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Technical Brief

A New Particle Image Velocimetry Technique for Turbomachinery Applications

[+] Author and Article Information
Sayantan Bhattacharya

School of Mechanical Engineering,
Purdue University,
585 Purdue Mall,
West Lafayette, IN 47907
e-mail: bhattac3@purdue.edu

Reid A. Berdanier

Mem. ASME
School of Mechanical Engineering,
Purdue University,
500 Allison Road,
West Lafayette, IN 47907
e-mail: rberdani@gmail.com

Pavlos P. Vlachos

Professor
School of Mechanical Engineering,
Purdue University,
585 Purdue Mall,
West Lafayette, IN 47907
e-mail: pvlachos@purdue.edu

Nicole L. Key

Mem. ASME
Associate Professor
School of Mechanical Engineering,
Purdue University,
500 Allison Road,
West Lafayette, IN 47907
e-mail: nkey@purdue.edu

1Corresponding author.

Manuscript received July 20, 2015; final manuscript received May 13, 2016; published online June 1, 2016. Assoc. Editor: Jim Downs.

J. Turbomach 138(12), 124501 (Jun 01, 2016) (4 pages) Paper No: TURBO-15-1164; doi: 10.1115/1.4033672 History: Received July 20, 2015; Revised May 13, 2016

Nonintrusive measurement techniques such as particle image velocimetry (PIV) are growing in both capability and utility for turbomachinery applications. However, the restrictive optical access afforded by multistage research compressors typically requires the use of a periscope probe to introduce the laser sheet for measurements in a rotor passage. This paper demonstrates the capability to perform three-dimensional PIV in a multistage compressor without the need for intrusive optical probes and requiring only line-of-sight optical access. The results collected from the embedded second stage of a three-stage axial compressor highlight the rotor tip leakage flow, and PIV measurements are qualitatively compared with high-frequency response piezoresistive pressure measurements to assess the tip leakage flow identification.

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Figures

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Fig. 1

(a) Schematic of the PIV setup with window, camera, and laser positions and (b) schematic showing flow direction, phase-locked measurement planes covering the blade passage, and the expected tip leakage flow

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Fig. 2

Schematic of the flow seeding method

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Fig. 3

Volume slices of the normalized radial velocity at fixed spanwise locations for stereo reconstructed velocity field

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Fig. 4

Comparison of PIV results with over-rotor static pressures. Flow is from left to right. (a) Contours of the normalized radial velocity near the wall, (b) over-rotor static pressure contours, and (c) both methods superimposed with PIV normalized radial velocities as flood contours and static pressure contours represented as lines.

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