This paper describes the introduction of 3-D blade designs into the core compressors of the Rolls-Royce Trent engine series with particular emphasis on the use of sweep and dihedral in the rotor designs. It follows the development of the basic ideas in a university research project, through multistage low-speed model testing, to their application to the high pressure engine compressor. An essential element of the project was the use of multistage CFD and some of the development of the method to allow the designs to take place is also discussed. Part I of the paper concentrated on the fundamental university-based research and the methods development. Part II describes additional low-speed multistage design and testing and the high-speed engine compressor designs and tests.

Issue Section:
Technical Papers
Keywords:
gas turbines, compressors, rotors, testing, design engineering, rotational flow, Multistage, Compressor, Sweep, Dihedral, Design
Topics:
Compressors, Design, Rotors, Stators, Blades, Computational fluid dynamics
1.
Gallimore
,
S. J.
,
Bolger
,
J. J.
,
Cumpsty
,
N. A.
,
Taylor
,
M. J.
,
Wright
,
P. I.
, and
Place
,
J. M. M.
,
2002
, “
The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading Part I: University Research and Methods Development
,”
ASME J. Turbomach.
,
124
, pp.
521
–
532
.
2.
Howard
,
M. A.
,
Ivey
,
P. C.
,
Barton
,
J. P.
, and
Young
,
K. F.
,
1994
, “
Endwall Effects at Two Tip Clearances in a Multistage Axial Flow Compressor with Controlled Diffusion Blading
,”
ASME J. Turbomach.
,
116
, pp.
635
–
647
.
3.
Swoboda, M., Ivey, P. C., Wenger, U., Gu¨mmer, V., 1998, “An Experimental Examination of Cantilevered and Shrouded Stators in a Multistage Axial Compressor,” ASME Paper 98-GT-282.
Copyright © 2002
 by ASME
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