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Aerospace
Special Issues
New Insights into Aerodynamics and Cooling in Gas Turbine Engines
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New Insights into Aerodynamics and Cooling in Gas Turbine Engines

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

Deadline for manuscript submissions: 30 April 2024 | Viewed by 2602

Special Issue Editors

Prof. Dr. Yu Rao

E-Mail Website
Guest Editor
School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai 201100, China
Interests: heat transfer; gas turbine cooling; aerodynamics; turbulent flow; heat exchanger
Dr. Yang Li

E-Mail Website
Guest Editor
School of Mechanical and Power Engineering, Shanghai Jiaotong University, Shanghai, China
Interests: heat transfer; gas turbine cooling; aerodynamics; turbulent flow; heat exchanger

Special Issue Information

Dear Colleagues,

Gas turbines are observed in a wide range of applications, from space propulsion to stationary power generation. The extensive utilization of gas turbines has led to many experimental and numerical studies aimed at enhancing their durability and efficiency. The reliability of gas turbine technology in a dynamic environment is a key factor for satisfying power-developing units. Hence, gas turbine technology has undergone significant advancements, resulting in high reliability, increased power generation, and improved efficiency. These developments have also led to more compact turbines with less vibration and weight.

Gas turbines have garnered significant attention from researchers due to their aerodynamic characteristics, which have substantially improved to achieve more realistic results. The study of aerodynamics within a turbine stage, the stator and rotor blades, is a highly complex task that continues to be a focal point of research efforts in the gas turbine community. The complex flow of gas turbine blades can lead to severe blade vibration and, consequently, efficiency loss or machine failure. As a result, extensive research has been undertaken for many years to comprehensively understand the aerodynamic flow through gas turbine blades better.

The efficiency of gas turbines is also highly related to the turbine inlet temperature. The rapid development of gas turbines, however, causes a large gap between the turbine inlet’s temperature and the maximum attainable temperature of the advanced material of gas turbine components. Advanced cooling techniques have been employed to bridge this gap to achieve the thermal protection requirement of gas turbine components. Many experimental and numerical investigations have been executed in the last 5 years to characterize the cooling performance of various geometrical configurations for a wide range of flow conditions. As advanced manufacturing methods have been utilized to generate sophisticated structures, more complicated and highly efficient cooling models have been proposed to improve the internal and external cooling performance of gas turbines.

Novel insights into aerodynamics and cooling in gas turbine engines have the potential to accelerate current fundamental research on advanced aerodynamics and cooling techniques and facilitate the advancement of revolutionary aerodynamics and cooling technologies to a higher level of technological readiness. The research conducted in the aerodynamics and cooling of gas turbine engines plays a significant and essential role in higher reliability and efficiency while satisfying the durability demands of gas turbine engines.

This Special Issue aims to unite innovative developments and collaborations concerning novel insights into aerodynamics and cooling in gas turbine engines. The potential topics include, but are not limited to, the following areas:

Advances in gas turbine cooling; advances in the aerodynamics of gas turbine blades; new concept aerodynamics and cooling systems in gas turbine engines; additive manufacture-based cooling technology; novel impingement/effusion cooling; novel external and internal cooling; advanced experimental techniques in aerodynamics and gas turbine cooling; aero-thermal-mechanical analysis in cooling systems; advanced analytical methods in aerodynamics and gas turbine cooling.

Prof. Dr. Yu Rao
Dr. Yang Li
Guest Editors

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

  • gas turbine
  • turbine blade aerodynamics
  • additive manufacturing
  • passive flow control
  • advanced cooling system
  • turbine blade/vane cooling
  • novel external cooling
  • high-efficiency internal cooling
  • double-wall cooling
  • conjugate heat transfer
  • experimental/analytical methods
  • computational fluid dynamics

Published Papers (3 papers)

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Research

16 pages, 4746 KiB  
Article
Investigations on Hot Air Anti-Icing Characteristics with Internal Jet-Induced Swirling Flow
by Yuyang Liu and Xian Yi
Aerospace 2024, 11(4), 270; https://doi.org/10.3390/aerospace11040270 - 30 Mar 2024
Viewed by 492
Abstract
The tangential jet-induced swirling flow is a highly efficient technology for enhancing heat transfer. This paper explores the application of swirling flow of an airfoil/aero-engine in a hot air anti-icing chamber, aiming to improve the anti-icing performance and achieve a more uniform temperature [...] Read more.
The tangential jet-induced swirling flow is a highly efficient technology for enhancing heat transfer. This paper explores the application of swirling flow of an airfoil/aero-engine in a hot air anti-icing chamber, aiming to improve the anti-icing performance and achieve a more uniform temperature on the surface. A series of numerical computations adopting the SST k − ω turbulent model was carried out to obtain the internal flow and heat transfer characteristics, as well as the surface temperature distributions, considering water evaporation and solid heat conduction. Three jet arrangements, including impingement jets, offset jets, and swirl jets, were studied and compared, which evidently showed that the swirling effect was helpful to elevate the internal heat transfer. Compared to the impingement jets at the Reynolds number of 40,000, the Nusselt number with the offset jets is increased by 19.5%, while the corresponding Nusselt number of the swirl jets is augmented by 44.3%. The swirling flow significantly elevates the swirl number within the internal chamber, intensifying the vortex strength near the wall and increasing the circumferential velocity, which also results in an augmentation of internal pressure loss. By adopting the swirling internal flow, the temperature distribution on the anti-icing surface is more uniform and is increased by up to about 4.1 K in the leading edge when the internal-to-external temperature difference is 80 K. Simultaneously, the heat absorption of water evaporation and the matches between the internal heat transfer and external icing load are of particular importance to determine the anti-icing performance, and this has been discussed in this paper. Full article
(This article belongs to the Special Issue New Insights into Aerodynamics and Cooling in Gas Turbine Engines)
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18 pages, 6706 KiB  
Article
Effect of Impellers on the Cooling Performance of a Radial Pre-Swirl System in Gas Turbine Engines
by Wenjie Shen, Suofang Wang and Xiaodi Liang
Aerospace 2024, 11(3), 187; https://doi.org/10.3390/aerospace11030187 - 26 Feb 2024
Viewed by 779
Abstract
Impellers are utilized to increase pressure to ensure that a radial pre-swirl system can provide sufficient cooling airflow to the turbine blades. In the open literature, the pressurization mechanism of the impellers was investigated. However, the effect of impellers on the cooling performance [...] Read more.
Impellers are utilized to increase pressure to ensure that a radial pre-swirl system can provide sufficient cooling airflow to the turbine blades. In the open literature, the pressurization mechanism of the impellers was investigated. However, the effect of impellers on the cooling performance of the radial pre-swirl system was not clear. To solve the aforementioned problem, tests were carried out to assess the temperature drop in a radial pre-swirl system with various impeller configurations (impeller lengths l/b ranging from 0 to 0.333). Furthermore, numerical simulations were used to investigate the flow and heat transfer characteristics of the radial pre-swirl system at high rotating Reynolds numbers. Theoretical and experimental investigations revealed that the pre-swirl jet and output power generate a significant temperature drop, but the impellers have no obvious effect on the system temperature drop. By increasing the swirl ratio, the impellers reduce the field synergy angle and thus improve convective heat transfer on the turbine disk. In addition, increasing the impeller length can reduce the volume-averaged field synergy angle and improve heat transfer, but the improvement effectiveness decreases as the impeller length increases. Thus, the study concluded that impellers could improve the cooling performance of the radial pre-swirl system by enhancing disk cooling. Full article
(This article belongs to the Special Issue New Insights into Aerodynamics and Cooling in Gas Turbine Engines)
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18 pages, 9332 KiB  
Article
Turbulent Flow Heat Transfer and Thermal Stress Improvement of Gas Turbine Blade Trailing Edge Cooling with Diamond-Type TPMS Structure
by Kirttayoth Yeranee, Yu Rao, Chao Xu, Yueliang Zhang and Xiyuan Su
Aerospace 2024, 11(1), 37; https://doi.org/10.3390/aerospace11010037 - 29 Dec 2023
Cited by 1 | Viewed by 1039
Abstract
Additive manufacturing allows the fabrication of relatively complex cooling structures, such as triply periodic minimal surface (TPMS), which offers high heat transfer per unit volume. This study shows the turbulent flow heat transfer and thermal stress of the Diamond-TPMS topology in the gas [...] Read more.
Additive manufacturing allows the fabrication of relatively complex cooling structures, such as triply periodic minimal surface (TPMS), which offers high heat transfer per unit volume. This study shows the turbulent flow heat transfer and thermal stress of the Diamond-TPMS topology in the gas turbine blade trailing edge channel. The thermal-fluid-solid analysis of the Diamond-TPMS structure, made of directionally solidified GTD111, at the nearly realistic gas turbine condition is executed, and the results are compared with the conventional pin fin array at the Reynolds number of 30,000. Compared to the baseline pin fin structure, the Diamond-TPMS model distributes flow characteristics more uniformly throughout the channel. The overall heat transfer enhancement, friction factor ratio, and thermal performance are increased by 145.3%, 200.9%, and 32.5%, respectively. The temperature, displacement, and thermal stress in the Diamond-TPMS model are also distributed more evenly. The average temperature on the external surface in the Diamond-TPMS model is lower than the baseline pin fin array by 19.9%. The Diamond-TPMS network in the wedge-shaped cooling channel helps reduce the volume displacement due to the material thermal expansion by 29.3%. Moreover, the volume-averaged von Mises stress in the Diamond-TPMS structure is decreased by 28.8%. Full article
(This article belongs to the Special Issue New Insights into Aerodynamics and Cooling in Gas Turbine Engines)
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