Film Cooling in Aerospace Applications

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

Deadline for manuscript submissions: closed (31 May 2023) | Viewed by 2922

Special Issue Editor


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Guest Editor
Gas Turbine and Transmissions Research Centre, Nottingham University, Nottingham NG7 2TU, UK
Interests: aero-engines; film cooling; turbomachinery; computational and experimental heat transfer

Special Issue Information

Dear Colleagues,

I extend a sincere invitation to all colleagues who wish to submit research papers to this Special Issue of Aerospace on “Film Cooling in Aerospace Applications”. Although the field is film cooling for aerospace applications, fluid flow and heat transfer analysis in fundamental or applied science fields, combined film and impingement cooling and transpiration cooling, cooling requirements for hydrogen or ammonia-based propulsion systems, or hybrid electric propulsion may also be included. The primary selection criteria for paper acceptance are academic excellence, industrial relevance, originality, and the novelty of applications, methods, or fundamental findings. Research can be experimental, theoretical, or computational, and their combination is equally acceptable. The purpose of this Special Issue of Aerospace is to share new ideas and research results in the aerospace industry that are related to cooling technologies of the key components exposed to extremely high temperatures. Therefore, submissions from other interdisciplinary fields, including energy, mechanical, and chemical engineering and new materials sciences, are possible. Of course, research papers on fluid flow and heat transfer in the field of the Fourth Industrial Revolution are also welcome.

We believe it would be very helpful for the community to exchange ideas on novel and efficient cooling techniques in the challenging aerospace sector, which is striving to achieve a net-zero target.

Dr. Kuldeep Singh
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

  • film cooling
  • aero-engines
  • gas turbine
  • rocket
  • combustion chambers
  • turbine blades
  • nozzles

Published Papers (1 paper)

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Research

18 pages, 8428 KiB  
Article
A Coupled Heat Transfer Calculation Strategy for Composite Cooling Liquid Rocket Engine
by Bo Xu, Bing Chen, Jian Peng, Wenyuan Zhou and Xu Xu
Aerospace 2023, 10(5), 473; https://doi.org/10.3390/aerospace10050473 - 17 May 2023
Cited by 1 | Viewed by 2199
Abstract
To better understand the characteristics of coupled heat transfer in liquid rocket engines, a calculation scheme is proposed in this paper. This scheme can simulate the coupled heat transfer processes, including combustion and flow in the thrust chamber, radiation heat transfer, heat conduction [...] Read more.
To better understand the characteristics of coupled heat transfer in liquid rocket engines, a calculation scheme is proposed in this paper. This scheme can simulate the coupled heat transfer processes, including combustion and flow in the thrust chamber, radiation heat transfer, heat conduction in the wall, heat transfer of coolant flow in the cooling channel, and gas film cooling in the thrust chamber wall. The numerical method used in each physical area, the data transfer method between each computing module, the strategy of data transfer on the coupling interface, the calculation process, and the convergence criterion are all introduced in detail. The calculation scheme was verified by analyzing a water-cooled nozzle. Then, the coupled heat transfer calculation was carried out for a liquid rocket engine using a propellant composed of unsymmetrical dimethylhydrazine and dinitrogen tetroxide. Two working conditions were analyzed: whether the gas film cooling was performed or not. The results showed that the algorithm successfully indicated the protective effect of the gas film on the wall surface, and the calculation results were reasonable. It played a guiding role for the coupled heat transfer of the liquid rocket engine using a composite cooling method. Full article
(This article belongs to the Special Issue Film Cooling in Aerospace Applications)
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