This paper describes a new universal algebraic model for the estimation of flow deflection and losses in axial compressor inlet guide vane devices. The model deals with nominal flow and far-off-design operating conditions in connection with large stagger angle adjustments. The first part of the model considers deflection and losses in 2D cascades, taking into account the main cascade geometry parameters and operating conditions, such as Mach number and stagger adjustment. The second part of the model deals with additional deviation and losses due to secondary flow caused by the end wall viscous effects and by the trailing vortices. The model is developed for NACA65 airfoils, NACA63-A4K6 airfoils, and airfoils having an NACA65 thickness distribution on a circular-arc camber line. It is suitable for application in 1D or 2D through-flow calculations for design and analysis cases. The development of the method is based on systematic computational fluid dynamics (CFD) flow calculations for various cascade geometries and operating parameters. The comparison of correlation results with experimental data for several test cases shows good agreement.

References

References
1.
Lieblein
,
S.
,
1950
, “
Turning Angle Design Rules for Constant-Thickness Circular-Arc Guide Vanes in Axial Annular Flow
,” Lewis Flight Propulsion Laboratory, Cleveland, OH, Paper No. NACA TN 2179.
2.
Zimmey
,
C. M.
, and
Lappi
,
V. M.
,
1945
, “
Data for Design of Entrance Vanes From Two Dimensional Tests of Airfoils in Cascade
,” NACA Advance Confidential Report L5G18.
3.
Waltke
,
U.
,
1995
, “
Berechnung des Meridianströmungsfeldes in Axialverdichtern mit der Methode der Finiten Elemente
,” Fortschritt-Berichte VDI Reihe 7 Nr. 261, VDI-Verlag, Düsseldorf, Germany.
4.
Petrovic
,
M. V.
,
Wiedermann
,
A.
, and
Banjac
,
M.
,
2009
, “
Development and Validation of a New Universal Throughflow Method for Axial Compressors
,”
ASME
Paper No. GT2009-59938. 10.1115/GT2009-59938
5.
Lieblein
,
S.
,
1965
, “
Experimental Flow in Two-Dimensional Cascades
,”
Aerodynamic Design of Axial-Flow Compressors
,
I. A.
Johnsen
and
R. O.
Bullock
, eds., NASA Lewis Research Center, Cleveland, OH, NASA SP-36, pp.
183
225
.
6.
Drela
,
M.
, and
Youngren
,
H.
,
1998
,
A User's Guide to MISES
,
MIT Computational Aerospace Sciences Laboratory, Cambridge, MA
.
7.
Bruna
,
D.
,
Turner
,
M. G.
, and
Cravero
,
C.
,
2006
, “
The Development of an Aerodynamic Performance Prediction Tool for Modern Axial Flow Compressor Profiles
,”
ASME
Paper No. GT2006-90187. 10.1115/GT2006-90187
8.
Pfitzinger
,
W. E.
,
1998
, “
Kennfeldberechnung für Axialverdichter mit systematischer Untersuchung der Verlust und Umlenkeigenschaften von Schaufelgittern
,” Fortschritt-Berichte VDI Reihe 7 Nr. 337, VDI-Verlag, Düsseldorf, Germany.
9.
Camp
,
T. R.
, and
Shin
,
H.-W.
,
1995
, “
Turbulence Intensity and Length Scale Measurements in Multistage Compressors
,”
ASME J. Turbomach.
,
117
, pp.
38
46
.10.1115/1.2835642
10.
Aungier
,
H. R.
,
2003
,
Axial-Flow Compressors, ASME Press
,
New York
.
11.
Dunavant
,
C. J.
,
1957
, “
Cascade Investigation of a Related Series of 6-Percent-Thick Guide-Vane Profiles
,”
Langley Aeronautical Laboratory
,
Langley Field
, VA, NACA TN 3959.
12.
Mattiske
,
B.
,
1994
, “
Experimentelle Untersuchung einer mehrstufigen Axialverdichterbeschufelung mit Randzonen-Korrektur
,” Fortschritt-Berichte, VDI Reihe 7, Nr. 252, VDI-Verlag, Düsseldorf, Germany.
13.
Lieblein
,
S.
, and
Ackley
,
R. H.
,
1951
, “
Secondary Flows in Annular Cascades and Effects on Flow in Inlet Guide Vanes
,”
Lewis Flight Laboratory
,
Cleveland
, OH, NACA RM E51G27.
14.
Hirsch
,
C.
, and
Denton
,
J. D.
,
1981
, “
Through Flow Calculations in Axial Turbomachines
,”
AGARD-AR-175
, pp.
229
255
.
15.
D'Ippolito
,
G.
,
Dossena
,
V.
,
Mora
,
A.
,
2011
, “
The Influence of Blade Lean on Straight and Annular Turbine Cascade Flow Field
,”
ASME J. Turbomach.
,
133
(
1
), p. 011013.
16.
Mahoney
,
J. J.
,
Dugan
,
P. D.
,
Budinger
,
R. E.
, and
Goelzer
,
F. H.
,
1950
, “
Investigation of Blade-Row Flow Distributions in Axial-Flow-Compressor Stage Consisting of Guide Vanes and Rotor-Blade Row
,”
Lewis Flight Propulsion Laboratory
,
Cleveland
, OH, NACA RM E50G12.
17.
Graham
,
R. C.
, and
Tysl
,
E. R.
,
1949
, “
Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine II—Performance of Inlet Guide Vanes as Separate Component
,” NACA, Washington, DC, NACA RM SE9E03.
18.
Lawrence
,
J. J.
, and
Theodore
,
E. F.
,
1957
, “
Experimental Investigation of Performance of Single-Stage Transonic Compressor With Guide Vanes Turning Counter to Direction of Rotor Whirl
,”
Lewis Flight Propulsion Laboratory
,
Cleveland
, OH, NACA RM E57B04.
You do not currently have access to this content.