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Gas Turbines: Controls, Diagnostics, and Instrumentation

A High Temperature High Bandwidth Fast Response Total Pressure Probe for Measurements in a Multistage Axial Compressor

[+] Author and Article Information
Mehmet Mersinligil

Turbomachinery and Propulsion Department,  von Kármán Institute for Fluid Dynamics, 72, Chaussée de Waterloo B-1640 Rhode-Saint-Genèse, Belgiummersinli@vki.ac.be

Jean-François Brouckaert

Turbomachinery and Propulsion Department,  von Kármán Institute for Fluid Dynamics, 72, Chaussée de Waterloo B-1640 Rhode-Saint-Genèse, Belgiumbrouckaert@vki.ac.be

Nicolas Courtiade

 Laboratoire de Mécanique des Fluides et d’Acoustique,  École Centrale de Lyon, 36, Avenue Guy de Collongue, 69 130 Écully, Francenicolas.courtiade@ec-lyon.fr

Xavier Ottavy

 Laboratoire de Mécanique des Fluides et d’Acoustique,  École Centrale de Lyon, 36, Avenue Guy de Collongue, 69 130 Écully, FranceXavier.Ottavy@ec-lyon.fr

J. Eng. Gas Turbines Power 134(6), 061601 (Apr 12, 2012) (11 pages) doi:10.1115/1.4006061 History: Revised October 24, 2011; Accepted January 13, 2012; Published April 10, 2012; Online April 12, 2012

Over the last decades, fast response aerodynamic probes have been recognized as a robust measurement technique to provide time-resolved flow field data in turbomachinery environments. Still, most of the existing probe designs are restricted to low temperature applications (<120 °C) either because of sensor temperature range limitations or packaging issues. Measurements in turbomachines also require a small probe size often with a very high bandwidth which are conflicting constraints difficult to satisfy simultaneously. This contribution therefore presents the development of a novel miniature (∅ 2.5 mm ) high temperature single sensor total pressure probe, designed for operation up to 250 °C with a very high bandwidth of 250 kHz. The probe main element is a 1.7 mm diameter commercial piezoresistive transducer placed in a Pitot type arrangement with a flush mounted sensor to provide the highest bandwidth. The details of the probe design are presented as well as the probe calibrations in pressure and in temperature. The effects of using a thermal compensation module or a sense resistor to monitor the temperature drift are described in the context of measurement uncertainty. The probes were characterized in terms of aerodynamic characteristics versus flow angle and Mach number. Shock tube tests have shown a dynamic response of the probe with sensor resonance frequencies well over 300 kHz, with a flat frequency range up to 250 kHz. Two probe prototypes were manufactured and first used in the 3½-stage high speed axial compressor CREATE of the LMFA at École Centrale de Lyon in France. The probes were traversed at each interblade row plane up to temperatures of 180 °C and absolute pressure of 3 bars. The probe was able to resolve the high blade passing frequencies (∼16 kHz) and several harmonics including rotor-stator interaction frequencies up to 200 kHz. Besides the average total pressure distributions from the radial traverses, phase-locked averages and random unsteadiness are presented. The probe spatial and temporal resolutions are discussed in the context of those results.

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Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Closeup and general view of the probe

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Figure 2

Kulite piezoresistive SOI pressure sensor [15]

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Figure 3

Amplifier circuit diagram showing pressure and temperature outputs

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Figure 4

Meridional view of the CREATE compressor

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Figure 5

Power spectrum density downstream of the second rotor using probe 510 using ECL acquisition system (fs  = 500 kHz) and VKI acquisition system (fs  = 1 MHz)

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Figure 6

Repeatability of the measurement of the pressure fluctuations over the time period of the compressor, section 28A, 73.7% of the blade height

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Figure 7

Steady pneumatic versus time averaged measurements for three spanwise positions, sections 270 and 27A

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Figure 8

Nondimensional total pressure and standard deviation in the six inter-row sections at the reference time

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Figure 9

Discrete Fourier transform distributions in the spanwise direction in the six inter-row sections

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