The flow instability always varies within different compressors; however, even in one compressor, there may be still multiple various unsteady modes. To study the triggering mechanism for these unsteady modes, a detailed experimental research on an industrial centrifugal compressor with variable vaned diffuser is performed from design point to surge. The multiposition dynamic pressure measurement is conducted during the whole valve-adjusting process. The characteristics of pressure fields under some specific operating conditions are focused on, especially the prestall, stall and surge conditions. According to the collected data, the features of different unsteady modes can be obtained, such as the surge pattern and the propagation direction of stall cells. In addition, when the diffuser vane setting angle (DVA) is adjusted, the core factors to trigger total instability will change. To better complement the experimental analysis, a multipassage numerical simulation is carried out. Based on the agreement of performance curves obtained by the two methods, the flow field characteristics in the prestall state shown in the simulation results are indeed a good complement to the dynamic experimental analysis. Meanwhile, with the help of dynamic mode decomposition (DMD) method, a few low-frequency unsteady structures are extracted from the transient numerical result over a long time, which correlate with the experimental result. Through detailed analysis, an insight into the different unsteady modes in a centrifugal compressor with variable vaned diffuser is obtained.

References

References
1.
Greitzer
,
E. M.
,
1981
, “
The Stability of Pumping System—The 1980 Freeman Scholar Lecture
,”
ASME J. Fluids Eng.
,
103
(
2
), pp.
193
242
.
2.
Haynes
,
J. M.
,
Hendricks
,
G. K.
, and
Epstein
,
A. H.
,
1994
, “
Active Stabilization of Rotating Stall in a Three-Stage Axial Compressor
,”
ASME J. Turbomach.
,
116
(
2
), pp.
226
239
.
3.
Lawless
,
P. B.
, and
Fleeter
,
S.
,
1993
, “
Rotating Stall Acoustic Signature in a Low-Speed Centrifugal Compressor—Part 2: Vaned Diffuser
,”
ASME
Paper No. 93-GT-254.
4.
Spakovszky
,
Z. S.
, and
Roduner
,
C. H.
,
2009
, “
Spike and Modal Stall Inception in an Advanced Turbocharger Centrifugal Compressor
,”
ASME J. Turbomach.
,
131
(
3
), p.
031012
.
5.
Skoch
,
G. J.
,
2003
, “
Experimental Investigation of Centrifugal Compressor Stabilization Techniques
,”
ASME J. Turbomach.
,
125
(
4
), pp.
704
713
.
6.
Spakovszky
,
Z. S.
,
2004
, “
Backward Traveling Rotating Stall Waves in Centrifugal Compressors
,”
ASME J. Turbomach.
,
126
(
1
), pp.
1
12
.
7.
Zheng
,
X.
,
Sun
,
Z.
,
Kawakubo
,
T.
, and
Tamaki
,
H.
,
2017
, “
Experimental Investigation of Surge and Stall in a Turbocharger Centrifugal Compressor With a Vaned Diffuser
,”
Exp. Therm. Fluid Sci.
,
82
, pp.
493
506
.
8.
Tamaki
,
H.
,
2017
, “
Experimental Study on the Effect of Diffuser Vane Setting Angle on Centrifugal Compressor Performance
,”
ASME J. Turbomach.
,
139
(
6
), p.
061001
.
9.
Marsan
,
A.
,
Trébinjac
,
I.
,
Coste
,
S.
, and
Leroy
,
G.
,
2014
, “
Influence of Unsteadiness on the Control of a Hub-Corner Separation Within a Radial Vaned Diffuser
,”
ASME J. Turbomach.
,
137
(
2
), p.
021008
.
10.
Ohta
,
Y.
, and
Fujisawa
,
N.
,
2014
, “
Unsteady Behavior and Control of Vortices in Centrifugal Compressor
,”
J. Therm. Sci.
,
23
(
5
), pp.
401
411
.
11.
Fujisawa
,
N.
,
Ikezu
,
S.
, and
Ohta
,
Y.
,
2016
, “
Structure of Diffuser Stall and Unsteady Vortices in a Centrifugal Compressor With Vaned Diffuser
,”
ASME
Paper No. GT2016-56154.
12.
Zhao
,
Y.
,
Zhao
,
J.
,
Wang
,
Z.
, and
Xi
,
G.
,
2017
, “
Numerical Investigation of Diffuser Flow Field and Rotating Stall in a Centrifugal Compressor With Vaned Diffuser
,”
ASME
Paper No. GT2017-63913.
13.
Furukawa
,
M.
,
Saiki
,
K.
,
Yamada
,
K.
, and
Inoue
,
M.
,
2000
, “
Unsteady Flow Behavior Due to Breakdown of Tip Leakage Vortex in an Axial Compressor Rotor at Near-Stall Condition
,”
ASME
Paper No. 2000-GT-0666.
14.
Mailach
,
R.
,
Lehmann
,
I.
, and
Vogeler
,
K.
,
2001
, “
Rotating Instabilities in an Axial Compressor Originating From the Fluctuating Blade Tip Vortex
,”
ASME J. Turbomach.
,
123
(
3
), pp.
453
463
.
15.
Fujisawa
,
N.
,
Ema
,
D.
, and
Ohta
,
Y.
,
2017
, “
Unsteady Behavior of Diffuser Stall in a Centrifugal Compressor With Vaned Diffuser
,”
ASME
Paper No. GT2017-63400.
16.
Fujisawa
,
N.
,
Inui
,
T.
, and
Ohta
,
Y.
,
2018
, “
Evolution Process of Diffuser Stall in a Centrifugal Compressor With Vaned Diffuser
,”
ASME
Paper No. GT2018-75462.
17.
Cizmas
,
P. G.
, and
Palacios
,
A.
,
2003
, “
Proper Orthogonal Decomposition of Turbine Rotor-Stator Interaction
,”
J. Propul. Power
,
19
(
2
), pp.
268
281
.
18.
Schmid
,
P. J.
,
2010
, “
Dynamic Mode Decomposition of Numerical and Experimental Data
,”
J. Fluid Mech.
,
656
, pp.
5
28
.
19.
Xue
,
X.
,
Wang
,
T.
,
Zhang
,
T.
, and
Yang
,
B.
,
2018
, “
Mechanism of Stall and Surge in a Centrifugal Compressor With a Variable Vaned Diffuser
,”
Chin. J. Aeronautics
,
31
(
6
), pp.
1222
1231
.
20.
Galindo
,
J.
,
Serrano
,
J. R.
,
Climent
,
H.
, and
Tiseira
,
A.
,
2008
, “
Experiments and Modelling of Surge in Small Centrifugal Compressor for Automotive Engines
,”
Exp. Therm. Fluid Sci.
,
32
(
3
), pp.
818
826
.
21.
Greitzer
,
E. M.
,
1976
, “
Surge and Rotating Stall in Axial Flow Compressors—Part I: Theoretical Compression System Model
,”
ASME J. Eng. Gas Turbines Power
,
98
(
2
), pp.
190
198
.
22.
Crevel
,
F.
,
Gourdain
,
N.
, and
Moreau
,
S.
,
2014
, “
Numerical Simulation of Aerodynamic Instabilities in a Multistage High-Speed High-Pressure Compressor on Its Test-Rig—Part I: Rotating Stall
,”
ASME J. Turbomach.
,
136
(
10
), p.
101003
.
23.
Houde
,
S.
,
Dumas
,
G.
, and
Deschênes
,
C.
,
2018
, “
Experimental and Numerical Investigations on the Origins of Rotating Stall in a Propeller Turbine Runner Operating in No-Load Conditions
,”
ASME J. Fluids Eng.
,
140
(
11
), p.
111104
.
24.
Rowley
,
C. W.
,
Mezić
,
I.
,
Bagheri
,
S.
,
Schlatter
,
P.
, and
Henningson
,
D. S.
,
2009
, “
Spectral Analysis of Nonlinear Flows
,”
J. Fluid Mech.
,
641
, pp.
115
127
.
You do not currently have access to this content.