Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
5.5
3.2
Journals
Energies
Special Issues
Flow and Heat Transfer in Turbomachinery
energies-logo
Submit to Energies Review for Energies Propose a Special Issue

Journal Menu

► Journal Menu

Journal Browser

► Journal Browser
share announcement

Flow and Heat Transfer in Turbomachinery

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

Deadline for manuscript submissions: closed (20 June 2023) | Viewed by 5158

Special Issue Editors

Prof. Dr. Zhongguo Sun

E-Mail Website
Guest Editor
Department of Fluid Machinery and Engineering, School of Energy and Power Engineering, Xi'an Jiaotong University, Xi'an, China
Interests: numerical and experimental study of the flow in fluid machinery; computational fluid dynamics with meshless methods
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Yijun Mao

E-Mail Website
Guest Editor
School of Aerospace Engineering, Huazhong University of Science and Technology, Wuhan 430074, China
Interests: turbomachinery flow and noise
Special Issues, Collections and Topics in MDPI journals
Dr. Tianyu Pan

E-Mail Website
Guest Editor
Research Institute of Aero-Engine, Beihang University, Beijing, China
Interests: unsteady flow and aeroelasticity in turbomachinery

Special Issue Information

Dear Colleagues,

Turbomachinery is regarded as one of the key pieces of equipment used in power machinery and engineering, and has been widely applied in the fields of energy production, aviation power, energy storage and saving, process industry, etc. However, the flow in turbomachinery is typical unsteady and complex, and is often coupled with heat transfer, fluid structure interactions, and even phase changes. The study of turbomachinery covers, but is not limited to, numerical and experimental analyses, design methods and technology, performance and reliability, phenomena and mechanisms. The demands from various industrial application strategies and extreme cases has advanced the research in the area of accurate analysis and design technology, stability and reliability enhancement, etc. This Special Issue aims to present and disseminate the most recent progress pertaining to the phenomenon, methodology, model, technology and application of turbomachinery.

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

  • Aerodynamic design and analysis for turbomachinery;
  • Test of compressor and turbine blading;
  • Compressor stall, surge, and operability issues;
  • Heat transfer phenomena and film cooling in turbomachinery;
  • Aeromechanical instabilities of turbomachinery;
  • CFD methods and models for turbomachinery;
  • Seal and gap flow for turbomachinery;
  • Measurement techniques for turbomachinery;
  • Cavity and leaking flows for turbomachinery.

Prof. Dr. Zhongguo Sun
Prof. Dr. Yijun Mao
Dr. Tianyu Pan
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

  • fluid dynamics
  • heat transfer
  • phenomena in turbomachinery
  • aeromechanical instabilities
  • boundary layer development
  • performance, loss, and leaking flow
  • centrifugal compressors
  • axial compressors
  • compressor stall and surge
  • rotor-stator interaction
  • design and optimization
  • film cooling
  • casing treatment
  • flow control
  • experimental techniques
  • numerical models and methods

Published Papers (3 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Research

26 pages, 61733 KiB  
Article
Numerical Investigations of a Non-Uniform Stator Dihedral Design Strategy for a Boundary Layer Ingestion (BLI) Fan
by Tianyu Pan, Kaikai Shi, Hanan Lu, Zhiping Li and Jian Zhang
Energies 2022, 15(16), 5791; https://doi.org/10.3390/en15165791 - 10 Aug 2022
Cited by 2 | Viewed by 1511
Abstract
A distributed propulsion system has the advantage of saving 5–15% fuel burn through ingesting the fuselage boundary layer of an aircraft by fan or compressor. However, due to boundary layer ingestion (BLI), the fan stage will continuously operate under serious inlet distortion. This [...] Read more.
A distributed propulsion system has the advantage of saving 5–15% fuel burn through ingesting the fuselage boundary layer of an aircraft by fan or compressor. However, due to boundary layer ingestion (BLI), the fan stage will continuously operate under serious inlet distortion. This will lead to a circumferentially non-uniform flow separation distribution on the stator blade suction surface along the annulus, which significantly decreases the fan’s adiabatic efficiency. To solve this problem, a non-uniform stator dihedral design strategy has been developed to explore its potential of improving BLI fan performance. First, the stator full-annulus blade passages were divided into blade dihedral design regions and baseline design regions on the basis of the additional aerodynamic loss distributions caused by BLI inlet distortion. Then, to find the appropriate dihedral design parameters, the full-annulus BLI fan was discretized into several portions according to the rotor blade number and the dihedral design parameter investigations for dihedral depth and dihedral angle were conducted at the portion with the largest inflow distortion through a single-blade-passage computational model. The optimal combinational dihedral design parameter (dihedral depth 0.3, dihedral angle 6 deg) was applied to the blade passages with notable flow loss which were mainly located in the annulus positions from −120 to 60 degrees suffering from inlet distortion, while the blades in the low-loss annulus locations were unchanged. In this way, a non-uniform stator dihedral design scheme was achieved. In the end, the effectiveness of the non-uniform stator dihedral design was validated by analyzing the internal flow fields of the BLI fan. The results show that the stator dihedral design in distorted regions can increase the inlet axial velocity and reduce the aerodynamic load near the blade trailing edge, which are beneficial for suppressing the flow separations and reducing aerodynamic loss. Specifically, compared with the baseline design, the non-uniform stator dihedral design has achieved a reduction of aerodynamic loss of about 7.7%. The fan stage has presented an improvement of adiabatic efficiency of about 0.48% at the redesigned point without sacrificing the total pressure ratio. In the entire operating range, the redesigned fan has also shown a higher adiabatic efficiency than the baseline design with no reduction of the total pressure ratio, which provides a probable guideline for future BLI distortion-tolerant fan design. Full article
(This article belongs to the Special Issue Flow and Heat Transfer in Turbomachinery)
►▼ Show Figures

Figure 1

18 pages, 8106 KiB  
Article
Research on 3D Design of High-Load Counter-Rotating Compressor Based on Aerodynamic Optimization and CFD Coupling Method
by Tingsong Yan, Huanlong Chen, Jiwei Fang and Peigang Yan
Energies 2022, 15(13), 4770; https://doi.org/10.3390/en15134770 - 29 Jun 2022
Cited by 3 | Viewed by 1430
Abstract
In view of the flow instability problem caused by the strong shock wave and secondary flow in the channel of the high-load counter-rotating compressor, this paper adopts the design method of coupling aerodynamic optimization technology and CFD and establishes a three-dimensional aerodynamic optimization [...] Read more.
In view of the flow instability problem caused by the strong shock wave and secondary flow in the channel of the high-load counter-rotating compressor, this paper adopts the design method of coupling aerodynamic optimization technology and CFD and establishes a three-dimensional aerodynamic optimization design platform for the blade channel based on an artificial neural network and genetic algorithm. The aerodynamic optimization design and internal flow-field diagnosis of a high-load counter-rotating compressor with a 1/2 + 1 aerodynamic configuration are carried out. The research indicates that the optimized blade channel can drive and adjust the flow better, and the expected supercharging purpose and efficient energy conversion process are achieved by controlling the intensity of the shock wave and secondary flow in the channel. The total pressure ratio at the design point of the compressor exceeds 2.9, the adiabatic efficiency reaches 87%, and the aerodynamic performance is excellent at the off-design condition, which is on the advanced design level of the same type of axial compressor. The established aerodynamic optimization design platform has important practical engineering applications for the development of high thrust-to-weight ratio aero-engine compression systems. Full article
(This article belongs to the Special Issue Flow and Heat Transfer in Turbomachinery)
►▼ Show Figures

Figure 1

15 pages, 4735 KiB  
Article
Numerical Simulation of the Flow and Heat Transfer Characteristics of Sweeping and Direct Jets on a Flat Plate with Film Holes
by Xiangcan Kong, Yanfeng Zhang, Guoqing Li, Xingen Lu, Junqiang Zhu and Jinliang Xu
Energies 2022, 15(12), 4470; https://doi.org/10.3390/en15124470 - 19 Jun 2022
Cited by 3 | Viewed by 1594
Abstract
The internal heat transfer performance and flow structures of a sweeping jet and film composite cooling on a flat plate were numerically studied. Sweeping jet and film composite cooling consists of a fluidic oscillator and 20 cylindrical film holes; the direct jet is [...] Read more.
The internal heat transfer performance and flow structures of a sweeping jet and film composite cooling on a flat plate were numerically studied. Sweeping jet and film composite cooling consists of a fluidic oscillator and 20 cylindrical film holes; the direct jet is formed by removing the feedback from the fluidic oscillator, which is different from the traditional cylindrical nozzle. Four different mass flow rates of coolant were considered, and the inclination angle of the film hole was 30°. The Conjugate Heat Transfer method (CHT) and Unsteady Reynolds Averaged Navier Stokes equation (URANS) were employed. The results indicated that the flow resistance coefficients of the sweeping jet were larger than those of the direct jet, and the Nusselt number monotonously increased with the increase in the mass flow rate. Compared to the direct jet, the sweeping jet had a more spatially uniform heat removal rate, and the area-averaged Nusselt number was slightly lower. Therefore, the sweeping jet and film composite cooling caused the distribution of the flat plate heat transfer to be more uniform. It is worth noting that the novel direct jet nozzle in the present work had considerable area-averaged impingement cooling effectiveness. Full article
(This article belongs to the Special Issue Flow and Heat Transfer in Turbomachinery)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-3
Back to TopTop