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Research Papers: Gas Turbines: Heat Transfer

Development of a Fast-Response Aerodynamic Pressure Probe Based on a Waveguide Approach

[+] Author and Article Information
Andrea Fioravanti

Department of Industrial Engineering,
University of Florence,
Via S. Marta, 3,
Florence 50139, Italy
e-mail: andrea.fioravanti@unifi.it

Giulio Lenzi

Department of Industrial Engineering,
University of Florence,
Via S. Marta, 3,
Florence 50139, Italy
e-mail: giulio.lenzi@unifi.it

Giovanni Ferrara

Department of Industrial Engineering,
University of Florence,
Via S. Marta, 3,
Florence 50139, Italy
e-mail: giovanni.ferrara@unifi.it

Lorenzo Ferrari

National Research Council of Italy
(CNR-ICCOM),
Department of Industrial Engineering,
University of Florence,
Via S. Marta, 3,
Florence 50139, Italy
e-mail: lorenzo.ferrari@iccom.cnr.it

Contributed by the Controls, Diagnostics and Instrumentation Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 6, 2016; final manuscript received July 12, 2016; published online September 27, 2016. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(3), 031902 (Sep 27, 2016) (11 pages) Paper No: GTP-16-1311; doi: 10.1115/1.4034451 History: Received July 06, 2016; Revised July 12, 2016

Currently, fast-response aerodynamic probes are widely used for advanced experimental investigations in turbomachinery applications. The most common configuration is a virtual three-hole probe. This solution is a good compromise between probe dimension and accuracy. Several authors have attempted to extend the capabilities of these probes in terms of bandwidth and operating conditions. Even though differences exist between the solutions in the literature, all of the designs involve the positioning of a dynamic pressure sensor close to the measurement point. In general terms, the higher the frequency response, the more the sensor is exposed to the flow. This physical constraint puts a limit on the probe applicability since the measurement conditions have to comply with the maximum allowed operating conditions of the sensor. In other applications, when the conditions are particularly harsh and a direct measurement is not possible, a waveguide probe is commonly used to estimate the local pressure. In this device, the sensor is connected to the measurement point through a transmitting duct which guarantees that the sensor is operating in a less critical condition. Generally, the measurement is performed through a pressure tap and particular attention must be paid to the probe design in order to have an acceptable frequency response function. In this study, the authors conceived, developed, and tested a probe which combines the concept of a fast-response aerodynamic pressure probe with that of a waveguide probe. Such a device exploits the benefits of having the sensor far from the harsh conditions while maintaining the capability to perform an accurate flow measurement.

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References

Figures

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Fig. 1

Sketch of the modified waveguide probe (dimensions in millimeters)

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Fig. 2

Sketch of the sensor housing (dimensions in millimeters)

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Fig. 3

Picture of the probe head

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Fig. 4

Detail of sensor housing

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Fig. 5

Full view of the probe (w/o damping duct)

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Fig. 6

Scheme of the waveguide probe with the standard head (dimensions in millimeters)

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Fig. 7

Scheme of the waveguide probe with the modified head (dimensions in millimeters)

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Fig. 8

Attenuation predicted by the numerical model for the standard waveguide probe simplified (WGP-S) and modified (WSG-M) waveguide probe

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Fig. 9

Experimental and numerical attenuation for the standard waveguide probe (WGP-S)

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Fig. 10

Experimental attenuation for the standard (WGP-S) and modified (WSG-M) waveguide probe

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Fig. 11

Experimental and numerical attenuation for the modified waveguide probe (WGP-M)

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Fig. 12

Phase shift between the calibration signal and that measured at the sensor section

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Fig. 13

Trend of the CP coefficient for the tested probe as a function of the yaw angle

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Fig. 14

Trend of the coefficient as a function of the yaw angle

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Fig. 15

Trend of KS coefficient as a function of the yaw angle

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Fig. 16

Trend of the KT coefficient as function of the yaw angle

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Fig. 17

Centrifugal blower facility and probe measurement position

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Fig. 18

Measured and corrected signals at position p1 (at midspan)

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Fig. 19

Yaw angle and total and static pressures at midspan

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Fig. 20

Yaw angle referenced to radial direction over a revolution

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Fig. 21

Normalized static pressure over a revolution

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Fig. 22

Normalized total pressure over a revolution

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Fig. 23

Absolute velocity over a revolution

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Fig. 24

Attenuations predicted by the numerical model for the modified waveguide probe (WSG-M) with different dimensions of the transmitting duct diameter (Φ) and length (L)

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