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Energies
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Gas Turbine Cooling and Sealing Technology: Fundamentals and Applications
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Gas Turbine Cooling and Sealing Technology: Fundamentals and Applications

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

Deadline for manuscript submissions: 20 August 2026 | Viewed by 1585

Special Issue Editor

Prof. Dr. Guoqing Li

E-Mail Website
Guest Editor
Key Laboratory of Light-Duty Gas-Turbine, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
Interests: heat transfer in aero-engines; high-effectiveness low-loss cooling technology; advanced sealing technology; rotational machinery measurement; AI optimization

Special Issue Information

Dear Colleagues,

The demand for higher efficiency of gas engine brings the need of higher turbine inlet temperature (TIT) and lower specific fuel consumption (SFC), which makes cooling and sealing technology very important. The development of these two technologies integrates multiple discipline such as fluid mechanics, heat transfer, thermodynamics, material, etc. With the continuous upgrading of gas turbines, more studies are focused on the cooling and sealing technology including higher cooling and sealing efficiency, lower loss, more optimized structures and less secondary air, which needs concept innovation, fundamental intensification, methodology improvement, and application validation.

This Special Issue aims to present and disseminate the most recent advances related to the theory, design, modelling, measurement, optimization, application for gas turbine heat transfer.

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

  • All aspects of heat transfer in gas turbines.
  • Cooling technology for gas turbines including film cooling, transpiration cooling, impingement cooling, double-wall cooling, rib, pin-fin, etc.
  • Flow and heat transfer for rotating cavity.
  • Flow and heat transfer for pre-swirl system.
  • Sealing technology for gas turbine including labyrinth seal, brush seal, carbon seal, finger seal, film seal, rim seal, etc.
  • Mixing mechanism between leakage flow and cooling flow.
  • AI optimization.
  • Advanced modelling approaches.
  • Advanced measurement methods.
  • Thermal management.
  • Secondary air system.

Prof. Dr. Guoqing Li
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 250 words) can be sent to the Editorial Office for assessment.

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

  • gas turbine
  • aero-engine
  • heat transfer
  • cooling
  • sealing
  • flow
  • blade
  • cavity

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Published Papers (3 papers)

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Research

16 pages, 2700 KB  
Article
Thermal Protection Modular Design for High-Speed Aircraft Engines and Optimization Based on Design of Experiments
by Guangyan Pan, Chunlei Zhang and Xiao Yu
Energies 2026, 19(7), 1616; https://doi.org/10.3390/en19071616 - 25 Mar 2026
Viewed by 436
Abstract
High-altitude and high-speed aircraft generate substantial aerodynamic heat during flight, creating a harsh thermal environment in the engine compartment that risks overheating and burnout of control components and fuel and lubricating oil accessories. Consequently, the thermal protection system (TPS) design for engine accessories [...] Read more.
High-altitude and high-speed aircraft generate substantial aerodynamic heat during flight, creating a harsh thermal environment in the engine compartment that risks overheating and burnout of control components and fuel and lubricating oil accessories. Consequently, the thermal protection system (TPS) design for engine accessories has become one of the key technologies in hypersonic vehicle design. Based on certain TBCC, this paper uses a modular active-passive integrated TPS design and employs the quality management experimental design tool to optimize the design and decouple the method proposed on the modular design boundaries. This paper is the first to combine modular design with design of experiments (DOE) tools and apply them to the TPS of high-altitude and high-speed combined power accessories. The design scheme is optimized by identifying the main influencing factors. The optimized TPS scheme decreases the performance loss by 10% and increases cooling efficiency by 22–26%. The proposed engineering method shortens the development cycle significantly and improves efficiency by 78%. The modular design method for accessory TPS provided in this paper has good engineering applicability and can be widely used in the early stages of thermal protection scheme design, scheme optimization, scheme selection, and overall thermal management of hypersonic combined power systems. Full article
(This article belongs to the Special Issue Gas Turbine Cooling and Sealing Technology: Fundamentals and Applications)
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22 pages, 6224 KB  
Article
Analysis of Aerodynamic and Heat Transfer Characteristics of Non-Axisymmetric Endwall for Turbine Vane
by Chengqi Zhang, Haohan Wang, Jiajie Liu, Pei Wang, Mai Li, Pengfei Wang, Jun Liu and Xingen Lu
Energies 2026, 19(6), 1533; https://doi.org/10.3390/en19061533 - 20 Mar 2026
Viewed by 355
Abstract
Gas turbine engines operate in extremely harsh environments, subjecting turbines to high aerodynamic and thermal loads. In this context, non-axisymmetric endwalls have emerged as an effective strategy for reducing aerodynamic losses and mitigating heat transfer on the endwall surfaces, leading to their widespread [...] Read more.
Gas turbine engines operate in extremely harsh environments, subjecting turbines to high aerodynamic and thermal loads. In this context, non-axisymmetric endwalls have emerged as an effective strategy for reducing aerodynamic losses and mitigating heat transfer on the endwall surfaces, leading to their widespread adoption in turbine designs. This study presents an optimization of the endwall shape for a turbine guide vane from a real engine, employing the multi-island genetic algorithm. The optimization objectives are the endwall surface heat transfer coefficient and the total pressure loss coefficient at the blade outlet. The findings indicate that the modified endwall disrupts the horseshoe vortex structure at the blade leading edge, adversely influencing the formation and development of passage vortices within the cascade. Notably, this modification results in a significant reduction in aerodynamic losses and a decrease in the heat transfer coefficient on the endwall surface. Specifically, the total pressure loss coefficient at the outlet is reduced by 1.96%, while the endwall surface heat transfer coefficient decreases by 3.05%. These results underscore the considerable effectiveness of the optimized endwall design in enhancing turbine performance. Full article
(This article belongs to the Special Issue Gas Turbine Cooling and Sealing Technology: Fundamentals and Applications)
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18 pages, 6834 KB  
Article
Numerical Investigation on the Flow Characteristics in Axial-Inlet Cover-Plate Cavities
by Zengyan Lian, Pei Wang, Guang Liu, Ziyi Sun, Jun Liu, Huiping Pei, Wenying Ju and Xingen Lu
Energies 2026, 19(3), 816; https://doi.org/10.3390/en19030816 - 4 Feb 2026
Viewed by 360
Abstract
This paper investigates the complex flow characteristics and parameter prediction methods for axial-inlet cover-plate cavities in pre-swirl systems numerically. Using a full-annulus three-dimensional computational model, the flow mechanisms of cover-plate cavities are compared between axial and radial inlet configurations. The analysis reveals that [...] Read more.
This paper investigates the complex flow characteristics and parameter prediction methods for axial-inlet cover-plate cavities in pre-swirl systems numerically. Using a full-annulus three-dimensional computational model, the flow mechanisms of cover-plate cavities are compared between axial and radial inlet configurations. The analysis reveals that the axial-inlet configuration exhibits intensified non-axisymmetric vortex pairs in the low-radius region due to axial inflow inertia. These vortex structures enhance radial angular momentum exchange, leading to a substantial inlet angular momentum deficit that consequently reduces swirl ratios and pressure coefficients relative to the radial-inlet configuration. Furthermore, parametric studies demonstrate that small gap ratio amplifies circumferential flow non-uniformity through strong impingement effects, while elevated inlet swirl ratio significantly extends the source region boundary by strengthening centrifugal forces. To address the prediction discrepancies in existing models, this work proposes a modified correlation for the effective inlet swirl ratio that account for the inlet momentum loss and develops a new predictive model for the edge of source region incorporating centrifugal effects. These physics-based corrections, validated against simulation data, significantly improve the prediction accuracy for axial-inlet cover-plate cavities compared to conventional models. Full article
(This article belongs to the Special Issue Gas Turbine Cooling and Sealing Technology: Fundamentals and Applications)
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