Measuring Failures and Correction Methods for Pneumatic Multi-Hole Probes

Hoenen, Herwart; Kunte, Robert; Waniczek, Phillip; Jeschke, Peter

doi:10.1115/gt2012-68113

Cited by 9 publications

(5 citation statements)

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“…Different versions of this correction are in common use, e.g. (Hoenen et al, 2012;Grimshaw and Taylor, 2016). The procedure applied in this investigation is based on Vinnemeier et al (1990).…”

Section: Five-hole-probe Measurementsmentioning

confidence: 99%

On the challenge of five-hole-probe measurements at high subsonic Mach numbers in the wake of transonic turbine cascades

Boerner

Bitter

Niehuis

2018

J. Glob. Power Propuls. Soc.

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Five-hole-probes are common use in turbomachinery flow investigations, even though, inserting a probe into a flow field inevitably induces perturbations to the flow which can falsify the measurement results, especially when exposed to transonic flows. The objective of the investigations presented here is to evaluate the Mach number measurements of a five-hole-probe (5HP) in the wake flow of a transonic turbine cascade at engine relevant Reynolds numbers by comparing them to the results of particle image velocimetry (PIV). Furthermore, PIV measurements were performed with inserted probe to investigate the influence of the probe on the wake flow field. Together with a sensitivity study of 5HP measurements in flow regimes close to Ma = 1, the results demonstrate how the measurement uncertainty can be improved in high subsonic flow regimes.

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Section: Five-hole-probe Measurementsmentioning

confidence: 99%

On the challenge of five-hole-probe measurements at high subsonic Mach numbers in the wake of transonic turbine cascades

Boerner

Bitter

Niehuis

2018

J. Glob. Power Propuls. Soc.

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“…Hoenen et al [6] studied the effect of the pressure gradients on the pneumatic probe measurements using a five-hole probe downstream of a symmetric NACA-65 profile located in front of a nozzle. Tests were conducted at two different Mach numbers (0.3 and 0.5) and at several axial distances between airfoil trailing edge and probe.…”

Section: Introductionmentioning

confidence: 99%

Vane–Probe Interactions in Transonic Flows

Torre

Patinios

Lopes

et al. 2023

Journal of Turbomachinery

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In this paper, a numerical investigation of the effect of a miniaturized five-hole probe downstream of a transonic low-pressure turbine vane row is presented. Firstly, a numerical calibration of the probe was performed. The effect of the probe on the flow-field throughout the vane segments was then evaluated by performing a comparison between a setup with vanes-only (no probe) and with vanes and probe. To assess the accuracy of the quantities ‘measured’ by the probe, the probe-determined flow-field was compared to the flow-field of the vanes-only setup. A non-negligible modification of the probe-determined local distributions of Mach number, yaw and pitch angle is revealed with respect to the undisturbed flow. A correction is used to account for the effects of the non-uniformity of the flow and its impact is evaluated on 2D and 3D flow regions. A significative effect of the correction was found on the probe-determined yaw angle, in which the difference from the vanes-only data was reduced to below 1 degree, except near the endwalls where larger discrepancies remain due to probe-endwall interactions. A shortfall of the correction was instead observed on the probe-determined Mach numbers. Finally, the pitch-wise averaged quantities were evaluated. It was observed that the highest differences between probe-determined and undisturbed data occur where radial gradients of total pressure are stronger and that the correction had almost negligible impact on the pitch-wise averaged quantities.

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“…Hoenen et al [6] studied the effect of the pressure gradients on the pneumatic probe measurements using a five-hole probe downstream of an asymmetric NACA-65 profile located in front of a nozzle. Tests were conducted at two different Mach numbers (0.3 and 0.5) and at several axial distances between airfoil trailing edge and probe.…”

Section: Introductionmentioning

confidence: 99%

Vane-Probe Interactions in Transonic Flows

Torre

Patinios

Lopes

et al. 2022

Volume 2: Coal, Biomass, Hydrogen, and Alternative Fuels; Controls, Diagnostics, and Instrumentation; Steam Turbine

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In this paper, a numerical investigation of the effect of a miniaturized five-hole probe downstream of a transonic low-pressure turbine vane row is presented. Firstly, a numerical calibration of the probe was performed in uniform flow conditions, as is the case for any traditional calibration, for a wide range of Mach number, yaw and pitch angle conditions. The effect of the probe on the general flow-field throughout the turbine vane segments was then evaluated by performing a comparison between a set-up with vanes-only (no probe) and with vanes and probe. It was found that, as the probe traverse downstream the vane, the probe impact on the vane isentropic Mach number depends on the probe circumferential position. The highest impact was observed when the probe is located at the upper mid passage (θ = 0.5), consisting on a relatively small reduction of the isentropic Mach number on the vane suction side of just 0.02. To assess the accuracy of the quantities ‘measured’ by the probe, the probe-determined flow-field was compared to the flow-field of the vanes-only set-up. A non-negligible modification of the probe-determined local distributions of Mach number, yaw and pitch angle is revealed with respect to the undisturbed flow. Further investigation involving stagnation point tracking showed that the artificial high circumferential variation of the yaw angle is not caused by a modification of the vane outlet flow angle, but is induced by non-uniform flow conditions downstream of the vanes. With knowledge of the above, a two-step correction is used to account for the effects of the non-uniformity of the flow and its impact is evaluated on 2D and 3D flow regions. A significative effect of the correction was found on the probe-determined yaw angle, in which the difference from the vanes-only data was reduced to below 1 degree, except near the endwalls where larger discrepancies remain due to probe-endwall interactions. A shortfall of the correction was instead observed on the probe-determined Mach numbers. Finally, the pitch-wise averaged quantities were evaluated. It was observed that the highest differences between probe-determined and undisturbed data occur where radial gradients of total pressure are stronger and that the two-step correction had almost negligible impact on the pitch-wise averaged quantities.

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Measuring Failures and Correction Methods for Pneumatic Multi-Hole Probes

Cited by 9 publications

References 0 publications

On the challenge of five-hole-probe measurements at high subsonic Mach numbers in the wake of transonic turbine cascades

On the challenge of five-hole-probe measurements at high subsonic Mach numbers in the wake of transonic turbine cascades

Vane–Probe Interactions in Transonic Flows

Vane-Probe Interactions in Transonic Flows

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