In order to advance the technology for measurements in higher temperature flows, a novel miniature (diameter 2.5 mm) fast response probe that can be applied in flows with temperatures of up to 533 K has been developed. The primary elements of the probe are two piezoresistive pressure transducers that are used to measure the unsteady pressure and unsteady velocity field, as well as the steady temperature. Additional temperature and strain gauge sensors are embedded in the shaft to allow a much higher degree of robustness in the use of this probe. The additional temperature sensor in the shaft is used to monitor and correct the heat flux through the probe shaft, facilitating thermal management of the probe. The strain gauge sensor is used to monitor and control probe shaft vibration. Entirely new packaging technology had to be developed to make possible the use of this probe at such high temperatures. Extensive calibration and thermal cycling of the probe used to bind the accuracy and the robustness of the probe. This novel probe is applied in the one-and-1/2-stage, unshrouded axial turbine at ETH Zurich; this turbine configuration is representative of a high work aero-engine. The flow conditioning stretch upstream of the first stator is equipped with a recently designed hot streak generator. Several parameters of the hot streak, including temperature, radial and circumferential position, and shape and size can be independently controlled. The interactions between the hot streak and the secondary flow present a perfect scenario to verify the probe’s capability to measure under real engine conditions. Therefore, measurements with the novel probe have been made in order to prove the principle and to detail the interaction effects with blade row pressure gradients and secondary flows.
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January 2011
Research Papers
High Temperature Fast Response Aerodynamic Probe
Christian Lenherr,
Christian Lenherr
Department of Mechanical and Process Engineering, Laboratory for Energy Conversion,
e-mail: lenherr@lec.mavt.ethz.ch
ETH Zurich
, Sonneggstr.3, 8092 Zurich, Switzerland
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Anestis I. Kalfas,
Anestis I. Kalfas
Aristotle University of Thessaloniki
, School of Engineering, 54124 Thessaloniki, Greece
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Reza S. Abhari
Reza S. Abhari
Department of Mechanical and Process Engineering, Laboratory for Energy Conversion,
ETH Zurich
, Switzerland
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Christian Lenherr
Department of Mechanical and Process Engineering, Laboratory for Energy Conversion,
ETH Zurich
, Sonneggstr.3, 8092 Zurich, Switzerlande-mail: lenherr@lec.mavt.ethz.ch
Anestis I. Kalfas
Aristotle University of Thessaloniki
, School of Engineering, 54124 Thessaloniki, Greece
Reza S. Abhari
Department of Mechanical and Process Engineering, Laboratory for Energy Conversion,
ETH Zurich
, SwitzerlandJ. Eng. Gas Turbines Power. Jan 2011, 133(1): 011603 (10 pages)
Published Online: September 17, 2010
Article history
Received:
April 8, 2010
Revised:
April 13, 2010
Online:
September 17, 2010
Published:
September 17, 2010
Citation
Lenherr, C., Kalfas, A. I., and Abhari, R. S. (September 17, 2010). "High Temperature Fast Response Aerodynamic Probe." ASME. J. Eng. Gas Turbines Power. January 2011; 133(1): 011603. https://doi.org/10.1115/1.4001824
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