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Aeroengine
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Aeroengine

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: closed (31 July 2018) | Viewed by 41749

Special Issue Editor

Prof. Dr. Kyros Yakinthos

E-Mail Website
Guest Editor
Department of Mechanical Engineering, Laboratory of Fluid Mechanics and Turbomachinery, Aristotle University of Thessaloniki, 541 24 Thessaloniki, Greece
Interests: computational fluid dynamics; turbulence modeling; transitional boundary layers; active flow control on wings; waste heat management technologies for aeroengines; innovative aeroengine thermodynamic cycles; UAV design and development
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

This Special Issue on “Aeroengine” aims to provide an overview of the state-of-the-art and the main challenges in the field of aeroengines technology. This Special Issue will include original and review research manuscripts associated with the main innovation and technological advancements in science and technology targeting (but not limited) the efficient operation and optimization of aeroengines, with the use of numerical/computational analysis and/or experimental methods.

Particular emphasis will be provided on original manuscripts targeting the achievement of ACARE (Advisory Council for Aviation Research and innovation in Europe) year 2050 targets regarding fuel consumption and pollutant emissions reduction and the fulfillment of the SRIA (Strategic Research and Innovation Agenda) key challenges towards the design of efficient, safe and environmentally friendly aeroengines. Last but not least, the Special Issue “Aeroengine” strongly encourages the submission of original manuscripts addressing other challenging topics such as the ones related with hypersonic propulsion concepts and configurations for future aeroengine applications.

The context of the Special Issue welcomes full research articles and review manuscripts that will make considerable contribution in the following topics:

  • Innovative cycles and engine core concepts
  • Aeroengine noise
  • Intake aerodynamics
  • Cooling technologies
  • Turbine and compressor blade aerodynamics
  • Measurement techniques and test rigs for aeroengines
  • Combustor chambers design and technologies for aeroengines
  • Specific fuel consumption reduction technologies      
  • Waste heat exploitation and management
  • Aeroengine performance
  • On board diagnostics and control
  • Hypersonic propulsion
  • Aeroengines for UAV applications
  • Aeroengine materials and structures
  • Aeroengine components design and optimization
  • Alternative fuels for aeroengines
  • Aeroengine integration to future aircraft concepts

Prof. Dr. Kyros Yakinthos
Guest Editor

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. Aerospace is an international peer-reviewed open access monthly 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 2400 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.

Published Papers (4 papers)

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Research

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19 pages, 6543 KiB  
Article
Performance Assessment of Reynolds Stress and Eddy Viscosity Models on a Transitional DCA Compressor Blade
by Zinon Vlahostergios
Aerospace 2018, 5(4), 102; https://doi.org/10.3390/aerospace5040102 - 30 Sep 2018
Cited by 10 | Viewed by 6094
Abstract
In the current work a detailed investigation and a performance assessment of two eddy viscosity and two Reynolds stress turbulence models for modelling the transitional flow on a double circular arc (DCA) compressor blade is presented. The investigation is focused on the comparison [...] Read more.
In the current work a detailed investigation and a performance assessment of two eddy viscosity and two Reynolds stress turbulence models for modelling the transitional flow on a double circular arc (DCA) compressor blade is presented. The investigation is focused on the comparison of the obtained computational results with available experimental data for a specific DCA compressor blade cascade which can be found in the European Research Community on Flow, Turbulence and Combustion (ERCOFTAC) experimental database. The examined flow field is very challenging for the performance assessment of the turbulence models. The blade inlet angle departs +5° from the compressor blade design conditions resulting in a complex flow field having large regions of boundary layer transition both on the suction and pressure sides of the blade with the presence of an unsteady wake. The presented results include velocity and turbulence intensity distributions along the pressure, the suction sides, and the wake region of the blade. From the comparison with the available experimental data, it is evident that in order to accurately compute such complex velocity and turbulence fields that are met in aero engine components (compressors and turbines), it is obligatory to use more advanced turbulence models with the Unsteady Reynolds Averaged Navier Stokes Equations (URANS) adoption, or other simulation and hybrid methodologies which require unsteady calculations. Full article
(This article belongs to the Special Issue Aeroengine)
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27 pages, 39998 KiB  
Article
Conceptual Advanced Transport Aircraft Design Configuration for Sustained Hypersonic Flight
by Can Alkaya, Ashish Alex Sam and Apostolos Pesyridis
Aerospace 2018, 5(3), 91; https://doi.org/10.3390/aerospace5030091 - 01 Sep 2018
Cited by 9 | Viewed by 12787
Abstract
The conceptual aircraft design and its integration with a combined cycle engine for hypersonic cruise at Mach 8 is documented in this paper. The paper describes the process taken to develop a hypersonic aircraft from a conceptual approach. The discussion also includes the [...] Read more.
The conceptual aircraft design and its integration with a combined cycle engine for hypersonic cruise at Mach 8 is documented in this paper. The paper describes the process taken to develop a hypersonic aircraft from a conceptual approach. The discussion also includes the design and CFD analysis of the integrated combined cycle engine. A final conceptual hypersonic transport aircraft with an integrated combined cycle engine was achieved through this study. According to the analysis carried out, the aircraft is able to take-off and land at the airports it is intended to be used and will be able to generate enough thrust to sustain hypersonic cruise at an altitude of 30 km. Full article
(This article belongs to the Special Issue Aeroengine)
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26 pages, 11767 KiB  
Article
Experimental and Numerical Investigation of the Outer Ring Cooling Concept in a Hybrid and in an All-Steel Ball Bearing Used in Aero-Engines by the Introduction of a Helical Duct
by Michael Flouros, Peter Gloeckner, Markus Hirschmann, Matthias Martin, Francois Cottier and Dimitra Papailia
Aerospace 2018, 5(1), 23; https://doi.org/10.3390/aerospace5010023 - 28 Feb 2018
Cited by 8 | Viewed by 10415
Abstract
Rolling element bearings for aero engine applications have to withstand very challenging operating conditions because of the high thermal impact due to elevated rotational speeds and loads. The high rate of heat generation in the bearing has to be sustained by the materials, [...] Read more.
Rolling element bearings for aero engine applications have to withstand very challenging operating conditions because of the high thermal impact due to elevated rotational speeds and loads. The high rate of heat generation in the bearing has to be sustained by the materials, and in the absence of lubrication these will fail within seconds. For this reason, aero engine bearings have to be lubricated and cooled by a continuous oil stream. When the oil has reached the outer ring it has already been heated up, thus its capability to remove extra heat from the outer ring is considerably reduced. Increasing the mass flow of oil to the bearing is not a solution since excess oil quantity would cause high parasitic losses (churning) in the bearing chamber and also increase the demands in the oil system for oil storage, scavenging, cooling, hardware weight, etc. A method has been developed for actively cooling the outer ring of the bearing. The idea behind the outer ring cooling concept was adopted from fins that are used for cooling electronic devices. A spiral groove engraved in the outer ring material of the bearing would function as a fin body with oil instead of air as the cooling medium. The method was first evaluated in an all steel ball bearing and the results were a 50% reduction in the lubricating oil flow with an additional reduction in heat generation by more than 25%. It was then applied on a Hybrid ball bearing of the same size and the former results were reconfirmed. Hybrid bearings are a combination of steel made parts, like the outer ring, the inner ring, and the cage and of ceramic rolling elements. This paper describes the work done to-date as a follow up of the work described in, and demonstrates the potential of the outer ring cooling for a bearing. Friction loss coefficient, Nusselt number, and efficiency correlations have been developed on the basis of the test results and have been compared to correlations from other authors. Computational Fluid Dynamics (CFD) analysis with ANSYS CFX has been used to verify test results and also for parametric studies. Full article
(This article belongs to the Special Issue Aeroengine)
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Review

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17 pages, 23159 KiB  
Review
Hybrid Propulsion Systems for Remotely Piloted Aircraft Systems
by Mithun Abdul Sathar Eqbal, Nuwantha Fernando, Matthew Marino and Graham Wild
Aerospace 2018, 5(2), 34; https://doi.org/10.3390/aerospace5020034 - 29 Mar 2018
Cited by 24 | Viewed by 11065
Abstract
The development of more efficient propulsion systems for aerospace vehicles is essential to achieve key objectives. These objectives are to increase efficiency while reducing the amount of carbon-based emissions. Hybrid electric propulsion (HEP) is an ideal means to maintain the energy density of [...] Read more.
The development of more efficient propulsion systems for aerospace vehicles is essential to achieve key objectives. These objectives are to increase efficiency while reducing the amount of carbon-based emissions. Hybrid electric propulsion (HEP) is an ideal means to maintain the energy density of hydrocarbon-based fuels and utilize energy-efficient electric machines. A system that integrates different propulsion systems into a single system, with one being electric, is termed an HEP system. HEP systems have been studied previously and introduced into Land, Water, and Aerial Vehicles. This work presents research into the use of HEP systems in Remotely Piloted Aircraft Systems (RPAS). The systems discussed in this paper are Internal Combustion Engine (ICE)–Electric Hybrid systems, ICE–Photovoltaic (PV) Hybrid systems, and Fuel-Cell Hybrid systems. The improved performance characteristics in terms of fuel consumption and endurance are discussed. Full article
(This article belongs to the Special Issue Aeroengine)
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