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Selected Papers from the 16th International Symposium on Unsteady Aerodynamics,...
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Selected Papers from the 16th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines (ISUAAAT16)

A special issue of International Journal of Turbomachinery, Propulsion and Power (ISSN 2504-186X).

Deadline for manuscript submissions: closed (31 December 2023) | Viewed by 2095

Special Issue Editors

Prof. Dr. Roque Corral

E-Mail Website1 Website2
Guest Editor
Department of Fluid Mechanics and Aerospace Propulsion, School of Aeronautics and Space, Universidad Politécnica de Madrid, 28040 Madrid, Spain
Interests: gas turbines aerodynamics; aeroelasticity and aeroacoustics in turbomachinery; computational fluid dynamics; reduced order methods
Prof. Dr. Damian Vogt

E-Mail Website
Guest Editor
Turbomachinery and Propulsion Group, Dipartimento di SM, ITSM—Institute of Thermal Turbomachinery and Machinery Laboratory, University of Stuttgart, 70569 Stuttgart, Germany
Interests: turbomachinery aerodynamics
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

It is our pleasure and honor to organize and present this Special Issue of the International Journal of Turbomachinery, Propulsion and Power for the 16th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines (ISUAAAT16) held at Toledo, Spain, September 19–23, 2022.

The ISUAAAT conference series, which started more than 40 years ago, is held every two to three years, primarily in Europe and occasionally in the United States and Asia. The symposia provide a unique opportunity in a single session format to bring together researchers and engineers from academic institutions and engine manufacturers working in the field to share their latest findings and to exchange ideas. For ISUAAAT15, there were 55 accepted full conference papers, and 4 keynote lectures, with authors from 14 countries and 4 continents.

The 10 papers selected for this Special Issue on Aeroelasticity of Turbomachinery were first recommended for consideration by the members of the International Scientific Committee of ISUAAAT based on the full paper and the presentations and then peer-reviewed according to the IJTPP standards.

Prof. Dr. Roque Corral
Prof. Dr. Damian Vogt
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. International Journal of Turbomachinery, Propulsion and Power is an international peer-reviewed open access quarterly 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 1000 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.

Published Papers (3 papers)

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Research

17 pages, 10631 KiB  
Article
Relationship between Casing Pressure and Non-Synchronous Vibration in an Axial Compressor
by Valerie Hernley, Aleksandar Jemcov, Jeongseek Kang, Matthew Montgomery and Scott C. Morris
Int. J. Turbomach. Propuls. Power 2024, 9(2), 14; https://doi.org/10.3390/ijtpp9020014 - 02 Apr 2024
Viewed by 548
Abstract
The relationship between aerodynamic forcing and non-synchronous vibration (NSV) in axial compressors remains difficult to ascertain from experimental measurements. In this work, the relationship between casing pressure and blade vibration was investigated using experimental observations from a 1.5-stage axial compressor under off-design conditions. [...] Read more.
The relationship between aerodynamic forcing and non-synchronous vibration (NSV) in axial compressors remains difficult to ascertain from experimental measurements. In this work, the relationship between casing pressure and blade vibration was investigated using experimental observations from a 1.5-stage axial compressor under off-design conditions. The wavenumber-dependent auto-spectral density (ASD) of casing pressure was introduced to aid in understanding the characteristics of pressure fluctuations that lead to the aeromechanical response. Specifically, the rotor blade’s natural frequencies and nodal diameters could be directly compared with the pressure spectra. This analysis indicated that the rotating disturbances coincided with the first bending (1B) and second bending (2B) vibration modes at certain frequencies and wavenumbers. The non-intrusive stress measurement system (NSMS) data showed elevated vibration amplitudes for the coincident nodal diameters. The amplitude of the wavenumber-dependent pressure spectra was projected onto the single-degree-of-freedom (SDOF) transfer function and was compared with the measured vibration amplitude. The results showed a near-linear relationship between the pressure and vibration data. Full article
(This article belongs to the Special Issue Selected Papers from the 16th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines (ISUAAAT16))
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19 pages, 11703 KiB  
Article
Numerical and Experimental Study of Flutter in a Realistic Labyrinth Seal
by Oscar Bermejo, Juan Manuel Gallardo, Adrian Sotillo, Arnau Altuna, Roberto Alonso and Andoni Puente
Int. J. Turbomach. Propuls. Power 2024, 9(2), 13; https://doi.org/10.3390/ijtpp9020013 - 01 Apr 2024
Viewed by 593
Abstract
Labyrinth seals are commonly used in turbomachinery in order to control leakage flows. Flutter is one of the most dangerous potential issues for them, leading to High Cycle Fatigue (HCF) life considerations or even mechanical failure. This phenomenon depends on the interaction between [...] Read more.
Labyrinth seals are commonly used in turbomachinery in order to control leakage flows. Flutter is one of the most dangerous potential issues for them, leading to High Cycle Fatigue (HCF) life considerations or even mechanical failure. This phenomenon depends on the interaction between aerodynamics and structural dynamics; mainly due to the very high uncertainties regarding the details of the fluid flow through the component, it is very hard to predict accurately. In 2014, as part of the E-Break research project funded by the European Union (EU), an experimental campaign regarding the flutter behaviour of labyrinth seals was conducted at “Centro de Tecnologias Aeronauticas” (CTA). During this campaign, three realistic seals were tested at different rotational speeds, and the pressure ratio where the flutter onset appeared was determined. The test was reproduced using a linearised uncoupled structural-fluid methodology of analysis based on Computational Fluid Dynamics (CFD) simulations, with results only in moderate agreement with experimental data. A procedure to adjust the CFD simulations to the steady flow measurements was developed. Once this method was applied, the matching between flutter predictions and the measured data improved, but some discrepancies could still be found. Finally, a set of simulations to retain the influence of the external cavities was run, which further improved the agreement with the testing data. Full article
(This article belongs to the Special Issue Selected Papers from the 16th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines (ISUAAAT16))
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16 pages, 4744 KiB  
Article
Modelling Method for Aeroelastic Low Engine Order Excitation Originating from Upstream Vanes’ Geometrical Variability
by Marco Gambitta, Bernd Beirow and Sven Schrape
Int. J. Turbomach. Propuls. Power 2024, 9(2), 12; https://doi.org/10.3390/ijtpp9020012 - 01 Apr 2024
Viewed by 543
Abstract
The manufacturing geometrical variability in axial compressors is a stochastic source of uncertainty, implying that the real geometry differs from the nominal design. This causes the real geometry to lose the ideal axial symmetry. Considering the aerofoils of a stator vane, the geometrical [...] Read more.
The manufacturing geometrical variability in axial compressors is a stochastic source of uncertainty, implying that the real geometry differs from the nominal design. This causes the real geometry to lose the ideal axial symmetry. Considering the aerofoils of a stator vane, the geometrical variability affects the flow traversing it. This impacts the downstream rotor, especially when considering the aeroelastic excitation forces. Optical surface scans coupled with a parametrisation method allow for acquiring the information relative to the real aerofoils geometries. The measured data are included in a multi-passage and multi-stage CFD setup to represent the mistuned flow. In particular, low excitation harmonics on the rotor vane are introduced due to the geometrical deviations of the upstream stator. The introduced low engine orders, as well as their amplitude, depend on the stator geometries and their order. A method is proposed to represent the phenomena in a reduced CFD domain, limiting the size and number of solutions required to probabilistically describe the rotor excitation forces. The resulting rotor excitation forces are reconstructed as a superposition of disturbances due to individual stator aerofoils geometries. This indicates that the problem is linear in the combination of disturbances from single passages. Full article
(This article belongs to the Special Issue Selected Papers from the 16th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines (ISUAAAT16))
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