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Analysis and Optimization of Cooling Performance in Gas Turbines

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

Deadline for manuscript submissions: closed (31 August 2023) | Viewed by 10083

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Special Issue Editor

Dr. Jiang Lei

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Guest Editor

School of Aerospace, Xi’an Jiaotong University, Xi'an 710049, China
Interests: gas turbine heat transfer; internal cooling; film cooling; secondary air system; blade thermal analysis; high-temperaure measurement

Special Issue Information

Dear Colleagues,

The Guest Editor is inviting submissions to the Special Issue of Energies in the area of the analysis and optimization of cooling performance in gas turbines. Gas turbines are widely used in aircraft propulsion, marine propulsion, power generation, and industry. Cooling systems are of vital importance to the safety and performance of modern gas turbines, and various techniques are applied to achieve cooling including internal cooling, film cooling, transpiration cooling, compound cooling, etc.

This Special Issue will focus on the cooling and heat transfer problems experienced by hot gas passage components (combustor linerss, turbine blades, turbine disk, etc.) in gas turbines, concerning design, analysis, and optimization. Topics of interest for publication include, but are not limited to:

Internal cooling;
Film cooling;
Transpiration cooling;
Compound cooling;
Other cooling methods;
Novel cooling concepts;
Secondary air system analysis;
Cooling design methodology;
Cooling/heat transfer experimental methodology;
Cooling/heat transfer numerical methodology;
Cooling optimization.

Dr. Jiang Lei
Guest Editor

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.

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Keywords

hot gas passage component
cooling
heat transfer
secondary air system
design
experiments
simulation
optimization

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Published Papers (5 papers)

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Research

24 pages, 10511 KiB

Open AccessArticle

Aerothermal Dynamic Characteristics of Array Micro Ribs in Channel Flow

by Ke Zhao, Xueying Li and Jing Ren

Energies 2023, 16(16), 5986; https://doi.org/10.3390/en16165986 - 15 Aug 2023

Cited by 1 | Viewed by 1364

Abstract

With the rising complexity of internal cooling structures in gas turbine blades, the limited cooling air volume and pressure head provided by the compressor have become significant constraints to further enhancements in the overall efficiency of gas turbines. To address this, micro-turbulators have been proposed as a viable solution in recent research. The rib turbulators, as a typical internal cooling structure, have inherent limitations in heat transfer measurements. In this study, a segmented lumped parameter method was employed to experimentally analyze the aerothermal dynamic characteristics of micro ribs under varying rib heights and Reynolds numbers in channel flow. It was found that heat transfer performance closely correlates with both rib height and the height of the incoming boundary layer. Under certain conditions of dimensionless height and dimensionless number, optimal heat transfer enhancement near the micro-rib was observed, leading to an approximately 30% increase in the overall thermal performance (OTP) compared to the results from research into traditional 90° ribs. Numerical results based on the Reynolds stress model (RSM) suggest that this improvement is primarily due to the increased turbulence intensity in the near-wall region (y⁺ = 20–55) of the boundary layer caused by the micro ribs. This study presents a new characteristic parameter

e^{+} / \sqrt{R e}

that offers improved representation of the heat transfer performance of micro ribs, and reveals that when this parameter is around 40, micro ribs can provide high heat transfer with low pressure loss, thereby improving the overall efficiency. These results underscore the potential applicability of micro ribs in advancing the efficiency of gas turbines and other related fields. Full article

(This article belongs to the Special Issue Analysis and Optimization of Cooling Performance in Gas Turbines)

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17 pages, 11554 KiB

Open AccessArticle

Application of the Source Term Method and Fan-Shaped Hole for Cooling Performance Improvement in a High-Pressure Turbine

by Sangook Jun, Dong-Ho Rhee, Young Seok Kang, Heeyoon Chung and Jae-Hwan Kim

Energies 2022, 15(19), 6943; https://doi.org/10.3390/en15196943 - 22 Sep 2022

Cited by 3 | Viewed by 1468

Abstract

This study presents the arrangement design of the cooling hole and the application of a fan-shaped hole to improve the cooling performance of the high-pressure turbine. To this end, the first stage nozzle vane of the energy efficient engine (E3) was selected as the base model, and for efficient design, the source term method, called the injection region, was applied for producing the effect of the cooling flow when the RANS analysis was performed. At this time, because the cooling flow rate also changed when the location of the cooling hole changed, a neural network model was constructed to predict the cooling flow rate for the location of the cooling hole. Design optimization was performed to improve the film cooling effectiveness and the temperature uniformity on the vane surface using the streamwise location of the cooling hole as a design variable, and then the cooling performance was investigated by applying several fan-shaped holes instead of cylinder holes on the pressure side. As a result, the final design was obtained, which improved the film cooling effectiveness by 4.1%p and temperature uniformity by 0.7% compared with the base model. Full article

(This article belongs to the Special Issue Analysis and Optimization of Cooling Performance in Gas Turbines)

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11 pages, 8242 KiB

Open AccessArticle

Determination of Film Cooling Effectiveness and Heat Transfer Coefficient Simultaneously on a Flat Plate

by Mingjie Zhang

Energies 2022, 15(11), 4144; https://doi.org/10.3390/en15114144 - 4 Jun 2022

Cited by 1 | Viewed by 1889

Abstract

In this paper, flat plate film cooling with two rows of compound angle cylindrical film cooling holes was investigated. A data processing method was evaluated which could determine the film cooling effectiveness and heat transfer coefficient simultaneously from the transient wall temperature data. The method was based on solving an inverse problem of the one-dimensional transient heat conduction equation. To evaluate the performance of the method, wall temperature data were obtained using the known film cooling effectiveness and heat transfer coefficient data as the convection boundary condition. Then, the method was applied to calculate the film cooling effectiveness and heat transfer coefficient based on the wall temperature data. Different blowing ratios, heat transfer coefficients, mainstream temperatures, and material thermal conductivities were investigated. In general, the data and calculation were in good agreement. It was found that the error decreased when the heat transfer coefficient increased and the material thermal conductivity decreased. The percentage error of the span-wise averaged film cooling effectiveness was mainly between 0% and 10%, and the percentage error of the span-wise averaged heat transfer coefficient was mainly between 0% and 4%. Full article

(This article belongs to the Special Issue Analysis and Optimization of Cooling Performance in Gas Turbines)

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14 pages, 5194 KiB

Open AccessArticle

Effect of Blockage Inside Holes on Film Cooling Performance on the Suction Side of a Turbine Guide Vane

by Wei Zhang, Rui Zeng, Song Liu and Guangchao Li

Energies 2022, 15(8), 2935; https://doi.org/10.3390/en15082935 - 16 Apr 2022

Cited by 7 | Viewed by 1833

Abstract

In order to study the effect of thermal barrier coating deposition inside the film holes of turbine guide vanes on film cooling performance, film effectiveness on the suction side is measured by infrared thermal imaging technology. Film effectiveness is obtained at blockage ratios of 0, 0.2, 0.5, and 0.8, and blowing ratios of 0.7, 1.05, and 1.4. Film effectiveness decreases and the spanwise inhomogeneity becomes evident with an increase of the blockage ratio. When blowing ratios increase from 0.7 to 1.4, the surface averaged film effectiveness decreases by 55–60% at a large blockage ratio of 0.8, 21–27% at the middle blockage ratio of 0.5 and by no more than 11% at a small blockage ratio of 0.2. The rounded corners formed by blockage enhance the adhesion of the film at the small blockage ratio of 0.2, thereby improving the film cooling performance near the hole exit. There is a maximum increase of 0.2 in film effectiveness within four hole diameters. Full article

(This article belongs to the Special Issue Analysis and Optimization of Cooling Performance in Gas Turbines)

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16 pages, 10272 KiB

Open AccessArticle

Effects of High Buoyancy Parameter on Flow and Heat Transfer of Two-Pass Smooth/Ribbed Channels

by Wenbin He, Ke Zhang, Junmei Wu, Jiang Lei, Pengfei Su and Yu Fang

Energies 2022, 15(1), 148; https://doi.org/10.3390/en15010148 - 27 Dec 2021

Cited by 3 | Viewed by 2518

Abstract

In order to deepen the understanding of rotating effects on internal cooling, the flow and heat transfer characteristics of 2-pass rotating rectangular smooth/ribbed channels are investigated by Reynolds-Averaged Navier-Stokes (RANS) simulation. Three rotating numbers (Ro = 0.10, 0.25, and 0.40) are simulated, and the maximum buoyancy parameter (Bo) reaches 5.0. The results show that the rotating buoyancy has significant effects on the flow and heat transfer under high Bo conditions. When Bo > 1.0, rotating buoyancy inducts flow separation near the leading edge (LE) in the first passage, while the air flow in the second passage shows a double-peak profile. With increased Bo, the heat transfer in the first passage is greatly increased, and the maximum growth rate occurs at Bo = 0.6~1.0. However, the heat transfer in the second passage has no obvious changes due to a strong turn effect. In the ribbed channel, rotating effects are much weaker than those in the smooth channel. This research helps to improve the understanding of the internal cooling heat transfer mechanism in land-based gas turbines under typical operating conditions. Full article

(This article belongs to the Special Issue Analysis and Optimization of Cooling Performance in Gas Turbines)

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