Nowadays, modern axial compressors have already reached a very high level of development. The current study is focused on the question, if the application of riblets on the surfaces of a highly efficient modern compressor blade can be a further step toward more efficient blade design. Therefore, a highly loaded compressor cascade has been designed and optimized specifically for low Reynolds number (LRN) conditions, as encountered at high altitudes and under consideration of the application of riblets. The optimization was performed at a Mach number of 0.6 and a Reynolds number of 1.5 × 105. Two objective functions were used. The aim of the first objective function was to minimize the cascade losses at the design point and at incidence angles of +5 and −5 deg. The intention of the second objective function was to achieve a smooth distribution of the skin friction coefficient on the suction side of the blade by influencing the blade curvature in order to apply riblets. The MISES flow solver as well as the DLR optimizer “AutoOpti” was used for the optimization process. The developed compressor cascade was investigated in the transonic cascade wind tunnel of DLR in Cologne, where the Reynolds number was varied in the range of 1.5 × 105–9.0 × 105. Furthermore, the measurements were carried out at a low turbulence level of 0.8% and at a high turbulence level of 4%, representative for high pressure compressor stages. The measurement program was divided into two parts. The first part consisted of the investigation of the reference cascade. In the second part of the study, riblets were applied on suction and pressure side of the cascade blades; two different manufacturing techniques, a rolling and a coating techniques, were applied. The rolling technique provides riblets with a width of 70 μm and the coated riblets (CRs) have a width of 50 μm. The wake measurements were performed using a three-hole probe at midspan of the cascade in order to determine the resulting losses of the reference blade and the blades with applied riblets. The detailed analysis of the measurements shows that the riblets have only a slight influence on the viscous losses in the case of the compressor application in this study. Finally, these results are discussed and assessed against the background of feasibility and effort of riblet applications within the industrial design and manufacturing process.

References

References
1.
Köller
,
U.
,
Mönig
,
R.
,
Küsters
,
B.
, and
Schreiber
,
H. A.
,
2000
, “
Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines—Part I: Design and Optimization
,”
ASME J. Turbomach.
,
122
(
3
), pp.
397
405
.
2.
Küsters
,
B.
,
Schreiber
,
H. A.
,
Köller
,
U.
, and
Mönig
,
R.
,
2000
, “
Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines—Part II: Experimental and Theoretical Analysis
,”
ASME J. Turbomach.
,
122
(
3
), pp.
406
415
.
3.
Siller
,
U.
,
Voß
,
C.
, and
Nicke
,
E.
,
2009
, “
Automated Multidisciplinary Optimization of a Transonic Axial Compressor
,”
AIAA
Paper No. AIAA-2009-863.
4.
Lengyel
,
T.
,
Schmidt
,
T.
,
Voß
,
C.
, and
Nicke
,
E.
,
2009
, “
Design of a Counter Rotating Fan—An Aircraft Engine Technology to Reduce Noise and CO2-Emissions
,”
19th ISABE Conference
,
Montreal, Canada
, Sept. 7–11, ISABE Paper No. 2009-1267.
5.
Lengyel
,
T.
,
Nicke
,
E.
,
Rüd
,
K.-P.
, and
Schaber
,
R.
,
2011
, “
Optimization and Examination of a Counter Rotating Fan Stage—The Possible Improvement of the Efficiency Compared With a Single Rotating Fan
,”
20th ISABE Conference
,
Gothenburg, Sweden
, Sept. 12–16, ISABE Paper No. 2011-1232.
6.
Lengyel-Kampmann
,
T.
,
Bischoff
,
A.
,
Meyer
,
R.
, and
Nicke
,
E.
,
2012
, “
Design of an Economical Counter Rotating Fan—Comparison of the Calculated and Measured Steady and Unsteady Results
,”
ASME
Paper No. GT2012-69587.
7.
Fang
,
C.
,
Yan-Ping
,
T.
, and
Mao-Zhang
,
C.
,
1990
, “
An Experimental Investigation of Loss Reduction With Riblets on Cascade Blade Surfaces and Isolated Airfoils
,”
ASME
Paper No. 90-GT-207.
8.
Boese
,
M.
, and
Fottner
,
L.
,
2002
, “
Effects of Riblets on the Loss Behavior of a Highly Loaded Compressor Cascade
,”
ASME
Paper No. GT2002-30438.
9.
Oehlert
,
K.
,
Seume
,
J. R.
,
Siegel
,
F.
,
Ostendorf
,
A.
,
Wang
,
B.
,
Denkena
,
B.
,
Vynnyk
,
T.
,
Reithmeier
,
E.
,
Hage
,
W.
,
Knobloch
,
K.
, and
Meyer
,
R.
,
2007
, “
Exploratory Experiments on Machined Riblets for 2-D Compressor Blades
,”
ASME
Paper No. IMECE2007-43457.
10.
Sonoda
,
T.
,
Yamaguchi
,
Y.
,
Arima
,
T.
,
Olhofer
,
M.
,
Sendhoff
,
B.
, and
Schreiber
,
H. A.
,
2004
, “
Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition—Part I: Design and Optimization
,”
ASME J. Turbomach.
,
126
(
3
), pp.
350
359
.
11.
Sonoda
,
T.
, and
Schreiber
,
H. A.
,
2007
, “
Aerodynamic Characteristics of Supercritical Outlet Guide Vanes at Low Reynolds Number Conditions
,”
ASME J. Turbomach.
,
129
(
4
), pp.
694
704
.
12.
Schreiber
,
H. A.
,
Steinert
,
W.
,
Sonoda
,
T.
, and
Arima
,
T.
,
2004
, “
Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition—Part II: Experimental and Numerical Analysis
,”
ASME J. Turbomach.
,
126
(
4
), pp.
482
492
.
13.
Klocke
,
F.
,
Feldhaus
,
B.
,
Hirt
,
G.
,
Thome
,
M.
,
Klumpp
,
S.
, and
Schröder
,
W.
,
2007
, “
Development of Two Innovative Rolling Processes for the Production of Defined Riblet Structures in Consideration of Common Fluid Dynamic Requirements
,”
2nd International Conference on New Forming Technology
(ICNFT),
Bremen, Germany
, Sept. 20-21, pp.
185
194
.
14.
Bechert
,
D. W.
,
Bruse
,
M.
,
Hage
,
W.
,
van der Hoeven
,
J. G. T.
, and
Hoppe
,
G.
,
1997
, “
Experiments on Drag Reducing Surfaces and Their Optimization With an Adjustable Geometry
,”
J. Fluid Mech.
,
338
, pp.
59
87
.
15.
Stenzel
,
V.
,
Wilke
,
Y.
, and
Hage
,
W.
,
2011
, “
Drag-Reducing Paints for the Reduction of Fuel Consumption in Aviation and Shipping
,”
Prog. Org. Coat.
,
70
(
4
), pp.
224
229
.
16.
Bechert
,
D. W.
,
Bruse
,
M.
, and
Hage
,
W.
,
2000
, “
Experiments With Three-Dimensional Riblets as an Idealized Model of Shark Skin
,”
Exp. Fluids
,
28
(
5
), pp.
403
412
.
17.
Ninnemann
,
T.
, and
Ng
,
W. F.
,
2004
, “
Loss Reduction Using Riblets on a Supersonic Through-Flow Fan Blade Cascade
,”
ASME J. Fluids Eng.
,
126
(
4
), pp.
642
649
.
18.
Voss
,
C.
,
Aulich
,
M.
,
Kaplan
,
B.
, and
Nicke
,
E.
,
2006
, “
Automated Multiobjective Optimisation in Axial Compressor Blade Design
,”
ASME
Paper No. GT2006-90420.
19.
Aulich
,
M.
, and
Siller
,
U.
,
2011
, “
High-Dimensional Constrained Multiobjective Optimization of a Fan Stage
,”
ASME
Paper No. GT2011-45618.
20.
Drela
,
M.
, and
Youngren
,
H.
,
1991
, “
Viscous/Inviscid Method for Preliminary Design of Transonic Cascades
,”
AIAA
Paper No. 91-2364.
21.
Klumpp
,
S.
,
Meinke
,
M.
,
Schröder
,
W.
,
Feldhaus
,
B.
, and
Klocke
,
F.
,
2009
, “
Riblets in Turbulent Flow Regimes of 2-D Compressor Blades
,”
ASME
Paper No. GT2009-59352.
22.
Hergt
,
A.
,
Steinert
,
W.
, and
Grund
,
S.
,
2013
, “
Design and Experimental Investigation of a Compressor Cascade for Low Reynolds Number Conditions
,”
21st International Symposium on Applications of Laser Techniques to Fluid Mechanics
(
ISABE
),
Busan, Korea
, Sept. 9–13, ISABE Paper No. 2013-1104.
23.
Feldhaus
,
B.
,
2011
, “
Walzen definierter Ribletstrukturen auf Verdichterschaufeln
,” Ph.D. thesis,
RWTH Aachen, Aachen
,
Germany
.
24.
Schongen
,
F.
,
Klocke
,
F.
,
Feldhaus
,
B.
,
Timmer
,
A.
,
Terhorst
,
M.
, and
Rohr
,
O.
,
2011
, “
Incremental Rolling of Defined Riblet Structures on Ti6Al4V Compressor Blades
,”
10th International Conference on Technology of Plasticity
(
ICTP 2011
), Aachen, Germany, Sept. 25–30, pp.
25
30
.
25.
Schreiber
,
H. A.
,
Starken
,
H.
, and
Steinert
,
W.
,
1993
, “
Transonic and Supersonic Cascades
,” Advanced Methods for Cascade Testing (AGARD AG), Vol.
328
, C. Hirsch, ed.,
AGARD, Neuilly sur Seine
,
France
, pp.
35
59
.
26.
Steinert
,
W.
,
Fuchs
,
R.
, and
Starken
,
H.
,
1992
, “
Inlet Flow Angle Determination of Transonic Compressor Cascade
,”
ASME J. Turbomach.
,
114
(
3
), pp.
487
493
.
27.
Schreiber
,
H. A.
,
Steinert
,
W.
, and
Kuesters
,
B.
,
2002
, “
Effects of Reynolds Numbers and Free-Stream Turbulence on Boundary Layer Transition in a Compressor Cascade
,”
ASME J. Turbomach.
,
124
(
1
), pp.
1
9
.
28.
Kiock
,
R.
,
Laskowski
,
G.
, and
Hoheisel
,
H.
,
1982
, “
Die Erzeugung höherer Turbulenzgrade in der Messstrecke des Hochgeschwindigkeits-Gitterwindkanals Braunschweig zur Simulation turbomaschinen-ähnlicher Bedingungen
” (DFVLR-FB-82-25), DFVLR,
Braunschweig
,
Germany
.
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