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  • 1
    Online Resource
    Online Resource
    Springer Science and Business Media LLC ; 2009
    In:  Flow, Turbulence and Combustion Vol. 83, No. 4 ( 2009-12), p. 449-484
    In: Flow, Turbulence and Combustion, Springer Science and Business Media LLC, Vol. 83, No. 4 ( 2009-12), p. 449-484
    Type of Medium: Online Resource
    ISSN: 1386-6184 , 1573-1987
    Language: English
    Publisher: Springer Science and Business Media LLC
    Publication Date: 2009
    detail.hit.zdb_id: 1492282-4
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  • 2
    In: Journal of Turbomachinery, ASME International, Vol. 142, No. 10 ( 2020-10-01)
    Abstract: Modern high-pressure turbine (HPT) blade design stands out due to its high complexity comprising three-dimensional blade features, multipassage cooling system (MPCS), and film cooling to allow for progressive thermodynamic process parameters. During the last decade, probabilistic design approaches have become increasingly important in turbomachinery to incorporate uncertainties such as geometric variations caused by manufacturing scatter and deterioration. Within this scope, the first part of this two-part article introduces parametric models for cooled turbine blades that enable probabilistic finite element (FE) analysis taking geometric variability into account to aim at sensitivity and robustness evaluation. The statistical database is represented by a population of more than 400 blades whose external geometry is captured by optical measurement techniques and 34 blades that are digitized by computed tomography (CT) to record the internal geometry and the associated variability, respectively. Based on these data, parametric models for airfoil, profiled endwall (PEW), wedge surface (WSF), and MPCS are presented. The parametric airfoil model that is based on the traditional profile theory is briefly described. In this regard, a methodology is presented that enables to adapt this airfoil model to a given population of blades by means of Monte Carlo-based optimization. The endwall variability of hub and shroud are parametrized by radial offsets that are applied to the respective median endwall geometry. WSFs are analytically represented by planes. Variations of the MPCS are quantified based on the radial distribution of cooling passage centroids. Thus, an individual MPCS can be replicated by applying adapted displacement functions to the core passage centroids. For each feature that is considered within this study, the accuracy of the parametric model is discussed with respect to the variability that is present in the investigated blade population and the measurement uncertainty. Within the scope of the second part of this article, the parametric models are used for a comprehensive statistical analysis to reveal the parameter correlation structure and probability density functions (PDFs). This is required for the subsequent probabilistic finite element analysis involving real geometry effects.
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2020
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
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  • 3
    Online Resource
    Online Resource
    ASME International ; 2008
    In:  Journal of Turbomachinery Vol. 130, No. 4 ( 2008-10-01)
    In: Journal of Turbomachinery, ASME International, Vol. 130, No. 4 ( 2008-10-01)
    Abstract: In this two-part paper, results of the periodical unsteady flow field within the third rotor blade row of the four-stage Dresden low-speed research compressor are presented. The main part of the experimental investigations was performed using laser Doppler anemometry. Results of the flow field at several spanwise positions between midspan and rotor blade tip will be discussed. In addition, time-resolving pressure sensors at midspan of the rotor blades provide information about the unsteady profile pressure distribution. In Part I of the paper, the flow field at midspan of the rotor blade row will be discussed. Different aspects of the blade row interaction process are considered for the design point and an operating point near the stability limit. The periodical unsteady blade-to-blade velocity field is dominated by the incoming stator wakes, while the potential effect of the stator blades is of minor influence. The inherent vortex structures and the negative jet effect, which is coupled to the wake appearance, are clearly resolved. Furthermore the time-resolved profile pressure distribution of the rotor blades is discussed. Although the negative jet effect within the rotor blade passage is very pronounced, the rotor blade pressure distribution is nearly independent of the convectively propagating chopped stator wakes.
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2008
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
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  • 4
    In: Journal of Turbomachinery, ASME International, Vol. 123, No. 3 ( 2001-07-01), p. 461-463
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2001
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
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  • 5
    Online Resource
    Online Resource
    ASME International ; 2004
    In:  Journal of Turbomachinery Vol. 126, No. 1 ( 2004-01-01), p. 45-51
    In: Journal of Turbomachinery, ASME International, Vol. 126, No. 1 ( 2004-01-01), p. 45-51
    Abstract: This two-part paper presents experimental investigations of unsteady aerodynamic blade row interactions in the first stage of the four-stage low-speed research compressor of Dresden. Both the unsteady boundary layer development and the unsteady pressure distribution of the stator blades are investigated for several operating points. The measurements were carried out on pressure side and suction side at midspan. In Part II of the paper the investigations of the unsteady pressure distribution on the stator blades are presented. The experiments were carried out using piezoresistive miniature pressure sensors, which are embedded into the pressure and suction side surface of a single blade. The unsteady pressure distribution on the blade is analyzed for the design point and an operating point near the stability limit. The investigations show that it is strongly influenced by both the incoming wakes and the potential flow field of the downstream rotor blade row. If a disturbance arrives the leading edge or the trailing edge of the blade the pressure changes nearly simultaneously along the blade chord. Thus the unsteady profile pressure distribution is independent of the wake propagation within the blade passage. A phase shift of the reaction on pressure and suction side is observed. The unsteady response of the boundary layer and the profile pressure distribution is compared. Based on the unsteady pressure distribution the unsteady pressure forces of the blades are calculated and discussed.
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2004
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
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  • 6
    Online Resource
    Online Resource
    ASME International ; 2008
    In:  Journal of Turbomachinery Vol. 130, No. 4 ( 2008-10-01)
    In: Journal of Turbomachinery, ASME International, Vol. 130, No. 4 ( 2008-10-01)
    Abstract: In this two-part paper, results of the periodical unsteady flow field within the third rotor blade row of the four-stage Dresden low-speed research compressor are presented. The main part of the experimental investigations was performed using laser Doppler anemometry. Results of the flow field at several spanwise positions between midspan and rotor blade tip will be discussed. In addition, time-resolving pressure sensors at midspan of the rotor blades provide information about the unsteady profile pressure distribution. In Part II of the paper, the flow field in the rotor blade tip region will be discussed. The experimental results reveal a strong periodical interaction of the incoming stator wakes and the rotor blade tip clearance vortices. Consequently, in the rotor frame of reference, the tip clearance vortices are periodical with the stator blade passing frequency. Due to the wakes, the tip clearance vortices are separated into different segments. Along the mean vortex trajectory, these parts can be characterized by alternating patches of higher and lower velocities and flow turning or subsequent counter-rotating vortex pairs. These flow patterns move downstream along the tip clearance vortex path in time. As a result of the wake influence, the orientation and extension of the tip clearance vortices as well as the flow blockage periodically vary in time.
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2008
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
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  • 7
    In: Journal of Turbomachinery, ASME International, Vol. 141, No. 2 ( 2019-02-01)
    Abstract: In this work, we present the results of the numerical investigations of periodic wake–secondary flow interaction carried out on a low pressure turbine (LPT) equipped with modified T106-profile blades. The numerical predictions obtained by means of unsteady Reynolds-averaged Navier–Stokes (URANS) simulations using a k-ω-model have been compared with measurements conducted in the same configuration and showed a good agreement. Based on the verified numerical data, the Q-criterion has been employed to characterize the secondary flow structures and accurately identify their origin. An analysis of the fundamental wake kinematics and the unsteady vortex migration revealed dominant interaction mechanisms such as the circumferential fluctuation of the pressure side horseshoe vortex (HSV) and its direct interaction with the passage vortex (PV) and the concentrated shed vortex (CSV). Finally, a correlation with the total pressure loss coefficient is provided and a link to the incoming wake structures is given.
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2019
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
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  • 8
    In: Journal of Turbomachinery, ASME International, Vol. 134, No. 5 ( 2012-09-01)
    Abstract: The understanding of the tip clearance flow in axial compressors is a key issue for developing new compressors with enhanced efficiency and reduced noise for instance. However, necessary flow measurements in the blade tip region and within the tip clearance are challenging due to the small gap width. The application of a novel optical measurement technique named Doppler global velocimetry with laser frequency modulation is presented, which provides velocity field measurements of all three velocity components nonintrusively in the tip clearance flow of a linear cascade at near stall conditions. These array measurements have a high temporal resolution enabling turbulence analysis such as the evaluation of velocity standard deviations and turbulence spectra up to several kilohertz. Conventional pneumatic and hot-wire measurements in planes at the inlet and the outlet as well as on the blade surface were taken to complete the flow pattern and validate the data of the Doppler global velocimetry. Wake measurements identified a strong flow separation in the rear suction side dominating the transient character of the cascade flow. Towards the endwall this high loss region is reduced by the clearance flow and the resulting vortex, which is obviously not affected by the profile separation and the pulsating blockage frequency. Inside the blade passage and the tip clearance the Doppler global velocimetry measurements allowed a spatial assignment of the origin of the tip leakage flow and the downstream developing vortex. In addition, the tip clearance vortex could be resolved and identified successfully as the most dominant turbulence generating effect in the near endwall region at this high loading operating point of the blading.
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2012
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
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  • 9
    In: Journal of Engineering for Gas Turbines and Power, ASME International, Vol. 145, No. 3 ( 2023-03-01)
    Abstract: A method for a coupled structural–computational fluid dynamics (CFD) analysis of a compressor rotor blade subjected to an ice impact scenario is investigated to assess the impact related blade deformations from a structural and fluid-dynamics perspective. On the basis of a probabilistic approach, in total 50 impact scenarios are derived for this study. In a first step, the numerical structural model based on finite elements is discussed, including several parameter variations like impact location, ice diameter, ice density, and rotor speed. Different analysis steps are subsequently carried out using ls-dyna implicit/explicit on a high performance computing cluster. Resulting blade deformations are evaluated in terms of local plastic deformation, cup size and modal parameters in comparison to the undamaged reference structure. The resultant postimpact blade geometry is extracted from the result data and passed to the CFD simulation setup in a fully automated manner. Based on this deformed structural mesh data, the fluid mesh is morphed via a radial basis function approach and analyzed with CFD. Finally, an uncertainty quantification study is performed to assess the variability of results with regard to the definition of the ice impactor.
    Type of Medium: Online Resource
    ISSN: 0742-4795 , 1528-8919
    Language: English
    Publisher: ASME International
    Publication Date: 2023
    detail.hit.zdb_id: 2010437-6
    detail.hit.zdb_id: 165371-4
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  • 10
    Online Resource
    Online Resource
    ASME International ; 2004
    In:  Journal of Turbomachinery Vol. 126, No. 4 ( 2004-10-01), p. 507-518
    In: Journal of Turbomachinery, ASME International, Vol. 126, No. 4 ( 2004-10-01), p. 507-518
    Abstract: This two-part paper presents detailed experimental investigations of unsteady aerodynamic blade row interactions in the four-stage Low-Speed Research Compressor of Dresden. In part I of the paper the unsteady profile pressure distributions for the nominal setup of the compressor are discussed. Furthermore, the effect of blade row clocking on the unsteady profile pressures is investigated. Part II deals with the unsteady aerodynamic blade forces, which are calculated from the measured profile pressure distributions. The unsteady pressure distributions were analyzed in the first, a middle and the last compressor stage both on the rotor and stator blades. The measurements were carried out on pressure side and suction side at midspan. Several operating points were investigated. A complex behavior of the unsteady profile pressures can be observed, resulting from the superimposed influences of the wakes and the potential effects of several up- and downstream blade rows of the four-stage compressor. The profile pressure changes nearly simultaneously along the blade chord if a disturbance arrives at the leading edge or the trailing edge of the blade. Thus the unsteady profile pressure distribution is nearly independent of the convective wake propagation within the blade passage. A phase shift of the reaction of the blade to the disturbance on the pressure and suction side is observed. In addition, clocking investigations were carried out to distinguish between the different periodic influences from the surrounding blade rows. For this reason the unsteady profile pressure distribution on rotor 3 was measured, while stators 1–4 were separately traversed stepwise in the circumferential direction. Thus the wake and potential effects of the up- and downstream blade rows on the unsteady profile pressure could clearly be distinguished and quantified.
    Type of Medium: Online Resource
    ISSN: 0889-504X , 1528-8900
    Language: English
    Publisher: ASME International
    Publication Date: 2004
    detail.hit.zdb_id: 56356-0
    detail.hit.zdb_id: 2010462-5
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