Investigation of Throughflow Hypothesis in a Turbine Cascade Using a Three-Dimensional Navier–Stokes Computation

Author:

Perrin G.1,Leboeuf F.1

Affiliation:

1. Laboratoire de Me´canique des Fluides et d’acoustique, Ecole Centrale de Lyon, Ecully, France

Abstract

The results of a computation, performed with a three-dimensional Navier–Stokes computation at ONERA, have been averaged in the blade-to-blade direction; the spatial fluctuations around the averaged flow variables have also been determined. It has then been possible to estimate all terms in the average components of the momentum equations. The comparison of the two-dimensional balances of these three equations shows that the shear stress plays a minor role in the momentum balance, except on the dissipation of the passage vortex kinetic energy downstream of the blade trailing edges. The kinetic energy of the spanwise component of the velocity spatial fluctuations has a very strong influence on the radial pressure gradient; it introduces a convection effect. This is a key effect for all these balances.

Publisher

ASME International

Subject

Mechanical Engineering

Reference14 articles.

1. Adkins G. G. , and SmithL. H., 1982, “Spanwise Mixing in Axial-Flow Turbomachines,” ASME Journal of Engineering for Power, Vol. 104, pp. 97–110.

2. Buleev, N. I., 1962, “Theoretical Model of the Mechanism of Turbulent Exchange in Fluid Flows,” Teploperedacha, Moscow, USSR, pp. 64–98; AERE translation 957, Atomic Energy Research Establishment, Harwell, United Kingdom, 1963.

3. Cambier, L., Couaillier, V., and Veuillot, J. P., 1988, “Re´solution nume´rique des e´quations de Navier–Stokes a` l’aide d’une me´thode multigrille,” La Recherche Ae´rospatiale, No. 1988-2, pp. 23–42.

4. Dawes W. N. , 1987, “A Numerical Analysis of the Three-Dimensional Viscous Flow in a Transonic Compressor Rotor and Comparison With Experiment,” ASME JOURNAL OF TURBOMACHINERY, Vol. 109, pp. 83–90.

5. Denton, J. D., Hodson, H. P., and Dominy, R. G., 1990, “Test Case E/CA-7: Subsonic Turbine Cascade LA,” in: “Test Cases for Computation of Internal Flows in Aero-engine Components,” AGARD-AR-275, Fottner, ed., pp. 124–138.

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