Relevant bibliographies by topics / Turboelectric propulsion

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  1. Journal articles
  2. Dissertations / Theses
  3. Conference papers

Academic literature on the topic 'Turboelectric propulsion'

Author: Grafiati
Published: 4 June 2021
Last updated: 14 February 2022

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Journal articles on the topic "Turboelectric propulsion"

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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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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "Turboelectric propulsion"

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Liu, Chengyuan. "Turboelectric Distributed Propulsion System Modelling." Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/8408.

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The Blended-Wing-Body is a conceptual aircraft design with rear-mounted, over wing engines. Turboelectric distributed propulsion system with boundary layer ingestion has been considered for this aircraft. It uses electricity to transmit power from the core turbine to the fans, therefore dramatically increases bypass ratio to reduce fuel consumption and noise. This dissertation presents methods on designing the TeDP system, evaluating effects of boundary layer ingestion, modelling engine performances, and estimating weights of the electric components. The method is first applied to model a turboshaft-driven TeDP system, which produces thrust only by the propulsors array. Results show that by distributing an array of propulsors that ingest a relatively large mass flow directly produces an 8% fuel burn saving relative to the commercial N+2 aircraft (such as the SAX-40 airplane). Ingesting boundary layer achieves a 7-8% fuel saving with a well-designed intake duct and the improved inlet flow control technologies. However, the value is sensitive to the duct losses and fan inlet distortion. Poor inlet performance can offset or even overwhelm this potential advantage. The total weight of the electric system would be around 5,000-7,000 kg. The large mass penalties further diminish benefits of the superconducting distributed propulsion system. The method is then applied to model a turbofan-driven TeDP system, which produces thrust by both the propulsors array and the core-engines. Results show that splitting the thrust between propulsors and core-engines could have a beneficial effect in fuel savings, when installation effects are neglected. The optimised thrust splitting ratio is between 60-90%, the final value depends on the propulsor intake pressure losses and the TeDP system bypass ratio. Moreover, splitting the thrust can reduce the weight of the electric system with the penalty of the increased core-engine weight. In short, if the power density of the superconducting system were high enough, turboshaft-driven TeDP would be preferable to power the N3-X aircraft
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Abada, Hashim H. "Turboelectric Distributed Propulsion System for NASA Next Generation Aircraft." Wright State University / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=wright1515501052742277.

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Shaw, Jennifer Catherine. "A reliability method for the analysis of turboelectric distributed propulsion electrical network architectures." Thesis, University of Strathclyde, 2016. http://oleg.lib.strath.ac.uk:80/R/?func=dbin-jump-full&object_id=27095.

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A set of goals for four successive generations of cleaner, more efficient subsonic aircraft has been published and championed by NASA; the radically different Turboelectric Distributed Propulsion (TeDP) aircraft was also proposed to meet the long term goals. Such a new aircraft design places a significant additional reliance on the electrical system, requiring architectures that meet specified thrust requirements at a minimum associated weight as well as providing the greatest performance against the proposed emissions targets. This thesis presents a method for evaluating the power and reliability profiles exhibited by a number of electrical propulsion network architectures specific to TeDP aircraft. The method is used to clearly determine the probability that each variation of the network will provide a given level of thrust. Each configuration may be compared in a visual manner, using a formulation developed as part of this thesis, showing the ‘best’ candidate solutions and establishing how each performs relative to the others in terms of both reliability afforded and thrust provided. A number of case studies are presented within this thesis to demonstrate how the developed method can be applied and secondly to test the effectiveness of bringing additional redundancy to the system and the extent to which the reliability is improved. Sensitivity studies are also undertaken to quantify the extent that component substitutions and alterations impact on network reliability. The overall goal is to establish the features of a TeDP network architecture that consistently exhibits the greatest thrust reliability profile. In conducting this research, the work of this thesis progresses the understanding of the TeDP concept with a particular focus on the NASA N3-X aircraft being used to validate the proposed method. Specifically the knowledge in the area of the concept reliability and predicted failure rates are addressed with recommendations being put forward on how each can be improved. These recommendations form a useful input to the general body of research that is working towards NASA’s future long term goals for cleaner more efficient aircraft.
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de, Tenorio Cyril. "Methods for collaborative conceptual design of aircraft power architectures." Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/34818.

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This thesis proposes an advanced architecting methodology. This methodology allows for the sizing and optimization of aircraft system architecture concepts and the establishment of subsystem development strategies. The process is implemented by an architecting team composed of subsystem experts and architects. The methodology organizes the architecture definition using the SysML language. Using meta-modeling techniques, this definition is translated into an analysis model which automatically integrates subsystem analyses in a fashion that represents the specific architecture concept described by the team. The resulting analysis automatically sizes the subsystems composing it, synthesizes their information to derive architecture-level performance and explores the architecture internal trade-offs. This process is facilitated using the Coordinated Optimization method proposed in this dissertation. This method proposes a multi-level optimization setup. An architecture-level optimizer orchestrates the subsystem sizing optimizations in order to optimize the aircraft as whole. The methodologies proposed in this thesis are tested and demonstrated on a proof of concept based on the exploration of turbo-electric propulsion aircraft concepts.
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Campbell, Angela Mari. "Architecting aircraft power distribution systems via redundancy allocation." Diss., Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/53087.

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Recently, the environmental impact of aircraft and rising fuel prices have become an increasing concern in the aviation industry. To address these problems, organizations such as NASA have set demanding goals for reducing aircraft emissions, fuel burn, and noise. In an effort to reach the goals, a movement toward more-electric aircraft and electric propulsion has emerged. With this movement, the number of critical electrical loads on an aircraft is increasing causing power system reliability to be a point of concern. Currently, power system reliability is maintained through the use of back-up power supplies such as batteries and ram-air-turbines (RATs). However, the increasing power requirements for critical loads will quickly outgrow the capacity of the emergency devices. Therefore, reliability needs to be addressed when designing the primary power distribution system. Power system reliability is a function of component reliability and redundancy. Component reliability is often not determined until detailed component design has occurred; however, the amount of redundancy in the system is often set during the system architecting phase. In order to meet the capacity and reliability requirements of future power distribution systems, a method for redundancy allocation during the system architecting phase is needed. This thesis presents an aircraft power system design methodology that is based upon the engineering decision process. The methodology provides a redundancy allocation strategy and quantitative trade-off environment to compare architecture and technology combinations based upon system capacity, weight, and reliability criteria. The methodology is demonstrated by architecting the power distribution system of an aircraft using turboelectric propulsion. The first step in the process is determining the design criteria which includes a 40 MW capacity requirement, a 20 MW capacity requirement for the an engine-out scenario, and a maximum catastrophic failure rate of one failure per billion flight hours. The next step is determining gaps between the performance of current power distribution systems and the requirements of the turboelectric system. A baseline architecture is analyzed by sizing the system using the turboelectric system power requirements and by calculating reliability using a stochastic flow network. To overcome the deficiencies discovered, new technologies and architectures are considered. Global optimization methods are used to find technology and architecture combinations that meet the system objectives and requirements. Lastly, a dynamic modeling environment is constructed to study the performance and stability of the candidate architectures. The combination of the optimization process and dynamic modeling facilitates the selection of a power system architecture that meets the system requirements and objectives.
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Drška, Martin. "Snížení enviromentálních dopadů letecké dopravy moderními technologiemi." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-231974.

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This master’s thesis discusses the impact of air traffic on our environment. The fuels combustion, the conditions necessary for realization of air traffic, or the situations resulting from it, such as aircraft maintenance, noise, emergencies, etc., have a negative impact on not only on the environment, but also on health and comfort of people, as well as flora and fauna, exposed to these conditions. Apart from the air traffic impacts on our environment mentioned above, the thesis also describes especially the possibilities of their reduction and companies dealing with them. The large main part of thesis paper is dedicated to an analysis of a new aircraft design technology, which should reduce the production of emissions in the future.
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Conference papers on the topic "Turboelectric propulsion"

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Łukasik, Borys. "Turboelectric Distributed Propulsion System As a Future Replacement for Turbofan Engines." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63834.

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The main purpose of this paper is to discuss the possibility of standard turbofan engine replacement by the turboelectric distributed propulsion system, in future commercial aviation. Paper describes how the distributed propulsion allows to reach significantly greater propulsive efficiency than state-of-the-art high bypass turbofan engines, and presents turboelectric system as the only practical method of distributed propulsion implementation. However, since extra weight of the electric components that would be added can overcome the high propulsive efficiency benefit, a detailed analysis is needed to verify the feasibility of such system. This article shows results of such analysis that was conducted for 90 PAX class regional jet. Thermodynamic cycle calculations, performed for both, turbofan engine and turboelectric distributed propulsion are presented. They prove that distributed propulsion is able to provide great reduction in fuel consumption of uninstalled propulsion system, while performed mission analysis depicts the penalty of extra mass of electric appliances, showing actual profits that are achievable. On this example, advantages and disadvantages of the turboelectric distributed propulsion system in comparison with modern turbofan engines are discuss, taking into account the potential technological development of turbofan engine and additional non-propulsive benefits that turboelectric system is able to provide. Finally, this document also presents mass estimations for different scenarios of electric appliances evolution, which highlight the technology levels that need to be achieved before the system can be introduced in commercial service.
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Athanasakos, Georgios, Nikolaos Aretakis, Alexios Alexiou, and Konstantinos Mathioudakis. "Turboelectric Distributed Propulsion Modelling Accounting for Fan Boundary Layer Ingestion and Inlet Distortion." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14621.

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Abstract A modelling approach of Boundary Layer Ingesting (BLI) propulsion systems is presented. Initially, a distorted compressor model is created utilizing the parallel compressor theory to estimate the impact of inlet distortion on fan performance. Next, a BLI propulsor model is developed considering both distortion effects and reduced inlet momentum drag caused from boundary layer ingestion. Finally, a Turbo-electric Distributed Propulsion (TeDP) model is set up, consisting of the BLI propulsor model, the associated turboshaft engine model and a representation of the relevant electrical system. Each model is validated through comparison with numerical and/or experimental data. A design point calculation is carried out initially to establish propulsor key dimensions for a specified number of propulsors and assuming common inlet conditions. Parametric design point analyses are then carried out to study the influence of propulsors number and location under different inlet conditions, by varying fan design pressure ratio between 1.15 and 1.5. BLI and non BLI configurations are compared at propulsion system level to assess the BLI benefits. The results show that maximum BLI gains of 9.3% in TSFC and 4.7% in propulsive efficiency can be achieved with 16 propulsors and FPR = 1.5, compared to podded propulsors, while further benefits can be achieved by moving the propulsor array backwards in the airframe.
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Ross, Christine, Michael Armstrong, Mark Blackwelder, Catherine Jones, Patrick Norman, and Steven Fletcher. "Turboelectric Distributed Propulsion Protection System Design Trades." In SAE 2014 Aerospace Systems and Technology Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2014. http://dx.doi.org/10.4271/2014-01-2141.

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Sitton, Travis, and Kaz Furmanczyk. "AC to DC Converter for Turboelectric Propulsion." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-4237.

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Choi, Benjamin, Gerald V. Brown, Carlos Morrison, and Timothy Dever. "Propulsion Electric Grid Simulator (PEGS) for Future Turboelectric Distributed Propulsion Aircraft." In 12th International Energy Conversion Engineering Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-3644.

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Gray, Justin S., Gaetan K. Kenway, Charles A. Mader, and Joaquim R. R. A. Martins. "Aero-propulsive Design Optimization of a Turboelectric Boundary Layer Ingestion Propulsion System." In 2018 Aviation Technology, Integration, and Operations Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3976.

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Jansen, Ralph, Kirsten P. Duffy, and Gerald Brown. "Partially Turboelectric Aircraft Drive Key Performance Parameters." In 53rd AIAA/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4702.

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Rouser, Kurt P., Nicholas Lucido, Matthew Durkee, Andrew Bellcock, and Tyler Zimbelman. "Development of Turboelectric Propulsion and Power for Small Unmanned Aircraft." In 2018 Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4618.

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Hamilton, Kent A., and Rodney Badcock. "Cryogenic Sensitivity of Turboelectric Commercial Aircraft with HTS Propulsion Motors." In AIAA Propulsion and Energy 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3659.

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Jansen, Ralph, Gerald V. Brown, James L. Felder, and Kirsten P. Duffy. "Turboelectric Aircraft Drive Key Performance Parameters and Functional Requirements." In 51st AIAA/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-3890.

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