Modeling and Investigation of a Turboprop Hybrid Electric Propulsion System

Cameretti, Maria Cristina; Pizzo, A. Del; Noia, Luigi Pio Di; Ferrara, Michele; Pascarella, Ciro

doi:10.3390/aerospace5040123

Cited by 32 publications

(14 citation statements)

References 19 publications

(24 reference statements)

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“…While partially superconducting machines reached a TTW value of up to 21.6 Nm kg −1 which is comparable to non-superconducting machines, fully superconducting machines showed results beyond 75 Nm kg −1 . In combination with decreasing losses in the stator of fully superconducting machines when lowering the electric frequency, we suggest that this machine type might be particularly interesting to be studied for even lower speed direct drive applications, such as propellers or large fans [29]. We find also that the best power-to-weight ratios come with designs with comparatively low magnetic flux densities in the airgap in the range from 0.55 T to 0.9 T -values that could also be achieved with NdFeB magnets.…”

Section: Resultsmentioning

confidence: 99%

Topology Comparison of Superconducting AC Machines for Hybrid Electric Aircraft

Corduan

Boll

Bause

et al. 2020

IEEE Trans. Appl. Supercond.

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Electric machines with very power-to-weight ratios are inevitable for hybridelectric aircraft applications. One potential technology that is very promising to achieve the required power-to-weight ratio for short-range aircraft, are superconductors used for high current densities in the stator or high magnetic fields in the rotor. In this paper, we present an indepth analysis of the potential for fully and partially superconducting electric machines that is based on an analytical approach taking into account all relevant physical domains such as electromagnetics, superconducting properties, thermal behavior as well as structural mechanics. For the requirements of the motors in the NASA N3-X concept aircraft, we find that fully superconducting machines could achieve 3.5 times higher power-to-weight ratio than partially superconducting machines. Furthermore, our model can be used to calculate the relevant KPIs such as mass, efficiency and cryogenic cooling requirements for any other machine design.

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Section: Resultsmentioning

confidence: 99%

Topology Comparison of Superconducting AC Machines for Hybrid Electric Aircraft

Corduan

Boll

Bause

et al. 2020

IEEE Trans. Appl. Supercond.

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“…The authors of [32] consider the optimisation of the steady-state operating modes of a turboshaft and electric engine of a hybrid power plant, but do not take into account the dynamic processes associated with loading and unloading the power turbine. A model of a turboshaft engine based on the empirical controller characteristics is presented in [33], where the calculated dynamic parameters have a significant (up to 8%) error.…”

Section: Literature Reviewmentioning

confidence: 99%

Self-Oscillations of The Free Turbine Speed in Testing Turboshaft Engine with Hydraulic Dynamometer

et al. 2021

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Self-oscillations are one of the common problems in the complex automatic system, that can occur due to the features of the workflow and the design of the governor. The development of digital control systems has made it possible to damp self-oscillations by applying complex control laws. However, for hydromechanical systems, such way is unacceptable due to the design complexity and the governor cost. The objective of this work is to determine the parameters of the hydromechanical free turbine speed controller, ensuring the absence of self-oscillations during ground tests of the turboshaft engine with a hydraulic dynamometer. The TV3-117VM engine (Ukraine) with the NR-3VM regulator pump (Ukraine) was selected as the object of the study. However, self-oscillations can also occur in any modifications of the TV3-117 engine with any NR-3 regulator pump. The results of the research may be of interest to engineers and scientists who investigate the dynamics of automatic control systems for similar engines. The paper analyses the nonlinear features of the empirical characteristics of the FTSC leading to self-oscillations of the engine speed. The authors propose the mathematical model of the automatic control system dynamics, which takes into account all the features of the engine and regulator pump. It is shown that the load characteristics of the water brake and the helicopter main rotor can differ significantly. Research of the dynamic characteristics of the TV3-117VM engine was carried out. The analysis showed a good agreement between the calculation results and the field test results, and made it possible to determine the parameters of the controller, which lead to self-oscillations during test. Two cases are considered. The first case includes ground tests of the engine with a water brake; the second case—flight tests of the engine as part of the helicopter’s power plant. The data obtained make it possible to develop recommendations for adjusting the hydromechanical governor without testing it on the engine.

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“…5 Additionally, estimating the emission produced by the propulsion system is one of the most important parts of their modeling process. 6,7 All these aside, the factor that influences the aircraft propulsion in all aspects is its ability to adapt to environmental elements and user demand. Considering the working envelope of an aircraft, its propulsion system performance is always influenced by its working environment that clears the importance of being context-aware for this system.…”

Section: Introductionmentioning

confidence: 99%

“…5 Additionally, estimating the emission produced by the propulsion system is one of the most important parts of their modeling process. 6,7…”

Section: Introductionmentioning

confidence: 99%

A novel hybrid aircraft propulsion based on the DEA compressor—part B: Performance

Aryana¹

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This two-parts article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part B of this article explains the performance sizing of the propulsion set designed in part A. Evaluating the performance of the propulsion, computer programs are written for all major components of the both master engine and ancillary thruster. The intake, compressor, detonation process, diffusers, axial turbine, and exit nozzle are modeled under certain flight conditions, and their performances are revealed and analyzed. The flight conditions are considered from the static condition at the sea level up to flight Mach number 5 at an altitude of 20,000 m. The performance of the propulsion set is also compared with some aircraft propulsions modeled by similar studies in all important aspects.

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Modeling and Investigation of a Turboprop Hybrid Electric Propulsion System

Cited by 32 publications

References 19 publications

Topology Comparison of Superconducting AC Machines for Hybrid Electric Aircraft

Topology Comparison of Superconducting AC Machines for Hybrid Electric Aircraft

Self-Oscillations of The Free Turbine Speed in Testing Turboshaft Engine with Hydraulic Dynamometer

A novel hybrid aircraft propulsion based on the DEA compressor—part B: Performance

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