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Aerospace
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Advances in Aerothermal Engineering
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Advances in Aerothermal Engineering

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (31 December 2021) | Viewed by 12973

Special Issue Editor

Dr. Hao Xia

E-Mail Website
Guest Editor
Department of Aeronautical & Automotive Engineering, Loughborough University, Loughborough LE11 3TU, UK
Interests: eddy-resolving flow simulation; flow-induced instability and noise; heat transfer; external and internal aerodynamics; high-performance computing; machine learning for fluids

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 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.

Keywords

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

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Further information on MDPI's Special Issue polices can be found here.

Published Papers (4 papers)

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Research

14 pages, 5821 KiB  
Article
Entropy Generation of Secondary Flow in a Turning Passage with Different Boundary Layer Characteristics
by Yueyun Xi, Xu Peng, Hao Xia, Zhengzhong Sun and Qiang Zhang
Aerospace 2022, 9(10), 539; https://doi.org/10.3390/aerospace9100539 - 23 Sep 2022
Viewed by 1789
Abstract
The development of secondary flow along a curved channel is a fundamental flow phenomenon occurring in a wide range of engineering applications, including turbomachinery, aerospace, heating, ventilation, air conditioning, etc. The underlying flow physics about end-wall secondary flows has been well-documented in the [...] Read more.
The development of secondary flow along a curved channel is a fundamental flow phenomenon occurring in a wide range of engineering applications, including turbomachinery, aerospace, heating, ventilation, air conditioning, etc. The underlying flow physics about end-wall secondary flows has been well-documented in the open literature, while the interaction between a secondary flow and a side-wall boundary layer, which is critical to the aerothermal performance of a side-wall surface, has not been comprehensively studied. In this study, the entropy generation of secondary flow and the interaction between an end-wall passage vortex and a side-wall boundary layer were numerically investigated by Reynolds-averaged Navier–Stokes (RANS) CFD for a 90° curved channel. The transportation effect of secondary flow and the generation mechanism of an induced vortex pair on the side wall is reported. It was also found that the growth of the secondary flow can be suppressed due to the displacement effect of the side-wall boundary layer. Furthermore, it was found that the interaction between a secondary flow and a side-wall boundary layer provides a suppression effect on side-wall boundary layer separation. Full article
(This article belongs to the Special Issue Advances in Aerothermal Engineering)
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14 pages, 7057 KiB  
Article
Temperature and Pressure Dynamic Control for the Aircraft Engine Bleed Air Simulation Test Using the LPID Controller
by Yonggui Zheng, Meng Liu, Hao Wu and Jun Wang
Aerospace 2021, 8(12), 367; https://doi.org/10.3390/aerospace8120367 - 27 Nov 2021
Cited by 5 | Viewed by 2995
Abstract
The aircraft engine bleed air simulation thermodynamic laboratory simulation parameters include the bleed air pressure and temperature. However, existing laboratories cannot carry out the dynamic test of the engine bleed air simulation. In the engine bleed air simulation dynamic test, the temperature control [...] Read more.
The aircraft engine bleed air simulation thermodynamic laboratory simulation parameters include the bleed air pressure and temperature. However, existing laboratories cannot carry out the dynamic test of the engine bleed air simulation. In the engine bleed air simulation dynamic test, the temperature control has the characteristics of strong coupling and nonlinear and large inertia. The conventional control strategy cannot solve the contradictions of the response speed and stability of the system. Moreover, the dynamic control of the pressure and temperature involve strong coupling. That often leads to the failure of control decisions. Therefore, there is still no relevant report on the laboratory equipment used for the engine dynamic bleed air simulation. According to the above problem, this study adopted heat exchangers for indirect heating to reduce the coupling of dynamic control between temperature and pressure. Specifically, to take into account the rapid response and stability of the system, this study used the lookup table-based PID (LPID) controller to control the temperature and pressure of the bleed air simulation test. The dynamic test errors were within 10%, and the steady-state accuracies were within ±2%. The simulation software results and the engine bleed air simulation test results showed that temperature and pressure control systems based on the LPID controller have advantages: high control precision, a low overshoot amount, a fast response, and a high stability. Full article
(This article belongs to the Special Issue Advances in Aerothermal Engineering)
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18 pages, 8857 KiB  
Article
Effect of Two-Head Flared Hole on Film Cooling Performance over a Flat Plate
by Xuan-Truong Le, Duc-Anh Nguyen, Cong-Truong Dinh and Quang-Hai Nguyen
Aerospace 2021, 8(5), 128; https://doi.org/10.3390/aerospace8050128 - 4 May 2021
Cited by 3 | Viewed by 3268
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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22 pages, 8022 KiB  
Article
Investigation of the Film-Cooling Performance of 2.5D Braided Ceramic Matrix Composite Plates with Preformed Hole
by Chenwei Zhao, Zecan Tu and Junkui Mao
Aerospace 2021, 8(4), 116; https://doi.org/10.3390/aerospace8040116 - 19 Apr 2021
Cited by 6 | Viewed by 2655
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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