Multi-point Design and Optimization of a Turboshaft Engine for Tiltwing Turboelectric VTOL Air Taxi

Chapman, Jeffryes W.

doi:10.2514/6.2019-1948

Cited by 4 publications

(5 citation statements)

References 10 publications

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“…3.1.1 Small engine cores. The performance of an engine core is primarily assessed by a certification agency, and the size of the engine core is intimately related to the overall system performance (Chapman, 2019;Felder et al, 2009a;Kim et al, 2013). In this case, the engine cores of a TeDP system must be relatively small to avoid weight and size issues that are likely to impact system efficiency.…”

Section: Results Indicatorsmentioning

confidence: 99%

Key performance indicators for turboelectric distributed propulsion

Alrashed

Nikolaidis

Pilidis

et al. 2021

IJPPM

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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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Section: Results Indicatorsmentioning

confidence: 99%

Key performance indicators for turboelectric distributed propulsion

Alrashed

Nikolaidis

Pilidis

et al. 2021

IJPPM

View full text Add to dashboard Cite

show abstract

“…For computing the weight of the engine in this study, a simple correlation was developed from historical data for turboshaft engines based on the overall airflow through the engine, which was presented in Chapman work. Previous studies of this engine [18] showed that thermodynamic cycle performance and weight were relatively insensitive to major design parameters such as overall pressure ratio and combustor exit temperature. Therefore, given the complexity of the cycle analysis calculations, the detailed cycle model was pre-executed with a surrogate model of the performance characteristics used in the integrated analysis.…”

Section: Thermodynamic Cycle Analysismentioning

confidence: 96%

“…For this work, the pre-computed data-table approach was used for the cycle analysis as previous studies showed that there was not enough design freedom in the thermodynamic design to warrant tight coupling of this discipline with the rest of the system. [18] For the mission performance modeling element of the overall process, two separate models were constructed for evaluating the performance of a tiltwing UAM concept. The first, shown in the XDSM in Fig.…”

Section: Multidisciplinary Design Analysis and Optimization Envmentioning

confidence: 99%

“…For the tiltwing turboelectric concept under consideration in this paper, the pyCycle model developed is represented by the blue portion of Figure 7 and is described in more detail in a paper by Chapman. [18] In summary, the flowpath for the turboshaft engine in this study includes an inlet, compressor, burner, turbine, power turbine and nozzle. Furthermore, the compressor and turbine are connected by a shaft with the power turbine connected to the generator by a separate shaft.…”

Section: Thermodynamic Cycle Analysismentioning

confidence: 99%

“…Finally, the turboshaft engine weight was approximated using a linear regression based on shaft power for existing turboshaft engines from Chapman. [18]…”

Section: Aircraft Mass Analysismentioning

confidence: 99%

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Urban air taxis, also known as urban air mobility (UAM) vehicles, are anticipated to be an area of significant market growth in the near future. These vehicles are typically vertical takeoff and landing (VTOL) designs which are capable of carrying 1 to 30 passengers in an intra-urban environment with flights of less than 50 nautical miles. Development of UAM vehicles and their integration into the airspace will be enabled by advancements in a number of areas including electrified propulsion systems, structures, acoustics, automation, and controls. However, the strong multidisciplinary interactions for these unique vehicles presents a significant new design challenge. This work describes the development of a multidisciplinary analysis and optimization environment which can be used to support the conceptual design of these UAM vehicles, using efficient gradient based optimization with analytic derivatives. The tools included in this multidisciplinary analysis model the aircraft trajectory, vehicle aerodynamics, structures, and electrified propulsion system. The multidisciplinary environment created in this research is unique in that all the physics tools are tightly integrated together, with the trajectory model directly calling the aerodynamics, structures, and propulsion models. This multidisciplinary analysis environment is then demonstrated in the design optimization of a turboelectric tiltwing UAM vehicle concept.

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2021

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NASA is conducting investigations in Advanced Air Mobility (AAM) aircraft and operations. AAM missions are characterised by ranges below 300 nm, including rural and urban operations, passenger carrying as well as cargo delivery. Urban Air Mobility (UAM) is a subset of AAM and is the segment that is projected to have the most economic benefit and be the most difficult to develop. The NASA Revolutionary Vertical Lift Technology project is developing UAM VTOL aircraft designs that can be used to focus and guide research activities in support of aircraft development for emerging aviation markets. These NASA concept vehicles encompass relevant UAM features and technologies, including propulsion architectures, highly efficient yet quiet rotors, and aircraft aerodynamic performance and interactions. The configurations adopted are generic, intentionally different in appearance and design detail from prominent industry arrangements. Already these UAM concept aircraft have been used in numerous engineering investigations, including work on meeting safety requirements, achieving good handling qualities, and reducing noise below helicopter certification levels. Focusing on the concept vehicles, observations are made regarding the engineering of Advanced Air Mobility aircraft.

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Multi-point Design and Optimization of a Turboshaft Engine for Tiltwing Turboelectric VTOL Air Taxi

Cited by 4 publications

References 10 publications

Key performance indicators for turboelectric distributed propulsion

Key performance indicators for turboelectric distributed propulsion

Multidisciplinary Optimization of a Turboelectric Tiltwing Urban Air Mobility Aircraft

NASA concept vehicles and the engineering of advanced air mobility aircraft

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