Film Cooling in Aerospace Applications

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

Deadline for manuscript submissions: closed (31 May 2023) | Viewed by 4374

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

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Keywords

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

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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 2 | Viewed by 3422
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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