Review on ducted fans for compound rotorcraft

Zhang, T.; Barakos, George N.

doi:10.1017/aer.2019.164

Cited by 47 publications

(21 citation statements)

References 61 publications

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“…The main functions of the ducted propeller system are to convert mechanical shaft power into thrust and to protect the PCS, the aircraft and the passengers from high-energy debris by containment in case of burst as stated by Zhang and Barakos (2020). The scope of the system includes the propeller and its control.…”

Section: Ducted Propeller Systemmentioning

confidence: 99%

Functional Hazard Assessment of the Propulsion Control System Designed for a Small Hybrid Electric Aircraft

Motte¹,

Niehuis²,

Fischer³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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This paper presents the Functional Hazard Assessment (FHA) of a Propulsion Control System (PCS) designed for a hybrid electric aircraft considering the Failure Conditions (FCs) that are novel due to the electrification of the propulsion system. It will be worked out whether these FCs are covered by current certification regulations. After defining the functionality, the FCs for a hybrid electric propulsion system are established, based on current standards and also the Working Group 113 (WG-113) recommendations. The FHA and Preliminary System Safety Assessment (PSSA) approaches are used to evaluate and improve the architecture of the control system. The system functions on propulsion level are defined and allocated to different subsystems. Their FCs and effects are then established. Based on the applicable standards and recommendations of WG-113, these effects are classified, and the Safety Requirements (SRs) are then defined. The FHA results include 23 FCs related to the hybrid system, some of which are not addressed by the current regulatory framework. In summary, this paper outlines how electrified powertrain systems will affect new propulsion architectures from a safety perspective and how the current regulatory framework and the work of the WG-113 could be improved by addressing new FCs resulting from the FHA. By suggesting SRs derived from the FHA, this paper also discusses what system/safety activities need to be undertaken in order to design a propulsion architecture that is compliant with the applicable certification documents.

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Section: Ducted Propeller Systemmentioning

confidence: 99%

Functional Hazard Assessment of the Propulsion Control System Designed for a Small Hybrid Electric Aircraft

Motte¹,

Niehuis²,

Fischer³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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“…A comprehensive overview of low-speed axial flow fan design methods and their state-of-the-art is given by Castegnaro [11] and Zhang and Barakos [46]. A widely used design tool is the Ducted Fan Design Code (DFDC) by Youngren, Drela, and Sanders [45].…”

Section: Introductionmentioning

confidence: 99%

Ducted fans for hybrid electric propulsion of small aircraft

et al. 2022

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This paper presents a method for modeling ducted fan propulsion systems for hybrid-electrically driven small aircraft based on mean line flow analysis methods. Studies of the essential design parameters provide the basis for a discussion of potential advantages when compared to free propellers, as well as possible new fields of application for the ducted fan. A two-seater aircraft, equipped with two ducted fans powered by a combustion engine and additionally by a parallel hybrid electric start-boost drive, is used as a reference application case. The fan performance characteristics are described with the aid of aero mean line flow analysis methods and semi-empirical loss correlations. Physics-based methods are applied to assess the nacelle drag and noise emissions. The combustion engine and electric motor performance are described using maps. The ducted fan design variables are investigated to identify the main trade-offs and favorable designs for the target aircraft mission, with special attention to noise. The results show that the performance of fixed pitch fans benefits strongly from hybridization. Ducted fans can also operate considerably more quietly than is required by current certification standards. The physics-based design method presented here can be used for conceptual design and performance prediction of ducted fan propulsion systems, which may be especially interesting if low noise emissions are required.

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“…Zhang summarizes all the published work on ducted propellers (Zhang and Barakos, 2020). Experiments, theoretical studies, lower-order computational models and high fidelity CFD studies and simulation are mentioned.…”

Section: Introductionmentioning

confidence: 99%

Aero-propulsive interaction model for conceptual distributed propulsion aircraft design

Awad

Stumpf

2022

AEAT

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Purpose This research aims to present an aero-propulsive interaction model applied to conceptual aircraft design with distributed electric propulsion (DeP). The developed model includes a series of electric ducted fans integrated into the wing upper trailing edge, taking into account the effect of boundary layer ingestion (BLI). The developed model aims to estimate the aerodynamic performance of the wing with DeP using an accurate low-order computational model, which can be easily used in the overall aircraft design's optimization process. Design/methodology/approach First, the ducted fan aerodynamic performance is investigated using a low-order computational model over a range of angle of attack required for conventional flight based on ducted fan design code program and analytical models. Subsequently, the aero-propulsive coupling with the wing is introduced. The DeP location chordwise is placed at the wing's trailing edge to have the full benefits of the BLI. After that, the propulsion integration process is introduced. The nacelle design's primary function is to minimize the losses due to distortion. Finally, the aerodynamic forces of the overall configuration are estimated based on Athena Vortex Lattice program and the developed ducted fan model. Findings The ducted fan model is validated with experimental measurements from the literature. Subsequently, the overall model, the wing with DeP, is validated with experimental measurements and computational fluid dynamics, both from the literature. The results reveal that the currently developed model successfully estimates the aerodynamic performance of DeP located at the wing trailing edge. Originality/value The developed model's value is to capture the aero-propulsive coupling accurately and fast enough to execute multiple times in the overall aircraft design's optimization loop without increasing runtime substantially.

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Review on ducted fans for compound rotorcraft

Cited by 47 publications

References 61 publications

Functional Hazard Assessment of the Propulsion Control System Designed for a Small Hybrid Electric Aircraft

Functional Hazard Assessment of the Propulsion Control System Designed for a Small Hybrid Electric Aircraft

Ducted fans for hybrid electric propulsion of small aircraft

Aero-propulsive interaction model for conceptual distributed propulsion aircraft design

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