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Thermal Design, Thermodynamic Analysis, and Optimization of Aero-Engines and Gas Turbines—2nd Edition

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "J: Thermal Management".

Deadline for manuscript submissions: 20 April 2026 | Viewed by 704

Special Issue Editors

School of Mechanical Engineering, Xi'an Jiaotong University, Xi'an 710049, China
Interests: advanced cooling technology for turbine blades; optimization design of cooling structure; machine learning in cooling design; equipment thermal design
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Guest Editor
School of Mechanical Engineering, Xi'an Jiaotong University, Xi'an 710049, China
Interests: artificial neural networks; inverse methods; computational fluid dynamics; numerical optimization; engineering, applied and computational mathematics
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

With the increasing operating temperatures of aero-engines and gas turbines, the cooling of high-temperature components has become a significant challenge. The development of reliable and efficient cooling structures is therefore essential to ensure the reliable operation of these systems. Traditional cooling methods may not be suitable for the new generation of aero-engines and gas turbines, as they may not provide the required cooling efficiency under extreme operating conditions. As a result, there is a need for novel cooling structures with enhanced cooling capabilities as well as cooling design methods with high efficiency and accuracy.

Building upon the success of the first edition, the second edition of this Special Issue continues to bring together original research and review articles discussing recent advances in thermal design, thermodynamic analysis, and optimization of aero-engines and gas turbines.

The topics of interest for publication include, but are not limited to, the following:

  • Overall thermal design and analysis of hot-temperature components such as blades and combustors;
  • Thermal design and analysis of unit cooling structures;
  • High-efficiency and high-precision thermal design methods;
  • Enhancement of cooling data;
  • Machine learning modeling of cooling performance;
  • Proposal and optimization of new cooling structures.

Dr. Lei Xi
Dr. Denglong Ma
Guest Editors

Manuscript Submission Information

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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. Energies is an international peer-reviewed open access semimonthly 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 2600 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

  • high-temperature components
  • thermal design
  • thermodynamic analysis
  • novel cooling structure
  • high-performance heat-transfer structure
  • machine learning
  • data enhancement
  • performance prediction
  • structural optimization

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Related Special Issue

Published Papers (2 papers)

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Research

17 pages, 3888 KB  
Article
Laser-Induced Phosphorescence Thermometry for Dynamic Temperature Measurement of an Effusion-Cooled Aero-Engine Model Combustor Liner Under Wide-Range Swirling Premixed Flames
by Yu Huang, Siyu Liu, Xiaoqi Wang, Tingjie Zhao, Wubin Weng, Zhihua Wang, Yong He and Zhihua Wang
Energies 2026, 19(3), 805; https://doi.org/10.3390/en19030805 - 3 Feb 2026
Abstract
The liner temperature distribution of an aero-engine combustor is a critical parameter for evaluating its cooling effectiveness. It provides essential guidance for designing the combustor cooling flow field, assessing combustion performance, identifying critical regions, and predicting service life. However, current research on surface [...] Read more.
The liner temperature distribution of an aero-engine combustor is a critical parameter for evaluating its cooling effectiveness. It provides essential guidance for designing the combustor cooling flow field, assessing combustion performance, identifying critical regions, and predicting service life. However, current research on surface temperature field measurements in real or model aero-engine combustors remains limited. Existing studies focus primarily on the liner temperature measurement under near-steady-state conditions, with less attention to its dynamic changes. This study employs Laser-Induced Phosphorescence (LIP) thermometry to measure the effusion-cooled liner temperature field of an aero-engine model combustor under various CH4/Air swirling premixed flame conditions and varying blowing ratios. Based on the geometric characteristics of the effusion-cooled liner, an optimization method for matching phosphorescence images of different wavelengths is proposed. This enhances the applicability of phosphorescence intensity ratio-based LIP thermometry in high-vibration environments. The study specifically focuses on the dynamic response of LIP thermometry for monitoring combustor liner temperature. The instantaneous effects of blowing ratio variations on liner temperature rise rates were investigated. Additionally, the influence mechanisms of a broad range of combustion conditions and the blowing ratios on the combustor liner temperature distribution and cooling effectiveness were examined. These findings provide theoretical and technical support for cooling design and dynamic liner temperature field measurement in real aero-engine combustors. Full article
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24 pages, 12417 KB  
Article
Conjugate Heat Transfer and Thermal Stress Analysis of a Gas Turbine Double-Wall Cooling System with a Diamond-Type TPMS Effusion
by Kirttayoth Yeranee, Chao Xu, Yuli Cheng and Yu Rao
Energies 2025, 18(23), 6322; https://doi.org/10.3390/en18236322 - 1 Dec 2025
Cited by 1 | Viewed by 455
Abstract
This research numerically investigates the cooling performance of Diamond-type triply periodic minimal surface (TPMS) networks as a gas turbine effusion cooling layer, augmented with various jet impingement configurations. The study analyzes the internal and external flow characteristics, pressure loss, and overall cooling effectiveness [...] Read more.
This research numerically investigates the cooling performance of Diamond-type triply periodic minimal surface (TPMS) networks as a gas turbine effusion cooling layer, augmented with various jet impingement configurations. The study analyzes the internal and external flow characteristics, pressure loss, and overall cooling effectiveness using conjugate heat transfer simulations. The Diamond design is compared to conventional film cooling and micro-hole models within a blowing ratio range of 0.5 to 2.0. The jet hole diameter and jet-to-plate distance are varied to identify an optimal double-wall cooling configuration. The results reveal that the Diamond hole mitigates the strong discharge of coolant, resulting in a more adherent cooling film, which provides excellent surface coverage. While jet impingement enhances internal heat transfer, its contribution to cooling effectiveness is minor compared to the benefit of film coverage. At an equivalent total pressure loss coefficient, the Diamond with impinging jets demonstrates 101% higher cooling effectiveness than the film hole. The thermal-mechanical analysis indicates that the Diamond model exhibits a more uniform distribution of thermal stress and displacement. The average stress is reduced by 44.7% compared to the film hole. This work confirms the TPMS-based effusion as an advanced cooling solution for next-generation gas turbines. Full article
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