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Journal articles on the topic 'Turboelectric propulsion'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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1

Choi, Benjamin B. "Propulsion Powertrain Simulator: Future turboelectric distributed-propulsion aircraft." IEEE Electrification Magazine 2, no. 4 (December 2014): 23–34. http://dx.doi.org/10.1109/mele.2014.2364901.

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2

Raja Sekaran, Paulas, Amir S. Gohardani, Georgios Doulgeris, and Riti Singh. "Liquid hydrogen tank considerations for turboelectric distributed propulsion." Aircraft Engineering and Aerospace Technology 86, no. 1 (December 20, 2013): 67–75. http://dx.doi.org/10.1108/aeat-12-2011-0195.

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3

Armstrong, Michael J., Christine A. H. Ross, Mark J. Blackwelder, and Kaushik Rajashekara. "Propulsion System Component Considerations for NASA N3-X Turboelectric Distributed Propulsion System." SAE International Journal of Aerospace 5, no. 2 (October 22, 2012): 344–53. http://dx.doi.org/10.4271/2012-01-2165.

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4

Dae Kim, Hyun, James L. Felder, Michael T. Tong, Jeffrey J. Berton, and William J. Haller. "Turboelectric distributed propulsion benefits on the N3-X vehicle." Aircraft Engineering and Aerospace Technology 86, no. 6 (September 30, 2014): 558–61. http://dx.doi.org/10.1108/aeat-04-2014-0037.

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5

Ibrahim, Kingsley, Suresh Sampath, and Devaiah Nalianda. "Optimal Voltage and Current Selection for Turboelectric Aircraft Propulsion Networks." IEEE Transactions on Transportation Electrification 6, no. 4 (December 2020): 1625–37. http://dx.doi.org/10.1109/tte.2020.3004308.

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6

Alrashed, Mosab, Theoklis Nikolaidis, Pericles Pilidis, Wael Alrashed, and Soheil Jafari. "Economic and environmental viability assessment of NASA’s turboelectric distribution propulsion." Energy Reports 6 (November 2020): 1685–95. http://dx.doi.org/10.1016/j.egyr.2020.06.019.

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7

Zong, Jianan, Bingjie Zhu, Zhongxi Hou, Xixiang Yang, and Jiaqi Zhai. "Evaluation and Comparison of Hybrid Wing VTOL UAV with Four Different Electric Propulsion Systems." Aerospace 8, no. 9 (September 9, 2021): 256. http://dx.doi.org/10.3390/aerospace8090256.

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Electric propulsion technology has attracted much attention in the aviation industry at present. It has the advantages of environmental protection, safety, low noise, and high design freedom. An important research branch of electric propulsion aircraft is electric vertical takeoff and landing (VTOL) aircraft, which is expected to play an important role in urban traffic in the future. Limited by battery energy density, all electric unmanned aerial vehicles (UAVs) are unable to meet the longer voyage. Series/parallel hybrid-electric propulsion and turboelectric propulsion are considered to be applied to VTOL UAVs to improve performances. In this paper, the potential of these four configurations of electric propulsion systems for small VTOL UAVs are evaluated and compared. The main purpose is to analyze the maximum takeoff mass and fuel consumption of VTOL UAVs with different propulsion systems that meet the same performance requirements and designed mission profiles. The differences and advantages of the four types propulsion VTOL UAV in the maximum takeoff mass and fuel consumption are obtained, which provides a basis for the design and configuration selection of VTOL UAV propulsion system.

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8

Gray, Justin S., and Joaquim R. R. A. Martins. "Coupled aeropropulsive design optimisation of a boundary-layer ingestion propulsor." Aeronautical Journal 123, no. 1259 (October 31, 2018): 121–37. http://dx.doi.org/10.1017/aer.2018.120.

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AbstractAirframe–propulsion integration concepts that use boundary-layer ingestion (BLI) have the potential to reduce aircraft fuel burn. One concept that has been recently explored is NASA’s STARC-ABL aircraft configuration, which offers the potential for fuel burn reduction by using a turboelectric propulsion system with an aft-mounted electrically driven BLI propulsor. So far, attempts to quantify this potential fuel burn reduction have not considered the full coupling between the aerodynamic and propulsive performance. To address the need for a more careful quantification of the aeropropulsive benefit of the STARC-ABL concept, we run a series of design optimisations based on a fully coupled aeropropulsive model. A 1D thermodynamic cycle analysis is coupled to a Reynolds-averaged Navier–Stokes simulation to model the aft propulsor at a cruise condition and the effects variation in propulsor design on overall performance. A series of design optimisation studies are performed to minimise the required cruise power, assuming different relative sizes of the BLI propulsor. The design variables consist of the fan pressure ratio, static pressure at the fan face, and 311 variables that control the shape of both the nacelle and the fuselage. The power required by the BLI propulsor is compared with a podded configuration. The results show that the BLI configuration offers 6–9% reduction in required power at cruise, depending on assumptions made about the efficiency of power transmission system between the under-wing engines and the aft propulsor. Additionally, the results indicate that the power transmission efficiency directly affects the relative size of the under-wing engines and the aft propulsor. This design optimisation, based on computational fluid dynamics, is shown to be essential to evaluate current BLI concepts and provides a powerful tool for the design of future concepts.

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9

Lowe, Angela, and Dimitri N. Mavris. "Technology Selection for Optimal Power Distribution Efficiency in a Turboelectric Propulsion System." SAE International Journal of Aerospace 5, no. 2 (October 22, 2012): 425–37. http://dx.doi.org/10.4271/2012-01-2180.

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10

Liu, Chengyuan, Georgios Doulgeris, Panagiotis Laskaridis, and Riti Singh. "Thermal cycle analysis of turboelectric distributed propulsion system with boundary layer ingestion." Aerospace Science and Technology 27, no. 1 (June 2013): 163–70. http://dx.doi.org/10.1016/j.ast.2012.08.003.

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11

Cinar, Gokcin, Elena Garcia, and Dimitri N. Mavris. "A framework for electrified propulsion architecture and operation analysis." Aircraft Engineering and Aerospace Technology 92, no. 5 (August 19, 2019): 675–84. http://dx.doi.org/10.1108/aeat-06-2019-0118.

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Purpose The purpose of this paper was to create a generic and flexible framework for the exploration, evaluation and side-by-side comparison of novel propulsion architectures. The intent for these evaluations was to account for varying operation strategies and to support architectural design space decisions, at the conceptual design stages, rather than single-point design solutions. Design/methodology/approach To this end, main propulsion subsystems were categorized into energy, power and thrust sources. Two types of matrices, namely, the property and interdependency matrices, were created to describe the relationships and power flows among these sources. These matrices were used to define various electrified propulsion architectures, including, but not limited to, turboelectric, series-parallel and distributed electric propulsion configurations. Findings As a case study, the matrices were used to generate and operate the distributed electric propulsion architecture of NASA’s X-57 Mod IV aircraft concept. The mission performance results were acceptably close to the data obtained from the literature. Finally, the matrices were used to simulate the changes in the operation strategy under two motor failure scenarios to demonstrate the ease of use, rapidness and automation. Originality/value It was seen that this new framework enables rapid and analysis-based comparisons among unconventional propulsion architectures where solutions are driven by requirements.

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12

Armstrong, Michael J., Christine A. H. Ross, Mark J. Blackwelder, and Kaushik Rajashekara. "Trade Studies for NASA N3-X Turboelectric Distributed Propulsion System Electrical Power System Architecture." SAE International Journal of Aerospace 5, no. 2 (October 22, 2012): 325–36. http://dx.doi.org/10.4271/2012-01-2163.

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13

ALRASHED, Mosab, Theoklis NIKOLAIDIS, Pericles PILIDIS, and Soheil JAFARI. "Utilisation of turboelectric distribution propulsion in commercial aviation: A review on NASA’s TeDP concept." Chinese Journal of Aeronautics 34, no. 11 (November 2021): 48–65. http://dx.doi.org/10.1016/j.cja.2021.03.014.

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14

Shaw, Jennifer C., Patrick Norman, Stuart Galloway, and Graeme Burt. "A Method for the Evaluation of the Effectiveness of Turboelectric Distributed Propulsion Power System Architectures." SAE International Journal of Aerospace 7, no. 1 (September 16, 2014): 35–43. http://dx.doi.org/10.4271/2014-01-2120.

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15

Liu, Chengyuan, Esteban Valencia, and Jinfang Teng. "Design point analysis of the turbofan-driven turboelectric distributed propulsion system with boundary layer ingestion." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 230, no. 6 (September 21, 2015): 1139–49. http://dx.doi.org/10.1177/0954410015605546.

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16

Alrashed, Mosab, Theoklis Nikolaidis, Pericles Pilidis, Wael Alrashed, and Soheil Jafari. "Corrigendum to “Economic and environmental viability assessment of NASA’s turboelectric distribution propulsion” [Energy Rep. 6C (2020) 1685–1695]." Energy Reports 6 (November 2020): 3491. http://dx.doi.org/10.1016/j.egyr.2020.11.069.

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17

Alrashed, Mosab, Theoklis Nikolaidis, Pericles Pilidis, Wael Alrashed, and Soheil Jafari. "Corrigendum to “Economic and environmental viability assessment of NASA’s turboelectric distribution propulsion” [Energy Rep. 6 (2020) 1685–1695]." Energy Reports 6 (November 2020): 3492. http://dx.doi.org/10.1016/j.egyr.2020.11.103.

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18

Zhang, Yang, Zhou Zhou, Kelei Wang, and Xu Li. "Aerodynamic Characteristics of Different Airfoils under Varied Turbulence Intensities at Low Reynolds Numbers." Applied Sciences 10, no. 5 (March 2, 2020): 1706. http://dx.doi.org/10.3390/app10051706.

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A numerical study was conducted on the influence of turbulence intensity and Reynolds number on the mean topology and transition characteristics of flow separation to provide better understanding of the unsteady jet flow of turboelectric distributed propulsion (TeDP) aircraft. By solving unsteady Reynolds averaged Navier-Stokes (URANS) equation based on C-type structural mesh and γ - Re ˜ θ t transition model, the aerodynamic characteristics of the NACA0012 airfoil at different turbulence intensities was calculated and compared with the experimental results, which verifies the reliability of the numerical method. Then, the effects of varied low Reynolds numbers and turbulence intensities on the aerodynamic performance of NACA0012 and SD7037 were investigated. The results show that higher turbulence intensity or Reynolds number leads to more stable airfoil aerodynamic performance, larger stalling angle, and earlier transition with a different mechanism. The generation and evolution of the laminar separation bubble (LSB) are closely related to Reynolds number, and it would change the effective shape of the airfoil, having a big influence on the airfoil’s aerodynamic characteristics. Compared with the symmetrical airfoil, the low-Reynolds-number airfoil can delay the occurrence of flow separation and produce more lift in the same conditions, which provides guidance for further airfoil design under TeDP jet flow.

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19

Sener, Eralp, Isil Yazar, Gurhan Ertasgin, and Hasan Yamik. "Baseline architecture design for a turboelectric distributed propulsion system using single turboshaft engine operational scenario." International Journal of Turbo & Jet-Engines, November 18, 2020. http://dx.doi.org/10.1515/tjeng-2020-0041.

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AbstractReducing the carbon footprints of aerial transportation became a major target for both industries and academia. Various solutions have been proposed to develop cleaner alternative methods for green transportation. Full electric, hybrid electric, and turboelectric propulsion system architectures intend to reduce greenhouse gas emissions and fuel consumption of today’s aero gas turbine engines. In this study, a turboelectric propulsion system, which is considered as the most promising technology for future aviation is selected for modelling and simulation. As the main power supply, a high fidelity mathematical model of GE T700 turboshaft engine is constructed in MATLAB/Simulink to emulate the technology of today. Selected aero gas turbine’s mathematical model is combined with NASA’s Baseline electrical power distribution architecture which is firstly designed for N-3X turboelectric aircraft. MATLAB/Simulink model is utilized to analyses a single-engine operational scenario of twin-engine aircraft which is a major design consideration due to single-engine failure. Power requirements, distribution percentages, preliminary power assessment for power electronic systems and nominal power capacities of each electrical unit of a turboelectric propulsion system are obtained using GE T700 as the main power supply.

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20

Sener, Eralp, Isil Yazar, Gurhan Ertasgin, and Hasan Yamik. "Baseline architecture design for a turboelectric distributed propulsion system using single turboshaft engine operational scenario." International Journal of Turbo & Jet-Engines, November 18, 2020. http://dx.doi.org/10.1515/tjj-2020-0041.

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Abstract Reducing the carbon footprints of aerial transportation became a major target for both industries and academia. Various solutions have been proposed to develop cleaner alternative methods for green transportation. Full electric, hybrid electric, and turboelectric propulsion system architectures intend to reduce greenhouse gas emissions and fuel consumption of today’s aero gas turbine engines. In this study, a turboelectric propulsion system, which is considered as the most promising technology for future aviation is selected for modelling and simulation. As the main power supply, a high fidelity mathematical model of GE T700 turboshaft engine is constructed in MATLAB/Simulink to emulate the technology of today. Selected aero gas turbine’s mathematical model is combined with NASA’s Baseline electrical power distribution architecture which is firstly designed for N-3X turboelectric aircraft. MATLAB/Simulink model is utilized to analyses a single-engine operational scenario of twin-engine aircraft which is a major design consideration due to single-engine failure. Power requirements, distribution percentages, preliminary power assessment for power electronic systems and nominal power capacities of each electrical unit of a turboelectric propulsion system are obtained using GE T700 as the main power supply.

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21

Yazar, I. "Simulation of a High Fidelity Turboshaft Engine-Alternator Model for Turboelectric Propulsion System Design and Applications." International Journal of Turbo & Jet-Engines, December 11, 2018. http://dx.doi.org/10.1515/tjj-2018-0036.

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Abstract The term sustainability became a popular subject both in the automotive industries and in the aerospace industries. Increasing and threatening environmental pollution problems and reduction in limited fuel sources are motivating either industries and academicians to develop alternative power systems to sustain more healthier and economical life in the long term. One innovation that has been researched in the automotive industry is all electric and hybrid electric propulsion concepts. These concepts have also been proposed as alternative solutions for aviation. These novel propulsion technologies are composed of a gas turbine/internal combustion engine structure (necessary for hybrid electric and turboelectric propulsion systems) and/or energy storage components (battery, fuel cell and so on.) with multiple electric motors respectively. In this paper, simulation of a high fidelity turboshaft engine-alternator model for turboelectric propulsion system is derived. To develop an aero-thermal engine model, GE T700 turboshaft engine data is used and constructed model is connected to an alternator model on MATLAB/Simulink environment. Open-loop simulations are carried out and satisfactory results are obtained.Simulation results are compared to the real engine design point data. Results show that there are acceptable differences between the simulation results and the real engine data. The power balances between compressor - high pressure turbine and power turbine – alternator are proven in the mathematical model. It is expected that the proposed model can be easily extended to power system design and power management studies in turboelectric propulsion systems and also in other suitable novel propulsion systems.

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22

Alrashed, Mosab, Theoklis Nikolaidis, Pericles Pilidis, Soheil Jafari, and Wael Alrashed. "Key performance indicators for turboelectric distributed propulsion." International Journal of Productivity and Performance Management ahead-of-print, ahead-of-print (February 23, 2021). http://dx.doi.org/10.1108/ijppm-02-2020-0081.

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PurposeRecent advancements in electrified transportation have been necessitated by the need to reduce environmentally harmful emissions. Accordingly, several aviation organisations and governments have introduced stringent emission reduction targets for 2050. One of the most promising technologies proposed for achieving these targets is turboelectric distributed propulsion (TeDP). The objective of this study was to explore and identify key indicators for enhancing the applicability of TeDP in air transportation.Design/methodology/approachAn enhancement valuation method was proposed to overcome the challenges associated with TeDP in terms of technological, economic and environmental impacts. The result indicators (RIs) were determined; the associated performance indicators (PIs) were analysed and the key RIs and PIs for TeDP were identified. Quantitative measurements were acquired from a simulated TeDP case study model to estimate the established key PIs.FindingsIt was determined that real-world TeDP efficiency could be enhanced by up to 8% by optimising the identified key PIs.Originality/valueThis study is the first to identify the key PIs of TeDP and to include a techno-economic environmental risk analysis (TERA) based on the identified key PIs. The findings could guide developers and researchers towards potential focus areas to realise the adoption of TeDP.

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23

Sener, Eralp, Isil Yazar, and Gurhan Ertasgin. "Single Turboshaft Engine Failure Analysis of an Inner Bus Tie Architecture for Turboelectric Distributed Propulsion System." SAE International Journal of Aerospace 13, no. 2 (October 19, 2020). http://dx.doi.org/10.4271/01-13-02-0013.

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