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Aerospace
Special Issues
Progress in Turbomachinery Technology for Propulsion
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Progress in Turbomachinery Technology for Propulsion

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: 1 July 2024 | Viewed by 1404

Special Issue Editors

Dr. Andrea Magrini

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Padova, Via Venezia 1, 35131 Padova, Italy
Interests: aircraft propulsion; turbomachinery; engine–airframe interaction; computational fluid dynamics; optimisation
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Ernesto Benini

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Padova, Via Venezia 1, 35131 Padova, Italy
Interests: CFD of flows in industrial and energy systems: optimal design methods; performance analysis in design and off-design conditions; full-annulus uRANS methods; aerothermodynamics of propulsion machines; CFD of supersonic and hypersonic flows
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The evolution of aircraft transport towards the binding requirement of environmental compatibility and socio-economical sustainability is facing huge challenges in the design and integration of future powerplants in hybrid electric boundary layer ingesting (BLI) vehicles. Despite their complexity, and the impressive advancements which have occurred in gas turbine technology in recent decades, uncountable scientific and technological challenges remain to be faced for a proper environmental transition following international regulations, such as novel design methodologies for distortion-tolerant turbomachinery, efficient computational methods for multi-disciplinary simulations, aeromechanical design and stability in the presence of inflow distortion, aeroacoustics of podded or fuselage-embedded engines, turbo-electric engines design and heat management, and the efficient testing of highly integrated propulsion. 

The Special Issue aims to collect the latest research results related to analytical, computational, or experimental methods advancing turbomachinery technology for propulsion. Original research or review papers illustrating significant contributions to design or analysis techniques, fundamental physics, applications, and performance improvement in gas turbines are welcomed. Representative topics include, for instance, design methodologies for gas turbine components; coupled methods for propulsion system integration; numerical/experimental analyses of gas turbine engines at the system or component level; aeromechanical design and analysis of turbomachinery; novel numerical tools for multi-disciplinary simulation; design and testing of low noise propulsor; hybrid electric and boundary layer ingestion (BLI) propulsion systems; and open rotors, turboprop, or electric fan engines.

Dr. Andrea Magrini
Prof. Dr. Ernesto Benini
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

  • turbomachinery
  • gas turbine engines
  • propulsion system design and integration
  • hybrid electric propulsion
  • inlet distortion
  • boundary layer ingestion
  • ultra-high bypass ratio turbofan
  • computational fluid dynamics (CFD)
  • wind tunnel tests
  • aeroelasticity and aeromechanics
  • aeroacoustics of jet engines and nacelles
  • propeller and open rotor

Published Papers (2 papers)

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Research

16 pages, 2909 KiB  
Article
Numerical Investigations on the Effects of Dome Cooling Air Flow on Combustion Characteristics and Emission Behavior in a Can-Type Gas Turbine Combustor
by Chenzhen Ji, Wentao Shi, Enlei Ke, Jiaying Cheng, Tong Zhu, Chao Zong and Xinyan Li
Aerospace 2024, 11(5), 338; https://doi.org/10.3390/aerospace11050338 - 25 Apr 2024
Viewed by 277
Abstract
To meet the requirements of achieving higher efficiency and lower NOx pollution, the flame temperature in gas turbine combustors increases continually; thus, the effusion-cooling technology has been used to ensure the combustor liner remains within the allowed temperature, by which the combustion characteristics [...] Read more.
To meet the requirements of achieving higher efficiency and lower NOx pollution, the flame temperature in gas turbine combustors increases continually; thus, the effusion-cooling technology has been used to ensure the combustor liner remains within the allowed temperature, by which the combustion characteristics and emission behavior are possibly influenced. In order to investigate the effects of dome cooling air flow on combustion characteristics and NOx emissions, three-dimensional combustion simulations for a swirl-stabilized can-type gas turbine combustor are carried out in this work by using the computational fluid dynamics (CFD) method. Through adjusting the ratio of the dome cooling air flow and the dilution cooling air flow, the characteristics of flow field, temperature distribution and NOx emissions under each work condition are analyzed. At different ratios of the dome-cooling air flow to the total air flow, the flow velocity field in the region near the center of the combustion chamber is not changed much, while the velocity field near the chamber wall shows a more significant difference. The temperature in the outer recirculation zone within the combustion chamber is effectively reduced as the dome cooling air flow increases. By analyzing the distribution characteristics of the concentration of OH*, it is demonstrated that the dome cooling air flow does not have a direct effect on the reaction of combustion. It is also found that as the ratio of the dome cooling air flow to the total air flow increases from 0 to 0.15, the value of the NOx emissions drops from 28.4 to 26.3 ppmv, about a 7.4% decrease. The distribution of the NOx generation rate in the combustion chamber does not vary significantly with the increasing dome cooling air flow. Furthermore, by calculating the residence time in different stages, when the the ratio of the dome cooling air flow to the total air flow varies from 0 to 0.15, the residence time in the pilot stage decreases obviously, from 42 ms to 18 ms. This means that reduction in residence time is the main factor in the decrease of NOx emissions when the dome cooling air flow increases. Full article
(This article belongs to the Special Issue Progress in Turbomachinery Technology for Propulsion)
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21 pages, 10150 KiB  
Article
Performance Improvement of a High Loading Centrifugal Compressor with Vaned Diffuser by Hub Contour Optimization
by Yunfeng Wu, Qingkuo Li, Hang Yuan, Ziliang Li, Shiji Zhou, Ge Han and Xingen Lu
Aerospace 2024, 11(4), 246; https://doi.org/10.3390/aerospace11040246 - 22 Mar 2024
Viewed by 740
Abstract
High-pressure ratio centrifugal compressors’ diffusers face challenges from high-velocity, non-uniform flow at the impeller outlet, decreasing efficiency and stall margin. To address this, this paper presents a novel vaned diffuser passage design method that successfully improved the compressor’s performance. An optimization method using [...] Read more.
High-pressure ratio centrifugal compressors’ diffusers face challenges from high-velocity, non-uniform flow at the impeller outlet, decreasing efficiency and stall margin. To address this, this paper presents a novel vaned diffuser passage design method that successfully improved the compressor’s performance. An optimization method using axisymmetric hub contours and NURBS curves was applied to modify the diffuser’s design. After optimization, centrifugal compressor peak efficiency increased by 0.78%, and stall margin expanded from 12.8% to 20.4%. Analysis at the peak efficiency point showed loss reduction mainly from decreased recirculation and mixing losses in the diffuser’s vaneless and semi-vaneless spaces. Furthermore, correlation analysis and Mach number distribution revealed that flow behavior at the diffuser’s leading edge significantly influences efficiency. Consequently, design principles emphasize satisfying specific Mach number distribution rules at the diffuser’s leading edge under certain inflow conditions for optimal performance. Full article
(This article belongs to the Special Issue Progress in Turbomachinery Technology for Propulsion)
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