Affiliation:
1. Whittle Laboratory, University of Cambridge, Cambridge, United Kingdom
Abstract
This paper describes the development of actuator disk models to simulate the asymmetric flow through high-speed low hub-to-tip ratio blade rows. The actuator disks represent boundaries between regions of the flow in which the flow field is solved by numerical computation. The appropriate boundary conditions and their numerical implementation are described, and particular attention is paid to the problem of simulating the effect of blade row blockage near choking conditions. Guidelines on choice of axial position of the disk are reported. In addition, semi-actuator disk models are briefly described and the limitations in the application of the model to supersonic flow are discussed.
Reference19 articles.
1. Billet
G.
, HuardJ., ChevalierP., and LavalP., 1988, “Experimental and Numerical Study of the Response of an Axial Compressor to Distorted Inlet Flow,” ASME Journal of Fluids Engineering, Vol. 110, pp. 355–360.
2. Dawes, W. N., 1986, “Numerical Techniques for Viscous Flow Calculations in Turbomachinery Blading,” Application of Full Navier–Stokes Solvers to Turbomachinery Flow Problems, Von Karman Institute Lecture Series 1986-02.
3. Dawes, W. N., 1988, “Development of a 3D Navier–Stokes Solver for Application to All Types of Turbomachinery,” ASME Paper No. 88-GT-70.
4. Dawes
W. N.
, 1990, “Towards Improved Throughflow Capability: The Use of 3D Viscous Flow Solvers in a Multistage Environment,” ASME JOURNAL OF TURBOMACHINERY, Vol. 109, pp. 83–90.
5. Dunham, J., 1965, “Non-axisymmetric Flows in Axial Flow Compressors,” Mech. Eng. Sci. Monograph No. 3, pp. 1–32.
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