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.

References

References
1.
Aotsuka
,
M.
, and
Murooka
,
T.
,
2014
, “
Numerical Analysis of Fan Transonic Stall Flutter
,”
ASME
Paper No. GT2014-26703.
2.
Holzinger
,
F.
,
Wartzek
,
F.
,
Juengst
,
M.
,
Schiffer
,
H.-P.
, and
Leichtfuss
,
S.
,
2015
, “
Self-Excited Blade Vibration Experimentally Investigated in Transonic Compressors: Rotating Instabilities and Flutter
,”
ASME
Paper No. GT2015-43628.
3.
Vogt
,
D.
,
2005
, “
Experimental Investigation of Three-Dimensional Mechanisms in Low-Pressure Turbine Flutter
,”
Ph.D. thesis
, Royal Institute of Technology KTH, Stockholm, Sweden.
4.
Liu
,
T.
, and
Sullivan
,
J. P.
,
2005
,
Pressure and Temperature Sensitive Paint
,
Springer
,
New York
.
5.
Kameda
,
M.
,
Tabei
,
T.
,
Nakakita
,
K.
,
Sakaue
,
H.
, and
Asai
,
K.
,
2005
, “
Image Measurements of Unsteady Pressure Fluctuation by a Pressure-Sensitive Coating on Porous Anodized Aluminum
,”
Meas. Sci. Technol.
,
16
(
12
), pp.
2517
2524
.
6.
Gregory
,
J. W.
,
Sakaue
,
H.
,
Liu
,
T.
, and
Sullivan
,
J. P.
,
2014
, “
Fast Pressure-Sensitive Paint for Flow and Acoustic Diagnostics
,”
Annu. Rev. Fluid Mech.
,
46
(
1
), pp.
303
330
.
7.
Nakakita
,
K.
, and
Asai
,
K.
,
2002
, “
Pressure-Sensitive Paint Application to a Wing-Body Model in a Hypersonic Shock Tunnel
,”
AIAA
Paper No. 2002-2911.
8.
Marienne
,
M.-C.
,
Molton
,
P.
,
Bur
,
R.
, and
Sant
,
Y. L.
,
2015
, “
Pressure-Sensitive Paint Application to an Oscillating Shock Wave in a Transonic Flow
,”
AIAA J.
,
53
(
11
), pp.
3208
3220
.
9.
Gregory
,
J. W.
,
2004
, “
Porous Pressure-Sensitive Paint for Measurement of Unsteady Pressures in Turbomachinery
,”
AIAA
Paper No. 2004-294.
10.
Fransson
,
T.
,
2013
, “
Flutter-Free Turbomachinery Blades (FUTURE)
,” EU Publications Office, Luxembourg, UK, Project Final Report No. FTR-5-93.
11.
Azuma
,
T.
,
Watanabe
,
T.
,
Himeno
,
T.
,
Uzawa
,
S.
,
Inoue
,
C.
,
Takahashi
,
Y.
,
Shibata
,
T.
, and
Takeda
,
H.
,
2015
, “
Unsteady Pressure Measurement on Oscillating Blade With Pressure-Sensitive Paint
,”
International Gas Turbine Congress (IGTC)
, Tokyo, Japan, Paper No. ThPME.3.
12.
Aotsuka
,
M.
,
Watanabe
,
T.
, and
Machida
,
Y.
,
2003
, “
Role of Shock and Boundary Layer Separation on Unsteady Aerodynamic Characteristics of Oscillating Transonic Cascade
,”
ASME
Paper No. GT2003-38425.
13.
Sakaue
,
H.
, and
Sullivan
,
J. P.
,
2000
, “
Fast Response Time Characteristics of Anodized Aluminum Pressure Sensitive Paint
,”
AIAA
Paper No. 2000-0506.
14.
Azuma
,
T.
,
2016
, “
Measurement of Unsteady Surface Pressure Distribution on Oscillating Cascade Blade With Pressure-Sensitive Paint
,” Master thesis, The University of Tokyo, Tokyo, Japan (in Japanese).
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