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Fluids
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Turbomachinery Flow Analysis
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Turbomachinery Flow Analysis

A special issue of Fluids (ISSN 2311-5521).

Deadline for manuscript submissions: closed (30 June 2019) | Viewed by 19641

Special Issue Editor

Prof. Dr. Abraham Engeda

E-Mail Website
Guest Editor
Turbomachinery Lab, Michigan State University, East Lansing, MI 48824, USA
Interests: experimental thermo-fluids; turbomachinery flow analysis and design； design and testing of centrifugal and regenerative flow compressors and pumps; gas turbine combustion; biogas for power generation
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

This Special Issue of Fluids will focus on all aspects of turbomachinery flow analysis. Topics to be considered include, but are not restricted to:

  • All aspects of turbomachinery aerodynamic/hydrodynamic design/operation.
  • The design/analysis/experimental testing of turbomachinery.
  • Practical applications of CFD technology in turbomachinery design and analysis.
  • CFD analysis of a turbomachinery stage/stage component.
  • Design optimization methods for turbomachinery stage and stage components.
  • Correlation of rotordynamic issues, bearing and seal design to a turbomachinery flow condition (surge, stall or chocke).
  • The prediction of turbomachinery stall and surge, including techniques for flow range extension.
  • Turbomachinery flow control, diagnostics and general instrumentation.
  • Turbomachinery failures and measures to overcome mechanical, rotordynamic or aerodynamic problems.
  • Turbomachinery aerodynamic forces that result in process machine vibrations and acoustic noise. Areas of interest include methods to identify, minimize, damp, or eliminate these aero-mechanical sources.

Prof. Abraham Engeda
Guest Editor

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. Fluids 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 1800 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 aerodynamic/hydrodynamic design/operation
  • turbomachinery optimization
  • turbomachinery unsteady flow surge/stall/choke
  • turbomachinery flow control

Published Papers (5 papers)

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Research

22 pages, 7943 KiB  
Article
Influence of Fluidic Control in a Staged Lean Jet Engine Burner on Combustor Performance
by Seiji Yoshida, Christoph Hassa, Takeshi Yamamoto, Johannes Heinze and Michael Schroll
Fluids 2019, 4(4), 188; https://doi.org/10.3390/fluids4040188 - 1 Nov 2019
Cited by 2 | Viewed by 3248
Abstract
To improve the turn-down ratio of a lean combustor, which has the greatest potential for reducing NOx emissions from jet engines, fuel staging is commonly employed. To further extend the stable operation range, air staging with a fluidic element is also considered. [...] Read more.
To improve the turn-down ratio of a lean combustor, which has the greatest potential for reducing NOx emissions from jet engines, fuel staging is commonly employed. To further extend the stable operation range, air staging with a fluidic element is also considered. The influence of fluidic control on combustion was analyzed to better understand fluidic element-burner interactions. The pressure loss of each fluidic element was determined by measuring the pressure at the element exits. The effect of fluidic control on the atomization, fuel distribution, and flow field was investigated using optical, noninvasive techniques. The combustion performance of the burner with the fluidic element was evaluated using exhaust gas analyses. The pressure losses of the swirlers and fuel mixers were varied depending on the bleed air from the fluidic element. Under the idle condition, the reduction of pressure loss in the pilot fuel mixer resulted in inferior atomization due to the reduced gas velocity around the fuel film, which had a positive effect on lean blowout. Under the cruise condition and the staged mode, the reduction of the pilot air flow increased the equivalence ratio of the lean pilot stage and resulted in higher combustion efficiency. Full article
(This article belongs to the Special Issue Turbomachinery Flow Analysis)
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25 pages, 2800 KiB  
Article
Uncertainty Quantification of Non-Dimensional Parameters for a Film Cooling Configuration in Supersonic Conditions
by Simone Salvadori, Mauro Carnevale, Alessia Fanciulli and Francesco Montomoli
Fluids 2019, 4(3), 155; https://doi.org/10.3390/fluids4030155 - 10 Aug 2019
Cited by 6 | Viewed by 3118
Abstract
In transonic high-pressure turbine stages, oblique shocks originating from vane trailing edges impact the suction side of each adjacent vane. High-pressure vanes are cooled to tolerate the combustor exit-temperature levels, then it is highly probable that shock impingement will occur in proximity to [...] Read more.
In transonic high-pressure turbine stages, oblique shocks originating from vane trailing edges impact the suction side of each adjacent vane. High-pressure vanes are cooled to tolerate the combustor exit-temperature levels, then it is highly probable that shock impingement will occur in proximity to a row of cooling holes. The presence of such a shock, together with the inevitable manufacturing deviations, alters the location of the shock impingement and of the performance parameters of each cooling hole. The present work provides a general description of the aero-thermal field that occurs on the rear suction side of a cooled vane. Computational Fluid Dynamics (CFD) is used to evaluate the deterministic response of the selected configurations in terms of adiabatic effectiveness, discharge coefficient, blowing ratio, density ratio, and momentum ratio. Turbulence is modelled by using both the Shear Stress Transport method (SST) and the Reynolds Stress Model (RSM) implemented in ANSYS® FLUENT®. The obtained results are compared with the experimental data obtained by the Institut für Thermische Strömungsmaschinen in Karlsruhe. Two uncertainty quantification methodologies based on Hermite polynomials and Padè–Legendre approximants are used to consider the probability distribution of the geometrical parameters and to evaluate the response surfaces for the system response quantities. Trailing-edge and cooling-hole diameters have been considered to be aleatory unknowns. Uncertainty quantification analysis allows for the assessment of the mutual effects on global and local parameters of the cooling device. Obtained results demonstrate that most of the parameters are independent by the variation of the aleatory unknowns while the standard deviation of the blowing ratio associated with the hole diameter uncertainty is around 12%, with no impact by the trailing-edge thickness. No relevant advantages are found using either SST model or RSM in combination with Hermite polynomials and Padè–Legendre approximants. Full article
(This article belongs to the Special Issue Turbomachinery Flow Analysis)
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16 pages, 3405 KiB  
Article
Wind Turbine Wake Modeling in Accelerating Wind Field: A Preliminary Study on a Two-Dimensional Hill
by Omar M. A. M. Ibrahim, Shigeo Yoshida, Masahiro Hamasaki and Ao Takada
Fluids 2019, 4(3), 153; https://doi.org/10.3390/fluids4030153 - 9 Aug 2019
Cited by 6 | Viewed by 2986
Abstract
Complex terrain can influence wind turbine wakes and wind speed profiles in a wind farm. Consequently, predicting the performance of wind turbines and energy production over complex terrain is more difficult than it is over flat terrain. In this preliminary study, an engineering [...] Read more.
Complex terrain can influence wind turbine wakes and wind speed profiles in a wind farm. Consequently, predicting the performance of wind turbines and energy production over complex terrain is more difficult than it is over flat terrain. In this preliminary study, an engineering wake model, that considers acceleration on a two-dimensional hill, was developed based on the momentum theory. The model consists of the wake width and wake wind speed. The equation to calculate the rotor thrust, which is calculated by the wake wind speed profiles, was also formulated. Then, a wind-tunnel test was performed in simple flow conditions in order to investigate wake development over a two-dimensional hill. After this the wake model was compared with the wind-tunnel test, and the results obtained by using the new wake model were close to the wind-tunnel test results. Using the new wake model, it was possible to estimate the wake shrinkage in an accelerating two-dimensional wind field. Full article
(This article belongs to the Special Issue Turbomachinery Flow Analysis)
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19 pages, 5365 KiB  
Article
Added Mass Effects on a Francis Turbine Runner with Attached Blade Cavitation
by Xingxing Huang and Xavier Escaler
Fluids 2019, 4(2), 107; https://doi.org/10.3390/fluids4020107 - 11 Jun 2019
Cited by 10 | Viewed by 5559
Abstract
To have a safe structural design, an analysis of the dynamic behavior of a Francis turbine runner with consideration of the added mass effects of surrounding water is necessary during design phase. Both in design and at off-design operations, large-scale forms of attached [...] Read more.
To have a safe structural design, an analysis of the dynamic behavior of a Francis turbine runner with consideration of the added mass effects of surrounding water is necessary during design phase. Both in design and at off-design operations, large-scale forms of attached cavitation may appear on runner blades and can change the added mass effects of the surrounding fluid in relation to a single water domain. Consequently, a numerical investigation of the modal response of a Francis runner has been carried out by reproducing the presence of various sizes of leading edge cavitation (LEC) and trailing edge cavitation (TEC). The fluid–structure interaction problem has been solved by means of an acoustic-structural coupling method. The calculated added mass effects with cavitation have been compared with those corresponding to the pure water condition without cavitation. Firstly, a single blade has been investigated to evaluate the level of significance for the proposed cavity shapes and dimensions. Afterwards, based on the results obtained, the complete runner structure has been considered, factoring in similar cavity shapes and locations. The results prove that significant added mass effects are induced on the entire runner by the attached cavitation that increase the natural frequencies of the first modes. Moreover, the added mass effects increase with cavity size and amplitude of blade deformation below the cavity. Full article
(This article belongs to the Special Issue Turbomachinery Flow Analysis)
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19 pages, 7614 KiB  
Article
Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial Compressor
by Motoyuki Kawase and Aldo Rona
Fluids 2019, 4(2), 88; https://doi.org/10.3390/fluids4020088 - 11 May 2019
Cited by 2 | Viewed by 4255
Abstract
A proof of concept is provided by computational fluid dynamic simulations of a new recirculating type casing treatment. This treatment aims at extending the stable operating range of highly loaded axial compressors, so to improve the safety of sorties of high-speed, high-performance aircraft [...] Read more.
A proof of concept is provided by computational fluid dynamic simulations of a new recirculating type casing treatment. This treatment aims at extending the stable operating range of highly loaded axial compressors, so to improve the safety of sorties of high-speed, high-performance aircraft powered by high specific thrust engines. This casing treatment, featuring an axisymmetric recirculation channel, is evaluated on the NASA rotor 37 test case by steady and unsteady Reynolds Averaged Navier Stokes (RANS) simulations, using the realizable k-ε model. Flow blockage at the recirculation channel outlet was mitigated by chamfering the exit of the recirculation channel inner wall. The channel axial location from the rotor blade tip leading edge was optimized parametrically over the range −4.6% to 47.6% of the rotor tip axial chord c z . Locating the channel at 18.2% c z provided the best stall margin gain of approximately 5.5% compared to the untreated rotor. No rotor adiabatic efficiency was lost by the application of this casing treatment. The investigation into the flow structure with the recirculating channel gave a good insight into how the new casing treatment generates this benefit. The combination of stall margin gain at no rotor adiabatic efficiency loss makes this design attractive for applications to high-speed gas turbine engines. Full article
(This article belongs to the Special Issue Turbomachinery Flow Analysis)
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