Measurement techniques for unsteady flows in turbomachines

Sieverding, C. H.; Arts, Tony; Dénos, R.; Brouckaert, Jean-François

doi:10.1007/s003480050390

Cited by 79 publications

(25 citation statements)

References 50 publications

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“…Various philosophies were followed regarding probe geometries, but over the years, and along with the evolution of piezoresistive sensors, lots of efforts were invested in probe miniaturization and increase of bandwidth. For a detailed and comprehensive review of fast response pressure probe development, the reader is referred to the papers of Sieverding et al [5], Kupferschmied et al [6], or Ainsworth et al [7]. Due to the use of first generation silicon sensors, most ofthe probe designs described in these contributions are limited to low temperature applications (i.e., below 120 °C), above which, current expansion.…”

Section: Introductionmentioning

confidence: 99%

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

Mersinligil

Brouckaert

Courtiade

et al. 2012

Journal of Engineering for Gas Turbines and Power

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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 (0 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 ofthe 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 ofthe 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 V/j-stage high speed axial compressor CREATE ofthe LMFA at Ecole 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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Section: Introductionmentioning

confidence: 99%

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

Mersinligil

Brouckaert

Courtiade

et al. 2012

Journal of Engineering for Gas Turbines and Power

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“…It is vital to measure and understand the flow behaviors in the turbo-machinery, such as pump, water or steam turbine, turbo-compressor and so on, where the flow has severe three-dimensional (3-D) and unsteady characteristics. 1 There are many instruments to measure the flow velocity fields. Hot-wire & hot-film anemometry (HWFA), Laser Doppler velocimetry (LDV), and particle image velocimetry (PIV) are the most advanced popular instruments.…”

Section: Introductionmentioning

confidence: 99%

Study on Multihole Pressure Probe System Based on LabVIEW

2013

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The multihole pressure probes are widely used to determine flow velocity vectors and pressures in the fluid machinery fields due to their robustness, convenience, and economy in flow measurement. Accuracy and fast calibration of a multihole pressure probe is very important. In this article, a multihole pressure probe automatic calibration system is developed. The hardware device mainly consists of computer, motion control equipment and data acquisition (DAQ) equipment, and the software program is developed using the Glanguage based on LabVIEW platform. The fundamental theory and method of multihole pressure probes is reviewed, as well as about how to take into account the compressibility effect of the fluid. The developed system can be easily integrated by engineers in research institutes or industries, without requiring more expertise in programming or multihole probe measurement method. Furthermore, the system is used for a five-hole probe's calibration and measurement, satisfactory results are obtained. 0.5 • is the maximum uncertainty for the flow angles and 1.7% is for the velocity magnitude. The measurement biases being caused by the effect of Reynolds number are investigated. In the Reynolds number range of 1.06 × 10 4 to 4.29 × 10 4 , the measurement biases of velocity vector are presented.

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“…In particular, unsteady aerodynamic phenomena in the compressor such as rotating stall, rotor / stator interaction, and flutter need to be measured and evaluated. Ainsworth et al 1 and Sieverding et al 2 have done significant work in developing embedded semiconductor sensors to measure these unsteady pressure fluctuations. Semi-conductor sensors, however, are only capable of providing discrete point measurements.…”

Section: Introductionmentioning

confidence: 99%

42nd AIAA Aerospace Sciences Meeting and Exhibit

2004

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This work details the development and application of porous pressure-sensitive paint (PSP) for measuring unsteady surface pressures in turbomachinery. The advantages of porous PSP over conventional methods include global pressure measurement, fast response time, and instrumentation of thin turbomachinery components that are otherwise difficult or impossible to instrument. In this paper, the development, calibration, and application of porous PSP to turbomachinery are discussed. Porous PSP formulations were developed to ensure fast response times and good adhesion characteristics to rotating parts. Experimental methods such as phase-locking and image registration were developed to acquire quality data. Dynamic response calibrations of PSP with a fluidic oscillator were performed, indicating that porous PSP formulations have a response time of up to 40 kHz. For a turbomachinery application, the inlet wall and impeller blades of a turbocharger compressor were painted with fast-responding polymer/ceramic PSP. The turbocharger was operated at 100,000 rpm, corresponding to a blade-passage frequency (BPF) of 10 kHz. Even at this high speed and BPF, porous PSP was able to resolve the unsteady wall pressure distributions about the blade. In addition, a flow blockage was created to induce an inlet flow distortion on the compressor. Porous PSP was able to resolve the 1.67 kHz unsteady blade loading. Potential applications of porous PSP to unsteady turbomachinery testing include evaluations of rotor/stator interaction, flutter, inlet flow distortion, rotating stall, and surge.

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Measurement techniques for unsteady flows in turbomachines

Cited by 79 publications

References 50 publications

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

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

Study on Multihole Pressure Probe System Based on LabVIEW

42nd AIAA Aerospace Sciences Meeting and Exhibit

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