Special Issue "Advances in Aerothermal Engineering"

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

Deadline for manuscript submissions: 31 August 2021.

Special Issue Editor

Dr. Hao Xia
E-Mail Website
Guest Editor
Senior Lecturer in Gas Turbine Aerothermal Engineering, National Centre for Combustion & Aerothermal Technology, Department of Aeronautical & Automotive Engineering, Loughborough University, Loughborough, United Kingdom.
Interests: computational aerodynamics; large-eddy simulation; computational aeroacoustics; numerical heat transfer; high-end computing

Special Issue Information

Dear Colleagues,

Aerothermal engineering is at the heart of aerospace propulsion systems. Its technological advances in fluid mechanics, thermodynamics, acoustics, etc. have been pushing design and manufacturing boundaries for more thrust and better efficiency. Challenges which are greater than ever are now the focal point of developing future propulsion systems as environmental concerns, such as ambitious emission and noise reductions, and relentless pressure on shortening design and manufacturing cycles, requiring novel solutions and new paradigms.

This Special Issue will be a collection of contributions that reflect the latest efforts in the research areas of aerothermal engineering with potential applications (or directly linked) to an aerospace propulsion system. Contributions can be original research articles as well as reviews, which will potentially be in (but not limited to) one or more research fields ranging from aerothermal aspects of gas turbine aeroengines to heat transfer (and cooling) problems of propulsion systems to mass transfer within multiphase flows and to aerothermal flow induced noise and vibration problems.

Dr. Hao Xia
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 papers will be 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 1400 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

  • turbomachinery
  • heat transfer
  • computational fluid dynamics
  • multiphase flow
  • aeroacoustics
  • fluid–structure interaction

Published Papers (2 papers)

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Research

Open AccessArticle
Effect of Two-Head Flared Hole on Film Cooling Performance over a Flat Plate
Aerospace 2021, 8(5), 128; https://doi.org/10.3390/aerospace8050128 - 04 May 2021
Viewed by 314
Abstract
Film cooling is commonly utilized in turbine blades to decrease the temperature of the air stream from the combustion chamber that contacts directly with the blades. The shape of a cylindrical hole (CH) with the geometrical variations at inlet and outlet ports was [...] Read more.
Film cooling is commonly utilized in turbine blades to decrease the temperature of the air stream from the combustion chamber that contacts directly with the blades. The shape of a cylindrical hole (CH) with the geometrical variations at inlet and outlet ports was examined using the 3D Reynolds-averaged Navier–Stokes equations (RANS) with a shear stress transport (SST k − ω) turbulence model to study the effect of the two-head flared hole on film cooling effectiveness (FE) at high accuracy with a small y+ value. To assess the effect of the changes, each geometry of the hole was changed one after another while the other parameters were kept invariable at the test value (cylindrical hole). The numerical laterally averaged film cooling effectiveness (ηl) of the CH case was validated and compared to the experimental data. The simulation results with the two-head flared hole indicated that most of these shape changes increase the FE as compared to the CH case. In particular, the maximum spatially averaged film cooling effectiveness (ηs) with hole shape expanded along the flow direction at the outlet port reached 60.787% in comparison to the CH case. Full article
(This article belongs to the Special Issue Advances in Aerothermal Engineering)
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Open AccessArticle
Investigation of the Film-Cooling Performance of 2.5D Braided Ceramic Matrix Composite Plates with Preformed Hole
Aerospace 2021, 8(4), 116; https://doi.org/10.3390/aerospace8040116 - 19 Apr 2021
Viewed by 282
Abstract
The film-cooling performance of a 2.5D braided ceramic matrix composite (CMC) plate with preformed holes was numerically studied. Four numerical models containing braided structures were established: one model with film-cooling holes preformed through fiber extrusion deformation (EP-Hole), one model with film-cooling holes directly [...] Read more.
The film-cooling performance of a 2.5D braided ceramic matrix composite (CMC) plate with preformed holes was numerically studied. Four numerical models containing braided structures were established: one model with film-cooling holes preformed through fiber extrusion deformation (EP-Hole), one model with film-cooling holes directly woven through fibers (WP-Hole), and two models with directly drilled holes (DP-Hole1,2). Besides, the influence of the ratio between the equivalent thermal conductivities on the axial and radial directions of fiber Kr was investigated. The results show that the preformed holes have better performance in controlling the thermal gradient with the increase of Kr. The maximum thermal gradient around the DP-Hole is significantly higher than that of the WP-Hole and EP-Hole, and the maximum relative variation reaches 123.3%. With Kr increasing from 3.32 to 13.05, the overall cooling effectiveness on the hot-side wall decreases for all models, by about 10%. Compared with the traditional drill method, the new preformed film-cooling hole studied in this paper can reduce the temperature and the thermal gradient in the region around the holes. Full article
(This article belongs to the Special Issue Advances in Aerothermal Engineering)
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