The paper describes an advanced three-dimensional blading concept for highly loaded transonic compressor stators. The concept takes advantage of the aerodynamic effects of sweep and dihedral. To the knowledge of the authors this is the first approach reported in the open literature that combines those two basic types of lean in an engine-worthy aerofoil design. The paper makes a contribution to the understanding of the endwall effect of both features with special emphasis put on sweep. The advanced three-dimensional blading concept was applied to an Engine Section Stator (ESS) of an aero-engine fan. In order to demonstrate how three-dimensional flow can be controlled, numerical analysis of the flow structure in a conventional and an advanced stator configuration was performed using a three-dimensional Navier–Stokes solver. The numerical analysis showed the advanced blade improving both radial loading distribution and the three-dimensional endwall boundary layer development. In particular, a strong hub corner stall could be largely alleviated. High-speed rig testing of the advanced ESS confirmed the concept and showed good qualitative agreement between measurement and prediction. The work presented was closely linked to the development of the BR710 engine on which the advanced ESS is in service today.

Issue Section:
Technical Papers
Keywords:
compressors, stators, transonic flow, aerodynamics, Navier-Stokes equations, load flow control
Topics:
Airfoils, Blades, Compressors, Design, Flow (Dynamics), Stators, Pressure, Boundary layers
1.
Hobbs
,
D. E.
, and
Weingold
,
H. D.
,
1984
, “
Development of Controlled Diffusion Airfoils for Multistage Compressor Application
,”
ASME J. Eng. Gas Turbines Power
,
106
, pp.
271
–
278
.
2.
Behlke
,
R. F.
,
1986
, “
The Development of a Second Generation of Controlled Diffusion Airfoils for Multistage Compressors
,”
ASME J. Turbomach.
108
, pp.
32
–
41
.
3.
Robinson, C. J., 1991, “End-Wall Flows and Blading Design of Axial Flow Compressors,” Ph.D. Thesis, Cranfield Institute of Technology, England.
4.
LeJambre
,
C. R.
,
Zacharias
,
R. M.
,
Biederman
,
A. J.
,
Gleixner
,
B. P.
, and
Yetka
,
C.
,
1995
, “
Development and Application of a Multistage Navier–Stokes Flow Solver: Part II—Application to a High-Pressure Compressor Design
,”
ASME J. Turbomach.
,
120
, pp.
215
–
223
.
5.
Smith
,
L. H.
, and
Yeh
,
H.
,
1963
, “
Sweep and Dihedral Effects in Axial-Flow Turbomachinery
,”
ASME J. Basic Eng.
,
85
, pp.
401
–
416
.
6.
Gu¨mmer, V., and Wenger, U., 2000, “The Impact of Sweep and Dihedral on Axial Compressor Endwall Aerodynamics,” Proc. 8th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery (ISROMAC-8), Mar. 26–30, Honolulu, HI.
7.
Stark, U., 1967, “Stro¨mungsuntersuchungen an gepfeilten Verdichtergittern bei kompressibler Unterschallstro¨mung,” DFL-Forschungsbericht 67–09.
8.
Stark, U., and Gotthardt, H., 1978, “Theoretische und experimentelle Untersuchungen an konischen Turbinengittern. Teil 1: Potentialtheoretische Untersuchungen an gepfeilten Verdichter-und konischen Turbinengittern,” Bericht 78/2, Institut fu¨r Stro¨mungsmechanik, Technische Universita¨t Braunschweig.
9.
Stark, U., and Barsun, K., 1969, “Untersuchungen u¨ber den Einfluß der Machzahl und der Pfeilung auf die Sekunda¨rverluste in Verdichtergittern bei hohen Unterschallgeschwindigkeiten,” DFL-Forschungsbericht 69-55.
10.
Peng, Z., Wu, G., Yan, M., and Ren, L., 1991, “An Experimental Investigation of Technologies of Endwall Flow Control in a Compressor Plane Cascade,” AIAA Paper No. 91–2005.
11.
Place, J. M. M., 1997, “Three-Dimensional Flow in Core Compressors,” Ph.D. Thesis, Department of Engineering, University of Cambridge.
12.
Sasaki
,
T.
, and
Breugelmans
,
F.
,
1998
, “
Comparison of Sweep and Dihedral Effects on Compressor Cascade Performance
,”
ASME J. Turbomach.
,
120
, pp.
454
–
464
.
13.
Baumgarten, S., 1998, “Untersuchungen zur Auslegung von unprofilierten Nachleitradbeschaufelungen bei hochbelasteten Axialventilatoren,” Dissertation, Technische Universita¨t Braunschweig.
14.
Weingold, H. D., Neubert, R. J., Behlke, R. F., and Potter, G. E., 1995, “Reduction of Compressor Stator Endwall Losses Through the Use of Bowed Stators,” ASME Paper No. 95-GT-380.
15.
Shang, E., Wang, Z. Q., and Su, J. X., 1993, “The Experimental Investigation on the Compressor Cascades With Leaned and Curved Blade,” ASME Paper No. 93-GT-50.
16.
Wadia, A. R., and Beacher, B. F., 1989, “Three-Dimensional Relief in Turbomachinery Blading,” ASME Paper No. 89-GT-151.
17.
Dawes, W. N., 1988, “Development of a Three-Dimensional Navier–Stokes Solver for Application to All Types of Turbomachinery,” ASME Paper No. 88-GT-70.
18.
Dawes
,
W. N.
,
1992
, “
Towards Improved Throughflow Capability: The Use of Three-Dimensional Viscous Flow Solvers in a Multistage Environment
,”
ASME J. Turbomach.
,
114
, pp.
8
–
17
.
19.
Dawes, W. N., 1991, “Multi-Blade Row Navier–Stokes Simulations of FanBypass Configurations,” ASME Paper No. 91-GT-148.
20.
Tobak
,
M.
, and
Peake
,
D. J.
,
1982
, “
Topology of Three-Dimensional Separated Flow
,”
Annu. Rev. Fluid Mech.
,
14
, pp.
61
–
85
.
21.
Perry
,
A. E.
, and
Chong
,
M. S
,
1987
, “
A Description of Eddying Motions and Flow Patterns Using Critical-Point Concepts
,”
Annu. Rev. Fluid Mech.
,
19
, pp.
125
–
155
.
Copyright © 2001
 by ASME
You do not currently have access to this content.