Three-dimensional Navier-Stokes heat transfer predictions for turbine blade rows

Abstract

Results are shown for a three-dimensional Navier-Stokes analysis of both the flow and the surface heat transfer for turbine applications. Heat transfer comparisons are made with the experimental shocktunnel data of Dunn and Kirn, and with the data of Blair for the rotor of the large scale rotating turbine. The analysis was done using the steady-state, three-dimensional, thin-layer Navier-Stokes code developed by Chlrna, which uses a multistage Runge-Kutta scheme with implicit residual smoothing. An algebraic mixing length turbulence model is used to calculate turbulent eddy viscosity. The variation in heat transfer due to variations in grid parameters is examined. The effects of rotation, tip clearance, and inlet boundary layer thickness variation on the predicted blade and endwall heat transfer are examined. Nomenclature Cp-Pressure coei_cient (P-P{N)/(PI_N-PSXIT) P-Pressure Re-Unit Reynolds number C-Chord s Fractionalsurfacedistance St-Stanton number based on inletconditions z Fractionalchordwise distance y Distance normal to surface _+-Normalized distancefrom surface 6 Full boundary layer thickness u Kinematic viscosity p Density fMember AIAA This paper isdeclared a work of the U.S. Government and isnot subjectto copyrightprotectionin the United States. Subscripts ¢-Gas total IN-Blade row inlet EXIT " Blade row hub exit w Wall 1-First gridlinefrom surface Superscript ' Total Form Approved REPORT DOCUMENTATION PAGE I OMB No. 0704-0188 i Public reporting burden "for this collection of information is estimated to average i hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this bu_en est_ate or any other aspect o! this collection of information, including suggestions for reducing this burden, to Washington Headquatlers Services, Directorate for information Operations and Reports,

Grid Orthogonality Effects on Predicted Turbine Midspan Heat Transfer and Performance

“…Yeuan, Harried, and Tabakoff(1993) The issue of grid size is especially important when one considers that the goal of code development work is to achieve accurate three-dimensional Navier-Stokes solutions while utilizing a reasonable amount of computer resources. It has been shown b y Boyle and Giel(1992) that over 50 spanwise grid planes are necessary to achieve grid independent heat transfer results for a typical turbine blade. If one wishes to limit the size of routine three dimensional Navier-Stokes calculations to around a half million grid points, then blade-to-blade grids would have a maximum of 10,000 points.…”

Calculation of multistage turbomachinery using steady characteristic boundary conditions

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Low-Pressure Turbine Separation Control: Comparison With Experimental Data

“…The viscous grid is obtained from an inviscid grid by clustering the grid near all the solid walls (blade here). The clustering is done in such a way as to ensure that in the viscous grid, the distance of any cell center adjacent to a solid wall, measured in wall units (y + ), is less than half for the cases studied here, following Boyle and Giel [22]. The inviscid grid was generated using the commercial code GridPro/az3000 [23].…”