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Advances in Heat Transfer and Combustion in Turbomachinery
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Advances in Heat Transfer and Combustion 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 (31 July 2023) | Viewed by 9260

Special Issue Editors

Dr. Antonio Andreini

E-Mail Website
Guest Editor
Department of Industrial Engineering, University of Florence, Via S. Marta 3, 50139 Firenze, Italy
Interests: gas turbine combustion; heat transfer; thermoacoustics; CFD modeling; spray atomization
Dr. Lorenzo Mazzei

E-Mail Website
Guest Editor
Ergon Research, Via Giuseppe Campani 50, 50127, Firenze, Italy
Interests: aerodynamics; turbomachinery; heat transfer; combustion; cooling; gas turbines; CFD; optimization; heat exchangers

Special Issue Information

Dear Colleagues,

Over the last few decades, advances in state-of-the-art gas turbines have led to a higher turbine inlet temperature and overall pressure ratio (for higher efficiency) and more compact core engines (for lower weight). Ultimately, this led to a general increase in the thermal loads along with a lower cooling capacity of the coolant flow, thus making the thermal management of hot gas path components an even more critical challenge. These novel engines are also more prone to significant interactions between different phenomena and components, including interactions between swirling flows and the liner, interactions between the combustor outflow and the nozzle guide vanes, and the multiphysics nature of the reactive flow, radiative heat transfer, and liner temperature. These factors have put into question the classical analysis approaches based on correlations for convective and radiative heat loads as well as the design practice that relies on a separate investigation of the combustor and the turbine without adequate integration. At the same time, heat transfer via combustor walls may greatly impact upon the combustion process; i.e., flame stabilization, combustion dynamics, and pollutant emissions.

For this Special Issue, we welcome the submission of works related to Advances in Heat Transfer and Combustion in Turbomachinery. Topics of interest include:

  1. combustor–turbine interaction;
  2. swirling flow–liner interaction;
  3. convective and radiative heat transfer;
  4. combustor liner cooling;
  5. flame–wall interaction;
  6. reactive film cooling;
  7. effects of heat transfer on combustion; and
  8. conjugate heat transfer modeling.

Dr. Antonio Andreini
Dr. Lorenzo Mazzei
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

  • combustor–turbine interaction
  • swirling flow–liner interaction
  • convective and radiative heat transfer
  • combustor liner cooling
  • flame–wall interaction
  • reactive film cooling
  • effects of heat transfer on combustion
  • conjugate Heat Transfer modeling

Published Papers (4 papers)

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Research

24 pages, 4278 KiB  
Article
Large Eddy Simulations of a Low-Swirl Gaseous Partially Premixed Lifted Flame in Presence of Wall Heat Losses
by Leonardo Langone, Matteo Amerighi and Antonio Andreini
Energies 2022, 15(3), 788; https://doi.org/10.3390/en15030788 - 21 Jan 2022
Cited by 7 | Viewed by 1776
Abstract
The use of lifted flames presents some very promising advantages in terms of pollutant emissions and flame stability. The focus here is on a specific low-swirl injection system operated with methane and derived from an air-blast atomizer for aero-engine applications, which is responsible [...] Read more.
The use of lifted flames presents some very promising advantages in terms of pollutant emissions and flame stability. The focus here is on a specific low-swirl injection system operated with methane and derived from an air-blast atomizer for aero-engine applications, which is responsible for flame lift-off. The key feature of this concept is the interaction between the swirling jet and the confinement walls, leading to a strong outer recirculation zone and thus to an upstream transport of combustion products from the main reaction region to the flame base. Here, the representation of the physics involved is challenging, since finite-rate effects govern the lift-off occurrence, and only a few numerical studies have been carried out on this test case so far. The aim of the present work is therefore to understand the limits of some state-of-the-art combustion models within the context of LES. Considering this context, two different strategies are adopted: the Flamelet-Generated Manifold (FGM) approach and the Thickened Flame (TF) model. A modified version of the FGM model including stretch and heat loss effects is also applied as an improvement of the standard model. Numerical results are compared with the available experimental data in terms of temperature and chemical species concentration maps, showing that the TF model can better reproduce the lift-off than the FGM approach. Full article
(This article belongs to the Special Issue Advances in Heat Transfer and Combustion in Turbomachinery)
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23 pages, 7996 KiB  
Article
Experimental Study of Impingement Effusion Cooled Double-Wall Combustor Liners: Aerodynamic Analysis with Stereo-PIV
by Thomas Jackowski, Maximilian Elfner, Hans-Jörg Bauer, Katharina Stichling and Marco Hahn
Energies 2021, 14(19), 6191; https://doi.org/10.3390/en14196191 - 28 Sep 2021
Cited by 3 | Viewed by 1706
Abstract
A new experimental study is presented for a combustor with a double-wall cooling design. The inner wall at the hot gas side features effusion cooling with 7-7-7 laidback fan-shaped holes, and the outer wall at the cold side features an impingement hole pattern [...] Read more.
A new experimental study is presented for a combustor with a double-wall cooling design. The inner wall at the hot gas side features effusion cooling with 7-7-7 laidback fan-shaped holes, and the outer wall at the cold side features an impingement hole pattern with circular holes. Data are acquired to asses the thermal and aerodynamic behavior of the setup, using a new, scaled up, engine similar test rig. Similarity includes Reynolds, Nusselt and Biot numbers for hot gas and coolant flow. Different geometrical setups are studied by varying the cavity height between the two walls and the relative alignment of the two hole patterns at two different impingement Reynolds numbers. This article focuses on the aerodynamic performance of the setup. Instationary flow data are acquired, using a high speed stereo PIV setup. For each geometrical configuration, approximately 20 planes are recorded with a data rate of 1000 Hz by traversing the flow region of interest in the cavity between the two specimen. This fine resolution allows the reconstruction of 3D flow fields for the mean data values and an extensive analysis of transient phenomena at each plane. Time averaged data and jet-center plane transient data are presented in detail. The results show a complex flow field with a hexagonal vortex pattern in the cavity, which is mainly influenced by the cavity height and the relative alignment of the two walls. The jet Reynolds number shows small influence when analyzing normalized data. Small cavity heights show a less developed flow field with less stable vortex systems. The alignment shows a similar influence on vortex system stability, with the aligned case performing better. Additionally, statistical analysis of the jet flow and frequency domain analysis of the jet and the effusion flow are presented, showing the damping capability of the cavity, especially at increased cavity heights, and a residual low frequency pulsation of the effusion cooling inflow. Full article
(This article belongs to the Special Issue Advances in Heat Transfer and Combustion in Turbomachinery)
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23 pages, 2622 KiB  
Article
Experimental Study of Impingement Effusion-Cooled Double-Wall Combustor Liners: Thermal Analysis
by Thomas Jackowski, Maximilian Elfner and Hans-Jörg Bauer
Energies 2021, 14(16), 4843; https://doi.org/10.3390/en14164843 - 09 Aug 2021
Cited by 5 | Viewed by 2770
Abstract
A new experimental study is presented for a combustor with a double-wall cooling design. The inner wall at the hot gas side features effusion cooling with 7-7-7 laidback fan-shaped holes, and the outer wall at the cold side features an impingement hole pattern [...] Read more.
A new experimental study is presented for a combustor with a double-wall cooling design. The inner wall at the hot gas side features effusion cooling with 7-7-7 laidback fan-shaped holes, and the outer wall at the cold side features an impingement hole pattern with circular holes. Data have been acquired to assess the thermal and aerodynamic behavior of the setup using a new, scaled up, engine-similar test rig. Similarity includes Reynolds, Nusselt, and Biot numbers for hot gas and coolant flow. Different geometrical setups are studied by varying the cavity height between the two walls and the relative alignment of the two hole patterns at several different blowing ratios. This article focuses on the thermal performance of the setup. The temperature data are acquired using two infrared systems on either side of the effusion wall specimen. In addition to cooling effectiveness evaluations, finite element simulations are performed, yielding the locally resolved wall heat fluxes. Results are presented for three cavity heights and two longitudinal specimen alignments. The results show that the hot gas side total cooling effectiveness can achieve values as high as 90% and is mainly influenced by the effusion coverage. Impingement cooling has a small influence on overall effectiveness, and the area of influence is mainly located upstream where effusion cooling is not built up completely. The analyzed geometric variations show a major influence on cavity flow and impingement heat transfer. Small cavities lead to constrained flow and high local Nusselt numbers, while larger cavities show more equalized Nusselt number distributions. A present misalignment shows especially high influence at small cavity heights. The largest cavity height, in general, showed a decrease in heat transfer due to reduced jet momentum. Full article
(This article belongs to the Special Issue Advances in Heat Transfer and Combustion in Turbomachinery)
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19 pages, 32798 KiB  
Article
Modelling Aspects in the Simulation of the Diffusive Flame in A Bluff-Body Geometry
by Alessandro Di Mauro, Marco Ravetto, Prashant Goel, Mirko Baratta, Daniela Anna Misul, Simone Salvadori, Rainer Rothbauer and Riccardo Gretter
Energies 2021, 14(11), 2992; https://doi.org/10.3390/en14112992 - 21 May 2021
Cited by 2 | Viewed by 1862
Abstract
Gas turbines are expected to play a key role in the energy production scenario in the future, and the introduction of carbon-free fuels is fundamental for the development of a sustainable energy mix. The development of a reliable numerical model is thus fundamental [...] Read more.
Gas turbines are expected to play a key role in the energy production scenario in the future, and the introduction of carbon-free fuels is fundamental for the development of a sustainable energy mix. The development of a reliable numerical model is thus fundamental in order to support the design changes required for the burners. This paper presents the results of a numerical investigation on a turbulent, diffusive, combustion test case, with the purpose of identifying the best compromise between accuracy and computational cost, in the perspective of the model application in real, more complex, geometries. Referring to a test case has two main advantages. First, a rather simple geometry can be considered, still retaining a few peculiar flow features, such as recirculation vortices and shear layers, which are typical of real applications. Second, the experimental setup is much more detailed than in the case of real turbines, allowing a thorough model validation to be performed. In this paper, the Standard 2-equations k-ε model and the Speziale-Sarkar-Gatski Reynolds Stress Model are considered. Moreover, both the FGM combustion model and the detailed chemistry model are used, coupled with two chemical reaction mechanisms, and their results are compared. Finally, a standard and an enhanced near-wall approach are employed to solve the transport equations close to the walls. The results show a good agreement in the temperature distribution at the axial positions corresponding to the experimental measurements. Overall, the standard wall function approach for describing the near-wall flow proved to be more effective at increasingly higher distances from the jet centre. Such differences are related to the formulations employed by the two near-wall approaches, which led to changes in the predicted flow field around the fuel jet. Finally, the adoption of a reaction mechanism describing in detail the species concentration is mandatory whenever the reliable prediction of the NOx formation is of primary importance. The conclusion reached in this paper can be helpful for the development of reliable and cost-effective CFD models of turbine combustors. Full article
(This article belongs to the Special Issue Advances in Heat Transfer and Combustion in Turbomachinery)
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