Abstract
This paper presents a satisfactory numerical strategy to reliably evaluate the three-dimensional large-scale flow feature of multistage axial compressors in response to complex swirl distortion with acceptable computational cost. Under the theoretical framework of the body force method, the guide vanes of a swirl distortion generator and the multiple blade rows of a two-stage low-speed axial compressor are described by distributed source terms instead of a complex body-fitted grid approach. The key flow structure of the paired swirl generated by the swirl generator and the main distributions of flow angle at the rotor outlet of the first stage captured by the model agree well with experimental results, demonstrating the effectiveness of the numerical strategy. Additionally, the interaction process between the steady-state paired swirl and the compressor is clearly revealed by the study. The intensity of the swirl distortion can be greatly reduced after passing through the axial compressor. However, the swirl has a significant impact on the local blade loading of the first stage, which induces the mass flux nonuniformity as well as total pressure and total temperature distortion. The combined total pressure and total temperature distortion is significantly attenuated near tip and slightly enhanced near hub as it moves through the second stage.
Article PDF
Similar content being viewed by others
Avoid common mistakes on your manuscript.
Abbreviations
- E, F, G :
-
inviscid fluxes
- E v, F v, G v :
-
viscid fluxes
- r, θ, z :
-
radial, circumferential and axial coordinate/m
- S :
-
Centrifugal and Coriolis source terms
- S b :
-
blockage source terms
- S F :
-
blade force source terms
- t :
-
time/s
- π :
-
circular constant
- r, θ, z :
-
radial, circumferential and axial direction
- T:
-
transposition
References
Society of Automotive Engineers, A methodology for assessing inlet swirl distortion. Aerospace Information Report No. AIR 5686, 2010.
Genssler H.P., Meyer W., Fottner L., Development of intake swirl generators for turbo jet engine testing. Technical report, DTIC Document, 1987.
Sheoran Y., Bouldin B., A versatile design of a controlled swirl distortion generator for testing gas turbine engines. ASME Turbo Expo, 2008, Paper No. GT2008-50657, pp. 81–92.
Sheoran Y., Bouldin B., Krishnan P.M., Advancements in the design of an adaptable swirl distortion generator for testing gas turbine engines. ASME Turbo Expo, 2009, Paper No. GT2009-59146, pp. 23–32.
Bouldin B., Sheoran Y., Inlet flow angularity descriptors proposed for use with gas turbine engines. World Aviation Congress and Exposition, 2002, SAE2002-01-2919.
Hoopes K.M., O’Brien W.F., The StreamVane method: a new way to generate swirl distortion for jet engine research. 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013, AIAA Paper No. 2013-3665.
Guimarães T., Lowe K.T., O’Brien W.F., StreamVane turbofan inlet swirl distortion generator: mean flow and turbulence structure. Journal of Propulsion and Power, 2018, 34(2): 340–353.
Frohnapfel D.J., Lowe K.T., O’Brien W.F., Experimental quantification of fan rotor effects on inlet swirl using swirl distortion descriptors. Journal of Engineering for Gas Turbines and Power, 2018, 140(8): 082603.
Dong X., Sun D., Li F., et al., Effects of stall precursor-suppressed casing treatment on a low-speed compressor with swirl distortion. Journal of Fluids Engineering, 2018, 140(9): 091101.
Pardo A.C., Mehdi A., Pachidis V., et al., Numerical study of the effect of multiple tightly-wound vortices on a transonic fan stage performance. ASME Turbo Expo, 2014, Paper No. GT2014-26481.
Yao J., Gorrell S.E., Wadia A.R., A time-accurate CFD analysis of inlet distortion induced swirl in multistage fans. 3rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2007, AIAA Paper No. 2007-5059.
Fidalgo V.J., Hall C.A., Colin Y., A study of fan-distortion interaction within the NASA rotor 67 transonic stage. Journal of Turbomachinery, 2012, 134(9): 051011.
Cousins W.T., Davis M.W., Evaluating complex inlet distortion with a parallel compressor model Part 1—Concepts, theory, extensions, and limitations. ASME Turbo Expo, 2011, Paper No. GT2011-45067, pp. 1–12.
Davis M.W., Cousins W.T., Evaluating complex inlet distortion with a parallel compressor model Part 2—Applications to complex patterns. ASME Turbo Expo, 2011, Paper No. GT2011-45068, pp. 13–23.
Hale A., O’Brien W., A three-dimensional turbine engine analysis compressor code (TEACC) for steady state inlet distortion. Journal of Turbomachinery, 1998, 120: 422–430.
Hale A., Davis M., Sirbaugh J., A numerical simulation capability for analysis of aircraft inlet-engine compatibility. ASME Turbo Expo, 2004, Paper No. GT2004-53473, pp. 127–137.
Gong Y., A computational model for rotating stall and inlet distortions in multistage compressors. Cambridge: Massachusetts Institute of Technology, 1998.
Chima R.V., A three-dimensional unsteady CFD model of compressor stability. ASME Turbo Expo, 2006, Paper No. GT2006-90040, pp. 1157–1168.
Sirovich L., Initial and boundary value problems in dissipative gas dynamics. Physics of Fluids, 1967, 10(1): 24–34.
Guo J., Hu J., A three-dimensional computational model for inlet distortion in fan and compressor. Proc IMechE, Part A: Journal of Power and Energy, 2018, 232: 144–156.
Marble F.E., Three-dimensional flow in turbomachines, aerodynamics of turbines and compressors. Princeton: Princeton University Press, 1964.
Carter A.D.S., Hughes H.P., A theoretical investigation of the effect of profile shape on the performance of aerofoils in cascade. Aeronautical Research Council Reports and Memoranda 1946, pp. No. 2384.
Lieblein S., Aerodynamic design of axial-flow compressors. VI-experimental flow in two-dimensional cascades. NACA Research Memorandums, Report No. NACA-RM-E55K01a, 1965.
Roberts W.B., Serovy G.K., Sandercock D.M., Design point variation of three-dimensional loss and deviation for axial compressor middle stages. Journal of Turbomachinery, 1988, 110(4): 426–433.
Lakshminarayana B., Methods of predicting the tip clearance effects in axial flow turbomachinery. Journal of Basic Engineering, 1970, 92(3): 467–482.
Howell A.R., Fluid dynamics of axial compressors. Proceedings of the Institution of Mechanical Engineers, 1945, 153(1): 441–452.
Banjac M., Petrovic M.V., Wiedermann A., Secondary flows, endwall effects, and stall detection in axial compressor design. Journal of Turbomachinery, 2015, 137(5): 051004.
Jameson A., Schimidt W., Turkel E., Numerical solutions of the Euler equations by finite volume methods with Runge-Kutta time stepping schemes. 14th Fluid and Plasma Dynamics Conference, 1981, AIAA Paper No. 81-1259.
Edwards J.R., A low-diffusion flux-splitting scheme for Navier-Stokes calculations. Computers & Fluids, 1997, 26(6): 635–659.
Van L.B., Upwind-difference methods for aerodynamics problems governed by the Euler equations of gas dynamics. Lectures in Applied Mathematics. 1985, 22: 327–336.
Gallimore S.J., Spanwise mixing in multistage axial flow compressors: Part II, Throughflow calculations including mixing. Journal of Turbomachinery, 1986, 108(1): 10–16.
Acknowledgements
The research was funded by National Science and Technology Major Project (Grant 2017-II-0004-0017).
Author information
Authors and Affiliations
Corresponding author
Rights and permissions
About this article
Cite this article
Guo, J., Hu, J., Wang, X. et al. Efficient Modeling of an Axial Compressor with Swirl Distortion. J. Therm. Sci. 30, 1421–1434 (2021). https://doi.org/10.1007/s11630-021-1483-7
Received:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s11630-021-1483-7