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TECHNICAL PAPERS

On the Development and Application of the Fast-Response Aerodynamic Probe System in Turbomachines—Part 1: The Measurement System

[+] Author and Article Information
Peter Kupferschmied, Pascal Köppel, Christian Roduner, Georg Gyarmathy

Turbomachinery Laboratory, Institute of Energy Technology, ETH—Swiss Federal Institute of Technology, 8092 Zurich, Switzerland http://www.lsm.ethz.ch

J. Turbomach 122(3), 505-516 (Feb 01, 1999) (12 pages) doi:10.1115/1.1303702 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

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Figures

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Piezoresistive miniature pressure sensor chip
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Typical excitation and output signals of a piezoresistive pressure sensor chip (Sensym P788, Ie=1 mA)
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Alteration of the amplitude and phase response due to bridge resistance Re and cable length L17
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Fast-response probe design and development steps
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Schematic view of the sensor chip location in a cylindrical fast-response probe
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Left: tips of one- and three-sensor probes C1LS18 and C3LS18 (tip diameter 1.80 mm, prismatic shaft diameter 3.0 mm); right: tip of one-sensor pitot probe P1S08 (diameter 0.84 mm)
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Pressure signal zero and short-time stability of a typical sensor during three temperature cycles (three-sensor fast-response aerodynamic probe C3S18, T=12[[ellipsis]]92°C,Δt=510 h)
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Long-term stability of the indicated temperature (fast-response aerodynamic probe C1S18#12, four temperature steps of 6 h, T=35[[ellipsis]]92°C)
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Overtemperature due to self-heating of a one-sensor fast-response aerodynamic probe C1S18#13 and model results (solid lines)
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Dynamic response of a miniature pressure sensor in a recessed cavity 32
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Indicated pressure zero after temperature changes of ±60 K and after a step of +60 K; fast-response aerodynamic probe C1S18#12
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Reconstructed pressure and temperature signals of fast-response aerodynamic probe C1S18#12: standard deviations of the residuals (left) and minimum and maximum residuals (right)
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Vertical-nozzle free jet facility (diameter 100 mm) for the calibration of aerodynamic probes; probe frame of reference: yaw-pitch system (as defined by 33)
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Aerodynamic coefficients of a three-hole probe (C3S18P, diameter 1.80 mm, M=0.30). Each mesh node is a calibration point. The frame of reference of the probe is defined in Fig. 13 (right).
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Difference between flow total temperature and indicated probe temperature; resulting effective recovery factor; fast-response aerodynamic probe C1S18#12
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Angular distribution with poles (zero lines) of the denominator Cp1−(Cp2+Cp3)/2 of three-hole probe C3P18
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Calibration surfaces φ(Kφ,Kγ) and γ(Kφ,Kγ) of a cylindrical four-hole probe 34
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Accuracy of the yaw and pitch angle evaluation model depending on polynomial degrees (m,n) and angular range
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One-sensor probe used in the pseudo-three-sensor mode
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Description of the three-sensor probe mode
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Residuals of a sensor evaluation: during calibration (C) and four following temperature cycles; fast-response aerodynamic probe C1S18#12
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Configuration of the fast-response aerodynamic probe system for time-resolved measurements in turbomachines
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Flow chart of the standard data evaluation software

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