconducting supply shows efficiencies of up to 9% are possible with existing designs, and suggests a conduction cooled variant may achieve up to 14% efficiency. This is above the efficiency required for this to be an attractive alternative to conventional copper lead energisation. The second half of this thesis describes the design of a modular AC Homopolar motor capable of 20,000–30,000 RPM operation, and a conduction cooled wireless current supply capable of energising the field coils of this motor. The AC Homopolar motor uses a non-rotating field coil to magnetise a solid steel rotor. Although this motor is not capable of achieving the high power to mass ratio required for aircraft propulsion, the modular design enables development and demonstration of superconducting motor technologies without each requiring a bespoke motor design. Through development of this motor, it is discovered the fully laminated AC Homopolar stator architecture described in literature may not be required as much of the stator is not exposed to alternating magnetic flux. The AC Homopolar motor is redesigned to include a stator which is only partially constructed of laminated steel sheets. This hybrid stator is less expensive to manufacture due to both the reduced material cost, and the capacity for the solid steel stator components to be manufactured using conventional subtractive manufacturing methods. Finally, a conduction cooled wireless current supply is designed to match the energisation requirements of the AC Homopolar motor. Based on the earlier characterisation work, the conduction cooled supply is estimated to be 14% efficient when delivering the 200 A required by the AC Homopolar motor field coil. Prior to manufacture, the design is validated through electrical, magnetic, and thermal simulations. Components of the AC Homopolar motor and wireless supply have been manufactured. The wireless superconducting supply is fully assembled and awaiting characterisation. The AC Homopolar motor is currently being assembled and expected to be commissioned later this year.

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Direct Drive Electric Motor for STARC-ABL Tail-Cone Propulsor

Cited by 7 publications

References 1 publication

Boundary Layer Ingestion Propulsion: A Review on Numerical Modeling

Boundary Layer Ingestion Propulsion: A Review on Numerical Modeling

Optimal Voltage and Current Selection for Turboelectric Aircraft Propulsion Networks

Superconducting Electric Aircraft Powertrain Mass Reduction by Wireless Rotor Energisation

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