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2 TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk
1 Zeszyty Naukowe. Cieplne Maszyny Przepływowe - Turbomachinery / Politechnika Łódzka

3 1999

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Deviation and profile losses in a turbine cascade at off-design incidences

Willinger R., Haselbacher H.

Zeszyty Naukowe. Cieplne Maszyny Przepływowe - Turbomachinery / Politechnika Łódzka

1999

nr 115

431--443

This paper presents details of an investigation of the two-dimensional flow field in a linear turbine cascade at off-design incidences. The cascade geometry corresponds to the tip section of a moving blade row of a gas turbine of recent design. Six different inlet flow angles, ranging from high positive incidence to high negative incidence, have been investigated experimentally. A three hole pressure probe was traversed immediately downstream of the trailing edge plane. Further work concerned the computation of the cascade flow field with a finite-element based Navier-Stokes solver. The k/ɛ-model was used to account for the turbulent behavior of the flow. The measurement and computational results are compared with an established profile incidence loss correlation.

Multiblock parallel computation of an incompressible 3-D flow in turbomachines

Papierski A., Rabiega M.

TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk

1999

Vol. 3, No 1

39-52

A finite volume numerical method for the prediction of a fluid flow in complex geometries such as turbomachinery channels has been parallelized using a domain decomposition approach. A mathematical formulation of a 3-D incompressible steady flow has been presented on the basis of the N-S equations in a grid-oriented co-ordinate system with contravariant velocity components. A parallelized pressure-based implicit algorithm with discretization on a staggered grid has been developed. A message exchange system with a boundary exchange, developed by the authors, has been described. Exemplary calculations have been carried out for a laminar flow through a curved duct and for an inviscid flow through a stage of the centrifugal pump. A good agreement has been obtained in both the cases. Despite considerable simplification that has been introduced in the flow through the pump stage, the computations have shown nearly the same pressure rise in the stage as the measurements. Further directions of numerical investigations of a flow through turbomachines, including in particular those devoted to pressure losses related to the rotor-stator interaction, have been mentioned.

A Parallel adaptive code for compressible Navier-Stokes simulations

Banaś K.

TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk

1999

Vol. 3, No 1

17-37

The paper presents a finite element code for compressible flow simulations. The code has two important features: adaptivity to increase accuracy of computations by selectively refining a finite element mesh and efficient parallel performance due to a special implementation based on concept of patches of elements. The algorithm for approximating the compressible Navier-Stokes equations is a version of the stabilized finite element method. Three time integration strategies are implemented, explicit, linear implicit and nonlinear implicit, and the GMRES method is used to solve systems of linear equations. For parallel simulations the code uses a special algorithm for mesh partition. The performance of the code is tested for two examples of supersonic flows: one inviscid and one viscous.