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Design, Simulation, Thermal Management, and Performance Assessment of Gas Turbines and Aeroengine System

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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 (10 March 2023) | Viewed by 7681

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Special Issue Editors

Dr. Xiaodong Ren

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Guest Editor

Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China
Interests: aerothermodynamics of compressor, advanced thermodynamic system and the turbine component design, and high-order methods for compressible flow in the compressor

Dr. Jin Wang

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Guest Editor

School of Energy and Environmental Engineering, Hebei University of Technology, Tianjin 300401, China
Interests: cooling technologies for gas turbines, advanced combustion technologies, high-temperature heat exchanger, multi-phase flow in gas turbines, plasma flow control, etc.
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Special Issue Information

Dear Colleagues,

Gas turbines and aeroengines have become improtant, widespread and reliable devices in fields such as power generation, aviation, and the oil and gas industry. Due to the requirement of carbon dioxide emission reduction for global climate change, large-scale utilization of hydrogen energy will become an alternative choice for gas turbines in the near future. All large commercial and military airplanes are currently, and will continue to be, powered by gas turbine propulsion systems. This indicates that gas turbines and aeroengines will continue to play a critically important role in many fields.

To improve the system performance of gas turbines or aeroengines, various studies have been conducted by both academic and industrial communities, such as on the GT-SOFC system and the GT system with sCO2 as the working fulid. Therefore, the main objective of this Special Issue is to collect the ideas of research communities worldwide in a common platform and to present the lastest advances and developments in the design, simulation, thermal management, and performance assessment of gas turbines and aeroengine systems. Topics and interests of this Special Issue include, but are not limited to:

Design and optimization for advanced or unconventional thermodynamic systems;
Design and optimization for gas turbine components compressor, turbine and combustor;
High-Fidelity simulations and validations;
High-temperature and high-power heat exchangers;
Thermal management of gas turbine and aeroengine systems;
Analysis of system integration;
Condition-based operations and maintenance;
Carbon capture and storage for the gas turbine system.

Dr. Xiaodong Ren
Dr. Jin Wang
Guest Editors

Manuscript Submission Information

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Keywords

gas turbine
aeroengine
heat exchanger
thermodynamic system
system design
energy storage and thermal management

Published Papers (5 papers)

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Research

19 pages, 11212 KiB

Open AccessArticle

Numerical Investigation and Optimization of Variable Guide Vanes Adjustment in a Transonic Compressor

by Ziyuan Wang, Xiaodong Ren, Wei Zhu, Xuesong Li and Chunwei Gu

Energies 2023, 16(1), 567; https://doi.org/10.3390/en16010567 - 3 Jan 2023

Cited by 1 | Viewed by 1475

Abstract

In the present work, numerical simulation and optimization was carried out to analyze the mechanism of the variable guide vanes (VGVs) of a transonic compressor. A seven-stage transonic compressor including three-stage VGVs was studied. The VGVs were adjusted individually and jointly under different IGV opening degrees. Changes in performance and shock wave were analyzed, and the coupling effect of the VGV joint adjustment was summarized. Aiming at the maximum efficiency, the joint turning angles were optimized. A novel phenomenon was found wherein the VGV adjustment can affect not only its own performance and that of adjacent downstream blades, but also that of upstream blades. Incidence and performance of upstream blades are improved, but those of the VGV and its adjacent downstream blades are deteriorated. VGV adjustment weakens the shock wave and shock-induced boundary layer separation. The optimal solution for VGV joint adjustment is the combination of the optimal solutions for single VGV adjustments. The joint adjustment optimization improves the efficiency by 0.2–1.93% under different IGV opening degrees. Full article

(This article belongs to the Special Issue Design, Simulation, Thermal Management, and Performance Assessment of Gas Turbines and Aeroengine System)

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21 pages, 11636 KiB

Open AccessArticle

Experimental and Numerical Investigation of the Non-Reacting Flow in a High-Fidelity Heavy-Duty Gas Turbine DLN Combustor

by Yuan Feng, Xuesong Li, Xiaodong Ren, Chunwei Gu, Xuan Lv, Shanshan Li and Ziye Wang

Energies 2022, 15(24), 9551; https://doi.org/10.3390/en15249551 - 16 Dec 2022

Cited by 2 | Viewed by 1997

Abstract

A dry, low-NO_x (DLN) combustor for a heavy-duty gas turbine using lean premixed technology was studied. A high-fidelity test model was built for the experimental study using particle image velocimetry (PIV). The non-reacting flow in the DLN combustion chamber was investigated experimentally and numerically. The numerical results are in good agreement with the experimental data. The results show that recirculation zones were formed downstream of each swirl nozzle and that the flow pattern in each section was self-similar under different working conditions. For two adjacent swirl nozzles with opposite swirling directions, the entrainment phenomenon was present between their two flows. The two flows gradually mixed with each other and obtained a higher speed. If the two adjacent swirl nozzles had the same swirling direction, then the mixing of the two flows out of the nozzles was not present, resulting in two separate downstream recirculation zones. The interaction of swirling flows out of different nozzles can enhance the turbulent fluctuation inside the combustion chamber. Based on the analysis of the recirculation zones and turbulent kinetic energy (TKE) distribution downstream of each nozzle, it can be found that nozzle coupling results in stronger recirculation and turbulent mixing downstream counterclockwise surrounding nozzles. Full article

(This article belongs to the Special Issue Design, Simulation, Thermal Management, and Performance Assessment of Gas Turbines and Aeroengine System)

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23 pages, 12970 KiB

Open AccessArticle

Optimal Design of Three-Dimensional Circular-to-Rectangular Transition Nozzle Based on Data Dimensionality Reduction

by Haoqi Yang, Qingzhen Yang, Zhongqiang Mu, Xubo Du and Lingling Chen

Energies 2022, 15(24), 9316; https://doi.org/10.3390/en15249316 - 8 Dec 2022

Viewed by 1153

Abstract

The parametric representation and aerodynamic shape optimization of a three-dimensional circular-to-rectangular transition nozzle designed and built using control lines distributed along the circumferential direction were investigated in this study. A surrogate model based on class/shape transformation, principal component analysis and radial basis neural network was proposed with fewer design parameters for parametric representation and performance parameter prediction of the three-dimensional circular-to-rectangular transition nozzle. The surrogate model was combined with Non-dominated Sorting Genetic Algorithm-II to optimize the aerodynamic shape of the nozzle. The results showed that the surrogate model effectively achieved the parametric representation and aerodynamic shape optimization of the three-dimensional circular-to-rectangular transition nozzle. The geometric dimensions and performance parameters of the parametric reconstructed model were comparable to that of the initial model, implying that they can meet the needs of optimal design. The axial thrust coefficient and lift of the optimized nozzle were increased by approximately 0.742% and 15.707%, respectively. Full article

(This article belongs to the Special Issue Design, Simulation, Thermal Management, and Performance Assessment of Gas Turbines and Aeroengine System)

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12 pages, 3498 KiB

Open AccessArticle

Utilization Optimization of Capacitive Pulsed Power Supply in Railgun

by Genrong Cao, Hongjun Xiang, Zhiming Qiao, Chunyan Liang, Xichao Yuan, Jin Wang and Bin Lei

Energies 2022, 15(14), 5051; https://doi.org/10.3390/en15145051 - 11 Jul 2022

Cited by 2 | Viewed by 1296

Abstract

The excitation pulse current used to drive the railgun needs to present very a high magnitude (hundreds of kA) flat-top with very low ripple. At present, the main method to obtain this current is to increase the number of the capacitive pulsed power supply (PPS) modules. However, low utilization and massive volume of the railgun system would occur with this method, hampering the application of railgun. Therefore, the utilization optimization technology of PPS is researched in this paper. In order to obtain highly stable flat-top current, the control strategy of the capacitive PPS is designed, and a new charging voltage configuration is proposed, which significantly decreases the use of the capacitive modules. Besides, a miniaturization transformation scheme of capacitive PPS is proposed based on the control strategy. The result shows that the flat-top current ripple has the biggest influence on the PPS utilization, and the smaller the flat-top current ripple, the lower the utilization. When the current with 200 kA magnitude and 0.75% flat-top current ripple is achieved, an 81.9% decrease of volume and a 428.7% utilization improvement are achieved through miniaturization transformation. Full article

(This article belongs to the Special Issue Design, Simulation, Thermal Management, and Performance Assessment of Gas Turbines and Aeroengine System)

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20 pages, 5829 KiB

Open AccessArticle

Numerical Investigation on Backward-Injection Film Cooling with Upstream Ramps

by Shengchang Zhang, Chunhua Wang, Xiaoming Tan, Jingzhou Zhang and Jiachen Guo

Energies 2022, 15(12), 4415; https://doi.org/10.3390/en15124415 - 17 Jun 2022

Cited by 1 | Viewed by 1113

Abstract

The present study investigates the effects of upstream ramps on a backward-injection film cooling over a flat surface. Two ramp structures, referred to as a straight-wedge-shaped ramp (SWR) and sand-dune-shaped ramp (SDR), are considered under a series of blowing ratios ranging from M = 0.5 to M = 1.5. Regarding the backward injection, the key mechanism of upstream ramps on film cooling enhancement is suggested to be the enlargement of the horizontal scale of the separate wake vortices and the reduction of their normal dimension. When compared to the SDR, the SWR modifies the backward coolant injection well, such that a larger volume of coolant is suctioned and concentrated in the near-field region at the film-hole trailing edge. As a consequence, the SWR demonstrates a more pronounced enhancement in film cooling than the SDR in the backward-injection process, which is the opposite of the result for the forward-injection scheme. For the SWR, the backward injection provides a better film cooling effectiveness than the forward injection, regardless of blowing ratios. However, for the SDR, the backward injection could show a superior effect to the forward injection on film cooling enhancement, when the blowing ratio is beyond a critical blowing ratio. In the present SDR situation, the critical blowing ratio is identified to be M = 1.0. Full article

(This article belongs to the Special Issue Design, Simulation, Thermal Management, and Performance Assessment of Gas Turbines and Aeroengine System)

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