Research Papers

Unsteady Pressure Measurement on Oscillating Blade in Transonic Flow Using Fast-Response Pressure-Sensitive Paint

[+] Author and Article Information
Toshinori Watanabe

Department of Aeronautics and Astronautics,
The University of Tokyo,
Tokyo 113-8656, Japan
e-mail: watanabe@aero.t.u-tokyo.ac.jp

Toshihiko Azuma

School of Engineering,
The University of Tokyo,
Tokyo 113-8656, Japan

Seiji Uzawa, Takehiro Himeno, Chihiro Inoue

Department of Aeronautics and Astronautics,
The University of Tokyo,
Tokyo 113-8656, Japan

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 23, 2017; final manuscript received November 13, 2017; published online April 18, 2018. Editor: Kenneth Hall.

J. Turbomach 140(6), 061003 (Apr 18, 2018) (8 pages) Paper No: TURBO-17-1196; doi: 10.1115/1.4039180 History: Received October 23, 2017; Revised November 13, 2017

A fast-response pressure-sensitive paint (PSP) technique was applied to the measurement of unsteady surface pressure of an oscillating cascade blade in a transonic flow. A linear cascade was used, and its central blade was oscillated in a translational manner. The unsteady pressure distributions of the oscillating blade and two stationary neighbors were measured using the fast-response PSP technique, and the unsteady aerodynamic force on the blade was obtained by integrating the data obtained on the pressures. The measurements made with the PSP technique were compared with those obtained by conventional methods for the purpose of validation. From the results, the PSP technique was revealed to be capable of measuring the unsteady surface pressure, which is used for flutter analysis in transonic conditions.

Copyright © 2018 by ASME
Topics: Pressure , Blades
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Fig. 6

Data processing of measurements made on the blades coated with PSP

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Fig. 5

Illuminated blade coated with PSP in the test section

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Fig. 4

Measurement system

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Fig. 3

Preparation process of the AA-PSP blade

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Fig. 1

Transonic linear cascade tunnel

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Fig. 7

Double circular arc blade with pressure taps

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Fig. 8

Blade with a strain gauge

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Fig. 9

Shadowgraph image of the cascade flow

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Fig. 10

Cp distribution at the midspan

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Fig. 11

Steady Cp distribution measurement: (a) blade 0 (P.S.) and (b) blade 0 (S.S.)

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Fig. 12

Oil flow visualization (central blade, suction surface)

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Fig. 13

Steady aerodynamic force (results of PSP and strain gauge measurements)

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Fig. 15

Cp distributions as a function of time: (a) blade 0 (S.S.) and (b) blade +1 (P.S.)

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Fig. 16

Unsteady aerodynamic force measured by the PSP technique and a strain gauge: (a) amplitude and (b) phase shift

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Fig. 14

Unsteady Cp distribution as measured with the PSP technique: (a) blade 0 (S.S.), Cp(Re), (b) blade 0 (S.S.), Cp(Im), (c) blade +1 (P.S.), Cp(Re), and (d) blade +1 (P.S.), Cp(Im)




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