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Publications (6 of 6) Show all publications
Pan, M., Mårtensson, H., Petrie-Repar, P., Sun, T. & Gezork, T. (2018). Determination of aerodynamic damping at high reduced frequencies. In: Proceedings of the ASME Turbo Expo: . Paper presented at ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018, 11 June 2018 through 15 June 2018. ASME Press
Open this publication in new window or tab >>Determination of aerodynamic damping at high reduced frequencies
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2018 (English)In: Proceedings of the ASME Turbo Expo, ASME Press, 2018Conference paper, Published paper (Refereed)
Abstract [en]

In turbomachines, forced response of blades is blade vibrations due to external aerodynamic excitations and it can lead to blade failures which can have fatal or severe economic consequences. The estimation of the level of vibration due to forced response is dependent on the determination of aerodynamic damping. The most critical cases for forced response occur at high reduced frequencies. This paper investigates the determination of aerodynamic damping at high reduced frequencies. The aerodynamic damping was calculated by a linearized Navier-Stokes flow solver with exact 3D non-reflecting boundary conditions. The method was validated using Standard Configuration 8, a two-dimensional flat plate. Good agreement with the reference data at reduced frequency 2.0 was achieved and grid converged solutions with reduced frequency up to 16.0 were obtained. It was concluded that at least 20 cells per wavelength is required. A 3D profile was also investigated: an aeroelastic turbine rig (AETR) which is a subsonic turbine case. In the AETR case, the first bending mode with reduced frequency 2.0 was studied. The 3D acoustic modes were calculated at the far-fields and the propagating amplitude was plotted as a function of circumferential mode index and radial order. This plot identified six acoustic resonance points which included two points corresponding to the first radial modes. The aerodynamic damping as a function of nodal diameter was also calculated and plotted. There were six distinct peaks which occurred in the damping curve and these peaks correspond to the six resonance points. This demonstrates for the first time that acoustic resonances due to higher order radial acoustic modes can affect the aerodynamic damping at high reduced frequencies.

Place, publisher, year, edition, pages
ASME Press, 2018
National Category
Energy Systems
Identifiers
urn:nbn:se:kth:diva-238364 (URN)10.1115/GT2018-75294 (DOI)000457071100048 ()2-s2.0-85054016240 (Scopus ID)9780791851159 (ISBN)
Conference
ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018, 11 June 2018 through 15 June 2018
Note

QC 20181113

Available from: 2018-11-12 Created: 2018-11-12 Last updated: 2020-01-02Bibliographically approved
Gezork, T., Petrie-Repar, P. & Fransson, T. (2016). A NEW VISUALIZATION METHOD FOR HARMONIC UNSTEADY FLOWS IN TURBOMACHINERY. In: PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2016, VOL 7B. Paper presented at ASME Turbo Expo: Turbine Technical Conference and Exposition. AMER SOC MECHANICAL ENGINEERS
Open this publication in new window or tab >>A NEW VISUALIZATION METHOD FOR HARMONIC UNSTEADY FLOWS IN TURBOMACHINERY
2016 (English)In: PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2016, VOL 7B, AMER SOC MECHANICAL ENGINEERS , 2016Conference paper, Published paper (Refereed)
Abstract [en]

Understanding unsteady flow processes is key in the analysis of challenging problems in turbomachinery design such as flutter and forced response. In this paper a new visualization method for harmonic unsteady flow is presented. The method illustrates the direction in which unsteady waves are traveling and transporting energy by the direct visualization of the propagating pressure waves in terms of field lines constructed from the wave group velocity. The group velocity is calculated from the unsteady flow solution by assuming that the local unsteady pressure perturbation of interest can be represented by a single harmonic unsteady wave. The applicability of the method is demonstrated for three test cases including a linear cascade of two-dimensional flat plates and a linear cascade of two-dimensional compressor blade profiles.

Place, publisher, year, edition, pages
AMER SOC MECHANICAL ENGINEERS, 2016
National Category
Mechanical Engineering
Identifiers
urn:nbn:se:kth:diva-196481 (URN)000385461300066 ()2-s2.0-84991735542 (Scopus ID)
Conference
ASME Turbo Expo: Turbine Technical Conference and Exposition
Note

QC 20161124

Available from: 2016-11-24 Created: 2016-11-14 Last updated: 2019-01-14Bibliographically approved
Gezork, T., Gutierrez, M., Groth, P., Vogt, D. M. & Fransson, T. (2015). Unsteady blade force computation sensitivity in a transonic turbine to rotor tip gap, hub and shroud cavity model detail. In: Proceedings of the 14th International Symposium on Unsteady Aerodynamics, Aeroacoustics & Aeroelasticity of Turbomachines: . Paper presented at The 14th International Symposium on Unsteady Aerodynamics, Aeroacoustics & Aeroelasticity of Turbomachines, KTH, Stockholm, 2015.
Open this publication in new window or tab >>Unsteady blade force computation sensitivity in a transonic turbine to rotor tip gap, hub and shroud cavity model detail
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2015 (English)In: Proceedings of the 14th International Symposium on Unsteady Aerodynamics, Aeroacoustics & Aeroelasticity of Turbomachines, 2015Conference paper, Published paper (Refereed)
Abstract [en]

The influence of including geometric detailing features on blade forcing predicted by CFD calculations is investigated. Various features such as rotor tip gap, rotor tip shroud cavity with substantial leakage flow and large rotor upstream hub rim cavity are investigated. The test case is based on a single stage transonic test turbine rig in which the unsteady aerodynamics and blade forcing have previously been investigated numerically.

Including the tip gap and the tip shroud leakage in the computational model resulted in an overall increase in unsteady forcing. The change in forcing is mainly due to a change in secondary flow structure, but also due to a change of the stage flow condition. Conversely, it is shown that including the hub cavity in the computational model, even without the presence of purge-flow, reduces the unsteady force. Lastly, even though there are changes in unsteady blade loading, the blade response amplitude is only changed marginally (maximum 7%) due to forcing variations alone.

National Category
Mechanical Engineering
Identifiers
urn:nbn:se:kth:diva-178410 (URN)
Conference
The 14th International Symposium on Unsteady Aerodynamics, Aeroacoustics & Aeroelasticity of Turbomachines, KTH, Stockholm, 2015
Note

Qc 20160318

Available from: 2015-12-07 Created: 2015-12-07 Last updated: 2019-01-14Bibliographically approved
Gezork, T., Mayorca, M. A., Groth, P., Vogt, D. M. & Fransson, T. (2014). Influence of tip shroud cavity detailing on turbine blade forcing calculations. In: ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. Paper presented at ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014, Dusseldorf, Germany, 16 June 2014 through 20 June 2014 (pp. V07BT35A021). ASME Press, 7B
Open this publication in new window or tab >>Influence of tip shroud cavity detailing on turbine blade forcing calculations
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2014 (English)In: ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, ASME Press, 2014, Vol. 7B, p. V07BT35A021-Conference paper, Published paper (Refereed)
Abstract [en]

Forced response in turbomachinery refers to the vibration of a component due to an excitation originating from another component. Obstacles, such as struts and blade rows in the upstream and downstream flow path of a turbomachine engine lead to engine order (EO) excitations. To be able to predict the severity of these excitations, both aerodynamic and structural calculations are performed. There is a risk of critical high cycle fatigue (HCF) failure when the force acts at a resonance frequency. Customarily, forcing calculations exclude detailing features, such as leakage flows. The current investigation uses a two stage subsonic model steam turbine configuration with shrouded rotor blades to demonstrate the influence of neglecting flow through seal cavities for blade forcing predictions. Upstream and downstream vanes are the excitation sources on the rotor blade. Calculation results are compared for a configuration including and excluding the tip shroud cavity. Computed data is compared to available pressure data from tests in the model turbine. The investigation shows for the first blade passing excitation at design point that the axial and circumferential rotor forcing change by +22%, respectively +4% when including the tip shroud cavity for the investigated configuration. The change in forcing arises from the interaction of the leakage flow with the main stream flow. For highly loaded designs this can be of importance if there is a critical excitation.

Place, publisher, year, edition, pages
ASME Press, 2014
Keywords
Engines, Excited states, Fatigue of materials, Leakage (fluid), Steam turbines, Stream flow, Turbomachine blades, Calculation results, Critical excitation, Downstream flow, Excitation sources, Forced response, High cycle fatigue, Resonance frequencies, Structural calculations
National Category
Energy Engineering
Identifiers
urn:nbn:se:kth:diva-160680 (URN)10.1115/GT2014-26724 (DOI)000362240200079 ()2-s2.0-84922237083 (Scopus ID)9780791845776 (ISBN)
Conference
ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014, Dusseldorf, Germany, 16 June 2014 through 20 June 2014
Funder
Swedish Energy Agency
Note

QC 20150226

Available from: 2015-02-26 Created: 2015-02-26 Last updated: 2019-01-14Bibliographically approved
Gezork, T. & Völker, S. (2013). Applicability of quasi-3d blade design methods to profile shape optimization of turbine blades. In: Proc. ASME Turbo Expo: . Paper presented at ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013, 3 June 2013 through 7 June 2013, San Antonio, Tx.
Open this publication in new window or tab >>Applicability of quasi-3d blade design methods to profile shape optimization of turbine blades
2013 (English)In: Proc. ASME Turbo Expo, 2013Conference paper, Published paper (Refereed)
Abstract [en]

The performance of gas turbine airfoils is continually improved by creating advanced aerodynamic and thermal designs. Optimization methods are used to handle the increasing complexity of such a design. However, optimization is expensive when performed based on 3D CFD calculations. Therefore, an optimization strategy based on simpler, less expensive analysis methods is desirable. Oftentimes, a so-called quasi-3D (Q3D) approach is used, where 2D calculations are carried out on multiple, radially stacked meridional blade sections. This paper investigates the applicability of such an approach for optimization with regard to blade profile loss. Obviously, certain physical effects are neglected using this approach, leading to errors in the predicted blade performance. Still, optimization based on Q3D calculations might be possible if the error is consistent, i.e. not random. For this purpose, a design of experiment (DOE) was carried out to compare and correlate loss predictions from Q3D calculations and high-fidelity 3D CFD calculations for gas turbine blades. It is shown that the total pressure loss coefficients found with both the Q3D and 3D calculations correlate well (75-90%) to warrant the use of a Q3D method for profile shape optimization. Subsequently, an optimization is performed to demonstrate the applicability of the method.

Series
Proceedings of the ASME Turbo Expo ; 6 B
National Category
Energy Systems
Identifiers
urn:nbn:se:kth:diva-139415 (URN)10.1115/GT2013-95467 (DOI)2-s2.0-84890172333 (Scopus ID)9780791855232 (ISBN)
Conference
ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, GT 2013, 3 June 2013 through 7 June 2013, San Antonio, Tx
Note

QC 20140116

Available from: 2014-01-16 Created: 2014-01-13 Last updated: 2014-01-16Bibliographically approved
Gezork, T. & Petrie-Repar, P. Influence of gap detailing on calculated unsteady non-adjacent blade row aero-forcing in a transonic compressor stage.
Open this publication in new window or tab >>Influence of gap detailing on calculated unsteady non-adjacent blade row aero-forcing in a transonic compressor stage
(English)Manuscript (preprint) (Other academic)
Abstract [en]

Resonant or close to resonant forced response excitation of compressor blades limits component life time, and can potentially lead to high cycle fatigue failure if the excitingforces are large and damping is insufficient. When numerically quantifying the forcing function by means of simulations,simplifications are typically made in the analysis to reducecomplexity and computational cost. In this paper we numerically investigate how the blade forcing function is influencedby the rotor tip gap flow and by flow across gaps in the upstream VIGV row. Unsteady simulations are made using a testrig geometry where a forcing crossing with an excitation froma non-adjacent blade row had previously been measured. Theeffects of the gaps on the forcing function for the first torsionmode are presented for both the non-adjacent blade row excitation (changes compared with a case without gaps indicating a 20% reduction) and an adjacent excitation (changes indicating an80% increase in terms of forcing function amplitude comparing with a case without gaps).

National Category
Engineering and Technology
Identifiers
urn:nbn:se:kth:diva-241111 (URN)
Note

QC 20190114

Available from: 2019-01-11 Created: 2019-01-11 Last updated: 2019-01-14Bibliographically approved
Organisations
Identifiers
ORCID iD: ORCID iD iconorcid.org/0000-0001-9195-793X

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