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Abstract

The distributed loss model has been included in a time-marching Euler solver. This predicts the axisymmetric flow field and hub-to-tip stream surface geometry once the loading distribution is prescribed in the blade regions. The loss model replaces shear stresses with a suitable viscous force distribution, which does not work on the relative flow motion, but is only meant to produce entropy along the meridional streamlines. As in a fully inverse computation the flow angles are unknown, empirical loss correlations for single cascades cannot be used. The overall loss level through each blade row will be provided by the one-dimensional stage of the design process, then simplifying assumptions or specific correlations are used to estimate its spanwise distribution. The loss model effects on the flow field and stream surface geometry predicted by the inverse solver have been assessed.

Keywords

axial turbomachinery axisymmetric design Euler inverse throughflow distributed loss model profile losses

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References

Bena

Larocca

Zannetti

Design of multi-stage axial flow turbines and compressors. In Proceedings of the IMechE 1999 3rd European Conference on Turbomachinery, London, UK, March 1999, pp. 635–644, paper C557/047/99.

Denton

J. D.

Dawes

W. N.

Computational fluid dynamics for turbomachinery design. Proc. Instn Mech. Engrs, Part C: J. Mechanical Engineering Science, 1999, 213(C2), 107–124.

Sturmayr

Hirsch

Ch.

Throughflow model for design and analysis integrated in a three-dimensional Navier–Stokes solver. Proc. Instn Mech. Engrs, Part A: J. Power and Energy, 1999, 213(A4), 263–273.

Rosa Taddei

Larocca

Bertini

Inverse design of high lift cascades by implicit upwind schemes. In the AIMETA XVIII Congresso Associazione Italiana di Meccanica Teorica e Applicata, Brescia, Italy, September 2007, paper FL06–1.

Horlock

J. H.

On entropy production in adiabatic flow in turbomachines. Trans. ASME J. Basic Eng., 1971, 93D, 587–593.

Jennions

I. K.

Stow

A quasi three-dimensional turbomachinery blade design system, part 1: Through-flow analysis. Trans. ASME J. Eng. Gas Turbines Power, 1985, 107, 301–307.

Yao

Hirsch

Ch.

Throughflow model using 3D Euler or Navier-Stokes solvers. In Turbomachinery-Fluid Dynamic and Thermodynamic Aspects, Düsseldorf, Germany, 1995, VDI Berichte 1185, Verein Deutscher Ingenieure.

Damle

S. V.

Dang

T. Q.

Reddy

D. R.

Through-flow method for turbomachines applicable for all flow regimes. Trans. ASME J. Turbomach., 1997, 119, 256–262.

Simon

Léonard

A throughflow analysis tool based on the Navier-Stokes equations. In the ETC 6th European Conference on Turbomachinery, Lille, France, 2005.

10.

Hirsch

Numerical computation of internal and external flows. In Fundamentals of numerical discretization, 1988, vol. 1, pp. 81–86 (Wiley, Chichester, UK).

11.

C. H.

A general through flow theory of fluid flow with subsonic or supersonic velocities in turbomachines of arbitrary hub and casing shapes. NACA technical report 2302, 1951.

12.

Zannetti

Pandolfi

Inverse design technique for cascades. NASA contractor report 3836, 1984.

13.

Ferlauto

Iollo

Zannetti

Set of boundary conditions for aerodynamic design. AIAA J., 2004, 42(8), 1582–1592.

14.

Rai

M. M.

Chackravarthy

S. R.

An implicit form for the Osher upwind scheme. AIAA J., 1986, 24(5), 735–743.

15.

Pandolfi

A contribution to the numerical prediction of unsteady flows. AIAA J., 1984, 22(5), 602–610.

16.

Rosa Taddei

Larocca

Bertini

Spano

Euler inverse throughflow model based on an implicit upwind time marching technique. To be presented at ICAS 26th International Council of Aeronautical Sciences, Anchorage, Alaska, USA, September 2008, paper 430.

17.

Horlock

J. H.

Axial flow turbines: fluid mechanics and thermodynamics, 1966 (Butterworths, London, UK).

18.

Horlock

J. H.

Axial flow compressors: fluid mechanics and thermodynamics, 1958 (Butterworths, London, UK).

Axisymmetric design of axial turbomachines: An inverse method introducing profile losses

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