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Designs
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Advances in Aircraft Propulsion System Modelling, Design and Simulation
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Advances in Aircraft Propulsion System Modelling, Design and Simulation

A special issue of Designs (ISSN 2411-9660). This special issue belongs to the section "Vehicle Engineering Design".

Deadline for manuscript submissions: closed (29 February 2024) | Viewed by 9180

Special Issue Editors

Dr. Andrea Magrini

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Padova, Via Venezia 1, 35131 Padova, Italy
Interests: aircraft propulsion; turbomachinery; engine–airframe interaction; computational fluid dynamics; optimisation
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Ernesto Benini

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Padova, Via Venezia 1, 35131 Padova, Italy
Interests: CFD of flows in industrial and energy systems: optimal design methods; performance analysis in design and off-design conditions; full-annulus uRANS methods; aerothermodynamics of propulsion machines; CFD of supersonic and hypersonic flows
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

In the context of the urgent pursual of environmental sustainability, the civil aviation sector is committed to a transition towards cleaner and quieter operations, and is tackling a broad range of scientific, engineering, and technological challenges to reduce its emission footprint. Among these, the propulsive layout of aircrafts represents a fundamental focus for development. Therefore, during recent years, several engineering topics have emerged in this field. Considering the propulsive configuration, innovative designs have been proposed based on the concept of boundary layer ingesting (BLI), with fuselage-embedded engines or distributed electric propulsion. With these configurations, new challenges arise in terms of system performance modelling, powerplant integration, turbomachinery design and operation under non-uniform conditions. Propulsion system integration and coupled-design approaches are becoming increasingly important, especially during the coming decade with the application of turbofan engines, which tackle ultra-high bypass ratios where the air–frame interaction is enhanced. Findings from numerical methods need to be supported by wind tunnel experiments. These must be conceived to reproduce the powered-on operating conditions and provide sufficient accuracy and resolution to validate the innovative concepts.

The present Special Issue, “Advances in aircraft propulsion system modelling, design and simulation”, aims to collect the latest results and open issues related to the synthesis, analysis, and improvement of aircraft propulsion in a broad sense, from theoretical and analytical aspects to practical and experimental activities. Review or research articles covering, but not limited to, the following topics are welcomed: propulsive configurations for high efficiency and improved environmental impact; aero-propulsive performance analysis; propulsion system integration; engine–airframe interaction; methods for propulsor modelling, design and simulation; turbomachinery operability; aeroacoustics. Articles are expected to illustrate innovative techniques, novel findings or recent results that contribute to the advancement of engineering methods for successful modelling, design and analysis of aircraft propulsion systems.

Dr. Andrea Magrini
Prof. Dr. Ernesto Benini
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Designs is an international peer-reviewed open access semimonthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 1600 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • aeronautical engines
  • aircraft aerodynamics and propulsion systems
  • propulsion system design and integration
  • computational fluid dynamics (CFD) simulations
  • aerodynamic design and analysis
  • aero-propulsive performance calculation and optimisation
  • aircraft wind tunnel tests
  • off-design operation
  • inlet distortion
  • engine–airframe interaction
  • coupled-flow simulations
  • turbomachinery
  • optimisation
  • aeroacoustics

Published Papers (5 papers)

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Research

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16 pages, 3208 KiB  
Article
Aircraft Structural Design and Life-Cycle Assessment through Digital Twins
by Sérgio M. O. Tavares, João A. Ribeiro, Bruno A. Ribeiro and Paulo M. S. T. de Castro
Designs 2024, 8(2), 29; https://doi.org/10.3390/designs8020029 - 22 Mar 2024
Viewed by 1002
Abstract
Numerical modeling tools are essential in aircraft structural design, yet they face challenges in accurately reflecting real-world behavior due to factors like material properties scatter and manufacturing-induced deviations. This article addresses the potential impact of digital twins on overcoming these limitations and enhancing [...] Read more.
Numerical modeling tools are essential in aircraft structural design, yet they face challenges in accurately reflecting real-world behavior due to factors like material properties scatter and manufacturing-induced deviations. This article addresses the potential impact of digital twins on overcoming these limitations and enhancing model reliability through advanced updating techniques based on machine learning. Digital twins, which are virtual replicas of physical systems, offer a promising solution by integrating sensor data, operational inputs, and historical records. Machine learning techniques enable the calibration and validation of models, combining experimental inputs with simulations through continuous updating processes that refine digital twins, improving their accuracy in predicting structural behavior and performance throughout an aircraft’s life cycle. These refined models enable real-time monitoring and precise damage assessment, supporting decision making in diverse contexts. By integrating sensor data and updating techniques, digital twins contribute to improved design and maintenance operations by providing valuable insights into structural health, safety, and reliability. Ultimately, this approach leads to more efficient and safer aviation operations, demonstrating the potential of digital twins to revolutionize aircraft structural analysis and design. This article explores various advancements and methodologies applicable to structural assessment, leveraging machine learning tools. These include the utilization of physics-informed neural networks, which enable the handling of diverse uncertainties. Such approaches empower a more informed and adaptive strategy, contributing to the assurance of structural integrity and safety in aircraft structures throughout their operational life. Full article
(This article belongs to the Special Issue Advances in Aircraft Propulsion System Modelling, Design and Simulation)
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16 pages, 11511 KiB  
Article
Impeller Design and Performance Analysis of Aviation Fuel Pump Based on the Inverse Method
by Chenguang Ping, Jinguang Yang, Michele Ferlauto and Yang Zhao
Designs 2023, 7(3), 61; https://doi.org/10.3390/designs7030061 - 30 Apr 2023
Viewed by 1800
Abstract
Centrifugal pumps have a wide range of applications in the aviation field. The present work focuses on the optimal design of aviation fuel pump impellers by means of an inverse method. The fuel pump impeller is designed here by solving an inverse problem, [...] Read more.
Centrifugal pumps have a wide range of applications in the aviation field. The present work focuses on the optimal design of aviation fuel pump impellers by means of an inverse method. The fuel pump impeller is designed here by solving an inverse problem, in which the impeller geometry is found by imposing a target blade loading. As the inverse procedure is inviscid, an iterative process based on RANS is then applied to finally converge to a fully viscous solution. Three representative loading distributions have been investigated, and the final performances are evaluated by RANS computations. Since flow variables, rather than the blade geometry, are imposed on the target flow field, it is found that the impellers designed by way of the inverse method have high efficiency under the conditions without cavitation; among them, the pump impeller with a higher loading at the hub maintains a high efficiency for a wide range of flow conditions and also has better anti-cavitation performances under low inlet pressure conditions. Moreover, cavitation resistance can be improved by adjusting the loading distribution near the blade leading edge using the inverse design tool. Full article
(This article belongs to the Special Issue Advances in Aircraft Propulsion System Modelling, Design and Simulation)
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25 pages, 4192 KiB  
Article
Improved Local Scale Generic Cycle Model for Aerothermodynamic Simulations of Gas Turbine Engines for Propulsion
by Manuel de Jesús Gurrola Arrieta and Ruxandra Mihaela Botez
Designs 2022, 6(5), 91; https://doi.org/10.3390/designs6050091 - 03 Oct 2022
Cited by 4 | Viewed by 1971 | Correction
Abstract
A local scale Aerothermodynamic Generic Cycle Model (AGCM) is proposed. The AGCM accounts for several improvements not considered in similar models, such as compressor bleed extraction for aircraft Environmental Control System (ECS), parasitic shaft power extraction, and the enthalpy of the fuel entering [...] Read more.
A local scale Aerothermodynamic Generic Cycle Model (AGCM) is proposed. The AGCM accounts for several improvements not considered in similar models, such as compressor bleed extraction for aircraft Environmental Control System (ECS), parasitic shaft power extraction, and the enthalpy of the fuel entering the combustor. The AGCM is intended for steady-state Design Point (DP) and Off-Design (OD) performance analyses. The underlying physics is presented for the DP model. The turbomachinery component maps scaling and the system of nonlinear equations necessary to define the OD model are thoroughly discussed. The AGCM is compared with an equivalent model developed in the Numerical Propulsion System Simulation (NPSS). The comparisons were performed considering a DP envisioned to approximate a General Electric CF34-8C5B1 engine. The average errors found in these comparisons for the Specific Fuel Consumption (SFC) and net thrust were −0.111% and 0.193%, respectively. Finally, the predictions of the absolute levels of performance intended for the -8C5B1 engine are compared with empirical correlations derived from a comprehensive turbofan engine database. It was found that the predictions of the AGCM are in agreement with the empirical correlations; the errors found in SFC and net thrust at cruise flight condition were −0.43% and 2.06%, respectively. Full article
(This article belongs to the Special Issue Advances in Aircraft Propulsion System Modelling, Design and Simulation)
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Review

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73 pages, 35413 KiB  
Review
A Review of Novel and Non-Conventional Propulsion Integrations for Next-Generation Aircraft
by Karim Abu Salem, Giuseppe Palaia, Pedro D. Bravo-Mosquera and Alessandro A. Quarta
Designs 2024, 8(2), 20; https://doi.org/10.3390/designs8020020 - 20 Feb 2024
Viewed by 2178
Abstract
The aim of this review paper is to collect and discuss the most relevant and updated contributions in the literature regarding studies on new or non-conventional technologies for propulsion–airframe integration. Specifically, the focus is given to both evolutionary technologies, such as ultra-high bypass [...] Read more.
The aim of this review paper is to collect and discuss the most relevant and updated contributions in the literature regarding studies on new or non-conventional technologies for propulsion–airframe integration. Specifically, the focus is given to both evolutionary technologies, such as ultra-high bypass ratio turbofan engines, and breakthrough propulsive concepts, represented in this frame by boundary layer ingestion engines and distributed propulsion architectures. The discussion focuses mainly on the integration effects of these propulsion technologies, with the aim of defining performance interactions with the overall aircraft, in terms of aerodynamic, propulsive, operating and mission performance. Hence, this work aims to analyse these technologies from a general perspective, related to the effects they have on overall aircraft design and performance, primarily considering the fuel consumption as a main metric. Potential advantages but also possible drawbacks or detected showstoppers are proposed and discussed with the aim of providing as broad a framework as possible for the aircraft design development roadmap for these emerging propulsive technologies. Full article
(This article belongs to the Special Issue Advances in Aircraft Propulsion System Modelling, Design and Simulation)
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Other

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1 pages, 207 KiB  
Correction
Correction: Gurrola Arrieta, M.d.J.; Botez, R.M. Improved Local Scale Generic Cycle Model for Aerothermodynamic Simulations of Gas Turbine Engines for Propulsion. Designs 2022, 6, 91
by Manuel de Jesús Gurrola Arrieta and Ruxandra Mihaela Botez
Designs 2023, 7(6), 120; https://doi.org/10.3390/designs7060120 - 24 Oct 2023
Viewed by 900
Abstract
In the published paper [...] Full article
(This article belongs to the Special Issue Advances in Aircraft Propulsion System Modelling, Design and Simulation)
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