The Influence of Wake-Wake Interactions on Loss Fluctuations of a Downstream Axial Compressor Blade Row

Walker, G. J.; Hughes, J. D.; Köhler, I.; Solomon, W. J.

doi:10.1115/97-gt-469

Cited by 18 publications

(10 citation statements)

References 21 publications

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“…Halstead et al (1995) observed a twofold variation in momentum thickness over a rotor wake passing period at 90% suction surface length for their third stage high pressure compressor stator baseline case (28). For the compressor stator of the present investigation, Walker et al (1997a) reported near wake momentum thickness varying by a factor of about 4 in the peak unsteadiness configuration. Such large perturbations in boundary layer thickness may have important implications for stall inception.…”

Section: Introductionmentioning

confidence: 44%

“…This model neglects turbulence decay during convection downstream, and also possible turbulence production through straining near the stator leading edge. Measurements downstream of the rotor by Walker et al (1997b) showed the random turbulence component to vary only slowly with axial position.…”

Section: Prediction Of Transition Onset -Temporal Variation Freestreamentioning

confidence: 99%

See 1 more Smart Citation

Periodic Transition on an Axial Compressor Stator — Incidence and Clocking Effects: Part II — Transition Onset Predictions

Solomon

Walker

Hughes

1998

Volume 1: Turbomachinery

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Transition onset observations from a 1.5-stage axial compressor outlet stator presented in Part 1 of this paper are compared with the predictions of conventional transition correlations applied in a quasi-steady manner. The viscous/inviscid interaction code MISES is used to predict the blade surface pressure distributions and boundary layer development. The temporal variation in transition onset is then predicted using ensemble-averaged freestream turbulence data from the compressor measurements. This simple procedure captures most significant features of the complex transition process on the compressor, and is clearly superior to fixed transition models based on long-term average freestream turbulence levels. Parallel computations for both natural and bypass transition modes indicate that the natural transition mode tends to dominate on the compressor. This is at variance with turbine airfoil experience, where bypass transition is clearly more important. Comparison of prediction and experiment highlights the significance of leading edge potential flow interactions in promoting periodic wake-induced transition. Viscous/inviscid interactions in the neighborhood of transition can also have an important influence on boundary layer stability and separation phenomena.

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Section: Introductionmentioning

confidence: 44%

Section: Prediction Of Transition Onset -Temporal Variation Freestreamentioning

confidence: 99%

Periodic Transition on an Axial Compressor Stator — Incidence and Clocking Effects: Part II — Transition Onset Predictions

Solomon

Walker

Hughes

1998

Volume 1: Turbomachinery

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“…In all cases, time resolved HWA data was recorded for one-hundred revolutions of the HP shaft Is worth of data, and post-processed using the techniques described below. For the reduction of the instantaneous data obtained from the hot wire measurements, the following procedure was employed, Walker (1997).…”

Section: Range Of Investigationmentioning

confidence: 99%

Time Resolved HWA Measurements of the OTL Flow Field From a Shrouded Turbine HP Rotor Blade

Taylor

Pablos

Rose

1998

Volume 1: Turbomachinery

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Detailed time resolved Hot Wire Anemometry (HWA) measurement have been made of the over tip leakage (OTL) flow field, from a shrouded HP rotor blade. The objective of this study being to investigate the sensitivity of the flow conditions presented to the IP Nozzle Guide Vane (IPNGV), resulting from changes to the HP blade tip gap clearance and shroud geometry. An extensive experimental data set has been produced in the outer 25% of the annulus height. Post-processing of this data has allowed both the absolute & rotor relative velocity and whirl angle to be calculated, which has been presented in both a graphical and semi-animated form. A detailed analysis of the flow field has been undertaken, which has been compared with the exit flow field predicted by a comprehensive CFD simulation of the HP blade and shroud. Good agreement between the measured and the predicted flow field has been obtained. This has permitted the salient features, which influence the flow conditions presented to the IPNGV, to be identified. Advanced post-processing of the time-resolved data, has enabled some of the Reynolds and Deterministic stress components to be evaluated. A comparison of the magnitude of these components has been made, which the objective of assessing their relative importance in multistage steady CFD calculations.

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“…This has been 2 International Journal of Rotating Machinery done to study vane clocking, the circumferential indexing of adjacent vane rows with similar vane counts. Researchers have shown that vane clocking can impact stage loss and efficiency by changing the amount of interaction the upstream vane wakes have with the downstream vane boundary layer [5][6][7][8]. In this research, clocking is used to isolate the flow field effects associated with the downstream vane potential field.…”

Section: Introductionmentioning

confidence: 99%

Influence of Upstream and Downstream Compressor Stators on Rotor Exit Flow Field

Key

2014

International Journal of Rotating Machinery

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Measurements acquired at the rotor exit plane illuminate the interaction of the rotor with the upstream vane row and the downstream vane row. The relative phase of the upstream and downstream vane rows is adjusted using vane clocking so that the effect of the upstream propagating potential field from the downstream stator can be distinguished from the effects associated with the wakes shed from the upstream stator. Unsteady absolute flow angle information shows that the downstream potential field causes the absolute flow angle to increase in the vicinity of the downstream stator leading edge. The presence of Stator 1 wake is also detected at this measurement plane using unsteady total pressure data. The rotor wakes are measured at different circumferential locations across the vane passage, and the influence of Stator 1 wake on the suction side of the rotor wake is evident. Also, the influence of the downstream stator is detected on the pressure side of the rotor wake for a particular clocking configuration. Understanding the role of the surrounding vane rows on rotor wake development will lead to improved comparison between experimental data and results from computational models.

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The Influence of Wake-Wake Interactions on Loss Fluctuations of a Downstream Axial Compressor Blade Row

Cited by 18 publications

References 21 publications

Periodic Transition on an Axial Compressor Stator — Incidence and Clocking Effects: Part II — Transition Onset Predictions

Periodic Transition on an Axial Compressor Stator — Incidence and Clocking Effects: Part II — Transition Onset Predictions

Time Resolved HWA Measurements of the OTL Flow Field From a Shrouded Turbine HP Rotor Blade

Influence of Upstream and Downstream Compressor Stators on Rotor Exit Flow Field

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