An implicit Navier-Stokes analysis of turbine rotor-stator interaction

Gibeling, H. J.; Buggeln, R. C.; Chen, Shyi-Yaung; Mcconnaughey, H. V.

doi:10.2514/6.1988-3090

Cited by 2 publications

(1 citation statement)

References 5 publications

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“…In the last seven years there have been several research groups working on the development of methods for the calculation of unsteady flows in turbomachinery (Hodson, 1984;Koya and Kotake, 1985;Rai, 1987aRai, , 1987bFourmaux, 1986;Lewis et al, 1987;Gibeling et al, 1988). At MIT we have also been working on unsteady flow calculation methods for the last five years, starting initially with an inviscid wake/rotor interaction program (Giles, 1988a).…”

Section: Introductionmentioning

confidence: 99%

Validation of a Numerical Method for Unsteady Flow Calculations

Giles

Haimes

1991

Volume 1: Turbomachinery

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This paper describes and validates a numerical method for the calculation of unsteady inviscid and viscous flows. A companion paper compares experimental measurements of unsteady heat transfer on a transonic rotor with the corresponding computational results. The mathematical model is the Reynolds-averaged unsteady Navier-Stokes equations for a compressible ideal gas. Quasi-three-dimensionality is included through the use of a variable streamtube thickness. The numerical algorithm is unusual in two respects: a) for reasons of efficiency and flexibility it uses a hybrid Navier-Stokes/Euler method, and b) to allow for the computation of stator/rotor combinations with arbitrary pitch ratio a novel space-time coordinate transformation is used.Several test cases are presented to validate the performance of the computer program, UNSFLO. These include: a) unsteady, inviscid flat plate cascade flows, b) steady and unsteady, viscous flat plate cascade flows, c) steady turbine heat transfer and loss prediction. In the first two sets of cases comparisons are made with theory, and in the third the comparison is with experimental data.

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Section: Introductionmentioning

confidence: 99%

Validation of a Numerical Method for Unsteady Flow Calculations

Giles

Haimes

1991

Volume 1: Turbomachinery

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Airfoil cascade in unsteady eddy flow

Yudin¹

1994

J Appl Mech Tech Phys

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1. Introduction. In passing through a row of blades in a turbomachine, a nonuniform fluid stream undergoes a change. To date, the question of how drastic the change is and how it affects the hydrodynamic characteristics of the row has not been adequately studied. Theoretical analyses have been performed mainly with the use of a two-dimensional model of flow under the assumption that the flow is nonuniform and the loading on the airfoils is small. In this statement of the problem, known as the problem of a cascade in an unsteady eddy flow, the disturbance of the flow induced by the airfoils is of purely potential character. Due to the exponential decrease of the disturbance, the flow nonuniformity upstream and downstream the cascade remains invariant. In recent years the availability of powerful computers made it possible to perform the calculations on the basis of the full Euler or Navier-Stokes equations to obtain the flow pattern behind the cascade [1, 2]. In view of the complexity of the model, only sporadic results have been obtained, which does not enable us to study the dependence of the flow structure on the basic parameters of the cascade.In the present paper, as in the problem of a cascade in unsteady eddy flow, the nonuniformity is assumed to be small, but the restriction on the loading on airfoils is removed. The airfoils may be of arbitrary shape. We consider the problem linearized on a steady stream, which corresponds to constant (at infinity) flow around the cascade.2. Statement of the Problem. Let us consider an airfoil cascade in the stream of an ideal incompressible liquid in the plane of the complex variable z = x + iy. We assume the arbitrary airfoils in the cascade to be smooth or with a sharp trailing edge. Let us suppose that the complex stream velocity at infmity ahead of the cascade can be presented as V = V 1 o, + d, where Vl~ = con~, and d = J(x, y + ut) = d(x, y + ut + h I) is the small nonuniformity. In the general case this is eddy nonuniformity (rot J ;~ 0) propagating in the y direction as a periodic traveling wave with velocity u (Fig. 1). We suggest an arbitrary period of nonuniformity h I and a cascade pitch h 2 that satisfy the condition H = Nlh 1 = N2h 2 (H is the full period, N 1 and N 2 are integers). Let us neglect the transient vortex wakes which trail down the airfoils due to the change in circulation (quasisteady-state statement of the problem). Moreover, we assume that there is no reverse stream near the cascade, while the eddying at infinity ahead of the cascade is equal to zero:

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An implicit Navier-Stokes analysis of turbine rotor-stator interaction

Cited by 2 publications

References 5 publications

Validation of a Numerical Method for Unsteady Flow Calculations

Validation of a Numerical Method for Unsteady Flow Calculations

Airfoil cascade in unsteady eddy flow

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