Turboelectric Distributed Propulsion System Modelling for Hybrid-Wing-Body Aircraft

Liu, Chengyuan; Doulgeris, Georgios; Laskaridis, Panagiotis; Singh, Riti

doi:10.2514/6.2012-3700

Cited by 16 publications

(15 citation statements)

References 4 publications

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“…Modeling distortion enables the incorporation of the inlet flow field characteristics into the analysis. Past studies on effects of distortion [13]- [15] have extensively used the PC approach with this aim.…”

Section: Distortion Modelingmentioning

confidence: 99%

Methodology for the Assessment of Distributed Propulsion Configurations with Boundary Layer Ingestion Using the Discretized Miller Approach

Valencia

Liu

Nalianda

et al. 2017

IREASE

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The growing global environmental awareness has motivated the search for more fuelefficient aircraft propulsion systems. In this context, a configuration based on distributed propulsion with Boundary Layer Ingestion (BLI) has been found to present potential performance benefits. The concept has been documented and explored extensively during the last few years and various aerodynamic integration issues, such as: high levels of distortion and low intake pressure recovery; have been identified as factors that may be detrimental in realizing the technology full potential. Parametric and parallel compressor (PC) approaches have been used to assess the effect of these aerodynamic issues on propulsors fan performance. However, in the context of BLI, these tools are unable to assess the effects of combined radial and circumferential distortion that are present. In order to assess the combined distortion patterns and the effects of distortion at component and system levels, this study uses a novel method based on semi-empirical correlations denominated the Discretized Miller (DM) approach. This method was developed for BLI systems previously by the author, and it is now incorporated into the propulsor performance method to assess the effects of the combined radial and circumferential distortion patterns. The performance analysis, undertaken at a component and system level, aims to assess several propulsion architectures, using Thrust Specific Fuel Consumption (TSFC) as figure of merit. To define the suitability of the distributed propulsor array in this study, an airframe layout based on the N3-X aircraft concept and High Temperature Superconducting (HTS) electric motor capabilities were assumed. The key contribution of this study is to enable the introduction of the concept of thrust split between energy source and propulsion system in the system analysis, and thereby, allows the assessment of its effects on different propulsion system layouts, while considering the BLI induced distortion. The results obtained with this alternative performance method showed that BLI reduces the fan efficiency of a conventional fan by approximately 2%, whilst corroborating the TSFC trends observed in previous studies. The study also indicates that when sizing effects of propulsors and core-engines were neglected, a propulsion system configuration with 75% thrust split was found optimum.

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Section: Distortion Modelingmentioning

confidence: 99%

Methodology for the Assessment of Distributed Propulsion Configurations with Boundary Layer Ingestion Using the Discretized Miller Approach

Valencia

Liu

Nalianda

et al. 2017

IREASE

Self Cite

View full text Add to dashboard Cite

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“…A number of applications are examining the possibility of using superconducting cables for the transfer of electrical power, including power distribution networks and more recently the concept of developing hybrid electric propulsion systems for aircraft [1, 2]. This is being driven by ongoing research to identify more efficient designs for air travel, which are being pursued by organisations including the national aeronautics and space administration (NASA) and aerospace technical institute.…”

Section: Introductionmentioning

confidence: 99%

“…To meet the requirements of the design proposed by NASA [2], the semiconductor selected needs to demonstrate Low on‐state resistance at 20 K Low resistance variation with temperature around 20 K …”

Section: Introductionmentioning

confidence: 99%

Evaluating suitable semiconducting materials for cryogenic power electronics

Bradley

Donaghy‐Spargo

Atkinson

et al. 2019

J. eng.

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“…11 Based on the above two configurations, extensive researches on DPC have been carried out to demonstrate the advanced designs, performance improvement, practicality, and potentiality of the distributed propulsion system. [12][13][14][15][16][17][18][19][20][21][22][23][24][25][26][27][28] As the important feature of DPC, BLI effect and the aerodynamic performance of a propulsion system were investigated by Plas. 29 A quantitative experiment on the ''silent aircraft'' showed that fuel consumption can be reduced by 3.8% due to the BLI effect.…”

Section: Introductionmentioning

confidence: 99%

Integrated flight/propulsion optimal control for DPC aircraft based on the GA-RPS algorithm

Zhang

Kang

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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The new distributed propulsion configuration (DPC) can effectively improve fuel efficiency and reduce pollution, but also brings in special cross-coupling effects between the flight and propulsion systems. To tackle this problem, integrated flight/propulsion modeling and optimal control of DPC with boundary layer ingestion (BLI) and supercirculation features are systematically investigated. As the basis, by taking the inherent BLI and supercirculation features into consideration, an integrated flight/propulsion model of SAX-40 is built to reflect the actual complex engine-aircraft coupling effects. Then an integrated flight/propulsion optimal control scheme is proposed to deal with the strong coupling effects and to implement the comprehensive control of redundant control surfaces as well as the distributed engines. Under this scheme, a detailed description of the optimal control problem is presented, and a novel two-stage optimization algorithm named genetic algorithm-random pattern search (GA-RPS) is proposed to solve this complex optimal problem. By the new strategies of ''parallel genetic algorithm computing in sub-regions'' and ''random pattern search'' in the GA-RPS algorithm, the optimization accuracy and convergence speed are effectively improved. Simulation results demonstrate the effectiveness of the GA-RPS algorithm and the significant performance improvement to DPC by optimization.

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Turboelectric Distributed Propulsion System Modelling for Hybrid-Wing-Body Aircraft

Cited by 16 publications

References 4 publications

Methodology for the Assessment of Distributed Propulsion Configurations with Boundary Layer Ingestion Using the Discretized Miller Approach

Methodology for the Assessment of Distributed Propulsion Configurations with Boundary Layer Ingestion Using the Discretized Miller Approach

Evaluating suitable semiconducting materials for cryogenic power electronics

Integrated flight/propulsion optimal control for DPC aircraft based on the GA-RPS algorithm

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