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Advanced Technologies in Gas Turbines
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Advanced Technologies in Gas Turbines

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

Deadline for manuscript submissions: closed (31 March 2023) | Viewed by 9864

Special Issue Editors

Dr. Lei Luo

E-Mail Website
Guest Editor
School of Energy Science and Engineering, Harbin Institue of Technology, Harbin 150001, China
Interests: heat transfer; gas turbines; aerodynamics
Dr. Wei Du

E-Mail Website
Guest Editor
School of Energy Science and Technology, Harbin Institute of Technology, Harbin 150001, China
Interests: heat transfer in gas turbine
Special Issues, Collections and Topics in MDPI journals
Dr. Xiao Liu

E-Mail Website
Guest Editor
College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China
Interests: combustion; heat transfer; gas turbines

Special Issue Information

Dear Colleagues,

Gas turbines are widely used in aviation propulsion plants, marine power plants, and the power generation field because of their high-power density, high efficiency, and good performance at off-design points. A high efficiency of gas turbines is conductive to improving the energy structure, reducing carbon dioxide emissions, protecting the Earth’s environment, and bringing great economic benefits. Further improving the efficiency and power of gas turbines has been the eternal pursuit of researchers and designers. However, advanced gas turbines are pushing the limits of technology in the areas of material science due to the very high firing temperatures, and of aerodynamics due to the very high-pressure ratios developed in the compressors. Dry low NOx combustors are also pushing the technology in the areas of combustion and flame stability. This Special Issue aims to encourage researchers to focus on the advanced technology in gas turbines and propose novel technologies. The topics of interest in this Special Issue include but are not limited to the flow mechanism in turbomachinery, heat transfer in turbine blades, secondary air systems, multidisciplinary design optimization, ceramic matrix composites, additive manufacturing, gas turbine combustion, and so on. In addition, we look forward to attracting review articles to help researchers to understand the challenges and progress for advanced gas turbines.

Dr. Lei Luo
Dr. Wei Du
Dr. Xiao Liu
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. 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

  • flow mechanism in compressors
  • flow mechanism in turbine blades
  • heat transfer and film cooling
  • secondary air systems
  • noise reduction
  • combustion and flame
  • multidisciplinary design optimization
  • ceramic matrix composites
  • additive manufacturing for turbomachinery
  • 3D full aerodynamics simulation

Published Papers (5 papers)

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Research

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24 pages, 9351 KiB  
Article
Numerical Investigation into a New Method of Non-Axisymmetric End Wall Contouring for Axial Compressors
by Fuhao You, Xiangjun Li, Qing Lu, Haoguang Zhang and Wuli Chu
Energies 2022, 15(9), 3305; https://doi.org/10.3390/en15093305 - 30 Apr 2022
Viewed by 1322
Abstract
To deal with corner separation in high-load axial compressors, this paper proposes a new end wall contouring method aimed at controlling the end wall secondary flow in more than one local area, generating a geometry with fewer control variables that is applicable for [...] Read more.
To deal with corner separation in high-load axial compressors, this paper proposes a new end wall contouring method aimed at controlling the end wall secondary flow in more than one local area, generating a geometry with fewer control variables that is applicable for multiple working conditions. The new method defines more than one surface unit function, with different effects on end wall secondary flow. Then, the geometry of these surface unit functions will be superposed to generate the end wall contouring, to combine their flow control effects. After applying the new method to a bi-objective optimization design process, with 15 design variables aimed at minimizing the loss of cascade at 0° and 4° incidence, the optimal design reduces the total pressure loss of the high-load cascade by 5% under the former incidence and by 3% under the latter. The most effective design rule is constructing an end wall surface with the rising suction side and sinking pressure side in the blade channel, while locally raising the SS corner with a gentle upstream slope. According to the analysis, the design variables of the new method show an intuitive influence on the variation of end wall geometry and the movement of secondary flow. The corner separation has been effectively suppressed, with fewer control variables than before. It, thus, indicates the advantage of the newly developed end wall contouring method compared with previous studies. Full article
(This article belongs to the Special Issue Advanced Technologies in Gas Turbines)
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13 pages, 2222 KiB  
Article
Theoretical Research on Flow and Heat Transfer Characteristics of Hydrostatic Oil Film in Flat Microfluidic Boundary Layer
by Liansheng Liu, Huiru Qu, Runze Duan, Teng Liu, Chentao Li, Enyu Wang and Lujia Liu
Energies 2022, 15(7), 2443; https://doi.org/10.3390/en15072443 - 26 Mar 2022
Viewed by 1425
Abstract
The hydrostatic bearing is the core component of ultra-precision computer numerical control (CNC) machine tools. Because the temperature rise in the oil film of hydrostatic bearings seriously affects the working accuracy of the bearings, it is important to study the flow and heat [...] Read more.
The hydrostatic bearing is the core component of ultra-precision computer numerical control (CNC) machine tools. Because the temperature rise in the oil film of hydrostatic bearings seriously affects the working accuracy of the bearings, it is important to study the flow and heat transfer characteristics of the oil film. Based on the physical model of an incompressible viscous fluid flowing in a flat microfluidic boundary layer, velocity, temperature and heat flux distribution equations of oil film are constructed by theories of heat transfer and hydrodynamics. Then, the effects of several parameters on velocity distribution, temperature distribution and heat flux distribution are analyzed, such as the upper plate velocity, the channel length, and so on. The results show that the dimensionless velocity of the oil film decreases with the increase in the upper plate velocity and the channel length. The oil film temperature distribution can be divided into three zones: the increasing zone, stabilizing zone and decreasing zone. The heat flux decreases linearly with the increase in the plate thickness, and increases linearly with the increase in the temperature difference. Full article
(This article belongs to the Special Issue Advanced Technologies in Gas Turbines)
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18 pages, 10964 KiB  
Article
Numerical Study on Vortex Structures and Loss Characteristics in a Transonic Turbine with Various Squealer Tips
by Yufan Wang, Weihao Zhang, Dongming Huang, Shoumin Jiang and Yun Chen
Energies 2022, 15(3), 1018; https://doi.org/10.3390/en15031018 - 29 Jan 2022
Cited by 3 | Viewed by 2121
Abstract
Cavity width and height are two key geometric parameters of squealer tips, which could affect the control effect of squealer tips on tip leakage flow (TLF) of gas turbines. To explore the optimal values and the control mechanisms of cavity width and height, [...] Read more.
Cavity width and height are two key geometric parameters of squealer tips, which could affect the control effect of squealer tips on tip leakage flow (TLF) of gas turbines. To explore the optimal values and the control mechanisms of cavity width and height, various cases with different cavity widths and heights are investigated by solving the steady Reynolds Averaged Navier–Stokes (RANS) equations. In this study, the range of cavity width is 9.2–15.1 τ, and that of cavity height is 1.0–3.5 τ. The results show that the optimal value of cavity height is 2.5–3.0 τ, and that of cavity width is about 10.0–10.5 τ. The small cavity width could restrain the breakdown of tip leakage vortex (TLV) and reduce the extra mixing loss. Both small cavity width and large cavity height could enhance the blocking effect on the TLF, reducing the corresponding mixing loss. However, both of them will inhibit the length of the scraping vortex (SV), which is bad for the control of loss. In addition, large cavity height could reduce the loss inside the clearance, while small cavity width could not. This work could provide a reference for the design of squealer tip. Full article
(This article belongs to the Special Issue Advanced Technologies in Gas Turbines)
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15 pages, 6030 KiB  
Article
Effects of Front Plate Geometry on Brush Seal in Highly Swirling Environments of Gas Turbine
by Yuxin Liu, Benzhuang Yue, Xiaozhi Kong, Hua Chen and Huawei Lu
Energies 2021, 14(22), 7768; https://doi.org/10.3390/en14227768 - 19 Nov 2021
Viewed by 1639
Abstract
Advanced brush seal technology has a significant impact on the performance and efficiency of gas turbine engines. However, in highly inlet swirling environments, the bristles of a brush seal tend to circumferentially slip, which may lead to aerodynamic instability and seal failure. In [...] Read more.
Advanced brush seal technology has a significant impact on the performance and efficiency of gas turbine engines. However, in highly inlet swirling environments, the bristles of a brush seal tend to circumferentially slip, which may lead to aerodynamic instability and seal failure. In this paper, seven different front plate geometries were proposed to reduce the impact of high inlet swirl on the bristle pack, and a three-dimensional porous medium model was carried out to simulate the brush seal flow characteristics. Comparisons of a plane front plate with a relief cavity, plane front plate with axial drilled holes, anti-“L”-type plate and their relative improved configurations on the pressure and flow fields as well as the leakage behavior were conducted. The results show that the holed front plate can effectively regulate and control the upstream flow pattern of the bristle pack, inducing the swirl flow to move radially inward, which results in decreased circumferential velocity component. The anti-“L” plate with both axial holes and one radial hole was observed to have the best effect on reducing the swirl of those investigated. The swirl velocity upstream the bristle pack can decline 50% compared to the baseline model with plane front plate, and the circumferential aerodynamic forces on the bristles, which scale with the swirl dynamic head, are reduced by a factor of 4. This could increase the bristle stability dramatically. Moreover, the front plate geometry does not influence the leakage performance significantly, and the application of the axial hole on the front plate will increase the leakage slightly by around 3.5%. Full article
(This article belongs to the Special Issue Advanced Technologies in Gas Turbines)
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Review

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21 pages, 6374 KiB  
Review
Large Eddy Simulation of Film Cooling: A Review
by Joon Ahn
Energies 2022, 15(23), 8876; https://doi.org/10.3390/en15238876 - 24 Nov 2022
Cited by 6 | Viewed by 2171
Abstract
Film cooling has dramatically contributed to the performance improvement of gas turbines, as it is a very effective cooling technique for gas turbines. Large eddy simulation (LES) began to be used in the study of film cooling 20 years ago, and meaningful results [...] Read more.
Film cooling has dramatically contributed to the performance improvement of gas turbines, as it is a very effective cooling technique for gas turbines. Large eddy simulation (LES) began to be used in the study of film cooling 20 years ago, and meaningful results have been found, but it has not yet been intensively reviewed. In this review paper, we analyze and introduce about 70 papers published on LES of film cooling over the past 20 years. Numerical instability must be overcome, and realistic inflow must be generated to perform LES of film cooling. This review summarizes how the groups that performed LES of film cooling solved these problems. In film-cooling research, the main topics are improving the film-cooling performance by preventing the lift-off of the injectant and the effect of flow conditions on film cooling. In addition, LES has also been conducted extensively on the above two topics, and this review focuses on them. Finally, turbulence statistics of film-cooling flow obtained from LES are introduced, and future challenges of film-cooling LES are predicted. Full article
(This article belongs to the Special Issue Advanced Technologies in Gas Turbines)
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