Sizing and Performance Analysis of a Turbo-Hybrid-Electric Regional Jet for the NASA ULI Program

Perullo, Christopher; Alahmad, Alan; Wen, Jiajie; D’Arpino, Matilde; Canova, Marcello; Mavris, Dimitri N.; Benzakein, M. J.

doi:10.2514/6.2019-4490

Cited by 15 publications

(19 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…1. This architecture is consistent with the previous paper [3] and the update of the ULI program in this year [4], where more details can be found. As shown in this figure, the electric propulsors, which are the electric fans driven by the motors.…”

Section: A Architecture Of the Electric Propulsion Systemsupporting

confidence: 90%

“…The proper PCM should be selected in terms of the working temperature of the motor and the inverter. The working conditions for the IMD were provided by the team from University of Wisconsin-Madison [3]: the target working temperature of the stator is 135 o C, and the its maximum working temperature is 180 o C; the target working temperature of the rotor is 139 o C, and its maximum working temperature is 200 o C. Based on such working conditions, two types of PCM, magnesium chloride hexahydrate (salt hydrate) [23] and Urea-KCl (eutectic compound) [24], are selected for assessment, and the corresponding properties are listed in Table 1. It should be noted that the melting temperatures of the selected PCM are both slightly lower than the target working temperature to effectively remove the heat when the IMD is working at its optimal operation temperature.…”

Section: Pcm To Absorb the Heatmentioning

confidence: 99%

“…A number of technologies and aircraft concepts have been proposed and studied to meet such goals, and the turboelectric aircraft is one of the concepts of interest. Under the NASA University Leadership Initiative (ULI) program, teams from The Ohio State University (OSU), Georgia Tech (GT), University of Wisconsin-Madison (UW), University of Maryland (UMD), and North Carolina A&T (NCA&T) are collaborating to demonstrate the concept of Hybrid Turboelectric Distributed Propulsion (HTeDP) with corresponding technologies for a 2030 regional jet, of which the previous work has been summarized in authors' previous paper [3] and the update is summarized in the accompanying paper this year [4].…”

Section: Introductionmentioning

confidence: 99%

“…On the other hand, the heat generated by the electric propulsion system is much larger than the heat generated by other existing electric systems in the aircraft. Considering the class of a reginal jet as studied in NASA ULI program, each motor is of 2.1 MW (8 in total) with a corresponding efficiency around 0.98 [3]. The corresponding heat generated is around 42 kW (336 kW in total), which is significantly larger than current electric systems applied in the aircraft.…”

Section: Introductionmentioning

confidence: 99%

“…However, the TMS of interest in this paper only refers to the subsystem that removes the heat generated from the electric propulsion system where the major cooling challenges lie in. Since the conventional ECS is cable of cooling both the cabin and the battery as shown in the previous work [3], the corresponding TMS for these two systems will not be discussed in detail in this paper.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Design and Analysis of the Thermal Management System of a Hybrid Turboelectric Regional Jet for the NASA ULI Program

Shi

Sanders

Alahmad

et al. 2020

AIAA Propulsion and Energy 2020 Forum

Self Cite

View full text Add to dashboard Cite

A team of researchers from multiple universities are collaborating on the demonstration of a hybrid turboelectric regional jet for 2030 under the NASA ULI Program. The thermal management is one of the major challenges for the development of such an electric propulsion concept. Existing studies hardly modeled the thermal management systems with the propulsion systems nor integrated it to the aircraft for system-and mission-level analyses. Therefore, it is very difficult to verify whether a design of the thermal management system is feasible and optimal based on current literature. To fill this gap, this paper presents a design of the thermal management system for the hybrid turboelectric regional jet under the ULI program and integrates it to the aircraft. The TMS is tested against the cooling requirements, where the thermal loads from the electric propulsion system are quantified through the whole mission. Potential solutions for peak thermal loads during takeoff and climb are also proposed and analyzed, where additional coolant or phase change materials are used. Moreover, the impacts of the TMS on the system-and missionlevel performance are investigated by the presented integration approach as well. It is discovered that a basic oil-air thermal management system cannot fully remove the heat during the early mission segments. Using additional coolant or phase change materials as heat absorption can handle such heating problem, but penalty due to additional weight is added. It is found that greater penalties in fuel burn and takeoff weight are added by additional coolant solution than the phase change material solution.

show abstract

Section: A Architecture Of the Electric Propulsion Systemsupporting

confidence: 90%