Research Papers

An Improved Mixing-Plane Method for Analyzing Steady Flow Through Multiple-Blade-Row Turbomachines

[+] Author and Article Information
Ding Xi Wang

Siemens Industrial Turbomachinery Ltd.,
Waterside South,
Lincoln LN5 7FD, UK
e-mail: dingxi.wang@siemens.com

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received May 28, 2013; final manuscript received November 19, 2013; published online January 31, 2014. Assoc. Editor: John Clark.

J. Turbomach 136(8), 081003 (Jan 31, 2014) (9 pages) Paper No: TURBO-13-1085; doi: 10.1115/1.4026170 History: Received May 28, 2013; Revised November 19, 2013

Presented in this paper is an improved method for dealing with a mixing plane that exists between computational domains of two adjacent blade rows of a multiple-blade-row turbomachine. The method makes use of the semidiscrete flow equation updating scheme to convert flux differences across an interrow interface to conservative flow variable incrementals then to characteristic variable perturbations. Therefore, the proposed method bears more physics and is much more robust than any known method of its kind. As a result, reverse flow can be accommodated by this method naturally without any special treatment. Two existing methods are also included to provide a clear illustration of the differences and advantages of the new method. Two numerical test cases using a transonic compressor stage are presented to investigate the robustness of the new method and its influence on solution convergence, accuracy, and time cost in comparison with the two existing methods.

Copyright © 2014 by ASME
Your Session has timed out. Please sign back in to continue.


Denton, J. D., “The Calculation of Three-Dimensional Viscous Flow Through Multistage Turbomachines,” ASME J. Turbomach., 114, pp. 18–26. [CrossRef]
Giles, M., 1991, “UNSFLO: A Numerical Method for the Calculation of Unsteady Flow in Turbomachinery,” MIT Gas Turbine Laborotory, Cambridge, MA, GTL Report No. 205.
Chima, R. V., 1998, “Calculation of Multistage Turbomachinery Using Steady Characteristic Boundary Conditions,” AIAA Paper No. 98-0968. [CrossRef]
Holmes, D. G., 2008, “Mixing Planes Revisited: A Steady Mixing Plane Approach Designed to Combine High Levels of Conservation and Robustness,” ASME Paper No. GT2008-51296. [CrossRef]
Moraga, F. J., Vysohlid, M., Smelova, N., Mistry, H., Atheya, S., Kanakala, V., 2012, “A Flux-Conservation Mixing Plane Algorithm For Multiphase Non-Equilibrium Steam models,” ASME Paper No. GT2012-68660. [CrossRef]
Fritsch, G., and Giles, M. B., 1995, “An Asymptotic Analysis of Mixing Loss,” ASME J. Turbomach., 117, pp. 367–374. [CrossRef]
Pullan, G., 2006, “Secondary Flows and Loss Caused by Blade Row Interaction in a Turbine Stage,” ASME J. Turbomach., 128, pp. 484–491, July 2006. [CrossRef]
Giles, M., 1988, “Non-Reflecting Boundary Conditions for the Euler Equations,” CFDL-TR-88-1.
Spalart, P., and Allmaras, S., 1992, “A One-Equation Turbulence Model for Aerodynamic Flows,” AIAA Paper No. 92-0439. [CrossRef]
Jameson, A., Schmidt, W., and Turkel, E., 1981, “Numerical Solution of the Euler Equations by Finite Volume Methods Using Runge–Kutta Time-Stepping Schemes,” AIAA 14th Fluid and Plasma Dynamic Conference, Palo Alto, CA, June 23–25, AIAA Paper No. 81-1259. [CrossRef]
Reid, L., and Moore, R. D., 1978, “Performance of Single-Stage Axial-Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 1.82,” NASA Technical Paper 1338.


Grahic Jump Location
Fig. 1

Schematic of an artificial interface between a rotor and a stator (left) and the virtual control volume formed by displacing two adjacent domains (right)

Grahic Jump Location
Fig. 2

Blade to blade view of the computational domain at the midspan

Grahic Jump Location
Fig. 3

Meridional view of the computational domain

Grahic Jump Location
Fig. 4

Average residual history of the energy equation at a near peak efficiency

Grahic Jump Location
Fig. 5

Convergence history of inlet mass flow rate and the compressor adiabatic efficiency at a near peak efficiency point

Grahic Jump Location
Fig. 6

Streamwise distribution of mass averaged entropy at a near peak efficiency

Grahic Jump Location
Fig. 7

Mach number contours at the midspan of the compressor (solution from the new method, and the other two methods give identical results that are not provided to avoid redundancy)

Grahic Jump Location
Fig. 8

Pressure ratio variation against mass flow rate at the compressor design speed

Grahic Jump Location
Fig. 9

Adiabatic efficiency variation against pressure ratio at the compressor design speed

Grahic Jump Location
Fig. 10

Average residual history of the energy equation for the reverse flow case

Grahic Jump Location
Fig. 11

Convergence history of inlet/outlet mass flow rate and adiabatic efficiency for the reverse flow case

Grahic Jump Location
Fig. 12

Axial velocity contours and streamlines on a meridional plane for the reverse flow case

Grahic Jump Location
Fig. 13

Total temperature contours at the stator inlet plane for the reverse flow case

Grahic Jump Location
Fig. 14

Total temperature (in the stationary frame of reference) contours at 98% span for the reverse flow case

Grahic Jump Location
Fig. 15

Entropy contours at 98% span for the reverse flow case



Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In