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FULL NAVIER-STOKES EQUATIONS APPLIED TO TURBOMACHINERY PROBLEMS

Objective


2 solution methods for the quasi 3 dimensional Reynolds averaged Navier Stokes equations have been developed and validated against a range of experimental data. These validations were specifically chosen, with strong adverse pressure gradients and flow separations, to enable the implementation of the methods for general turbomachinery flows.

A computer tool has been designed which is capable of accurately analysing viscous effects of the flow analysis of components for turbomachinery design. This has been achieved by solving the Navier-Stokes equation. The 2 solvers developed are workable, have been validated and produce good results in turbomachine flow design.
MODERN TRENDS IN THE REQUIREMENTS OF TURBOMACHINERY PERFORMANCE HAVE RESULTED IN TURBINES AND COMPRESSORS OPERATING AT HIGHER PRESSURE RATIOS OVER FEWER STAGES. TO PREDICT A FLOW SOLUTION FOR ANY PARTICULAR TURBINE GEOMETRY, THE DESIGNER MUST SOLVE THE NAVIER-STOKES EQUATIONS IN SOME FORM. A FULL SOLUTION OF THE EQUATIONS IS NOT POSSIBLE SINCE THERE ARE NOT ENOUGH "KNOWNS" TO PRODUCE A UNIQUE SOLUTION. THEREFORE, SIMPLIFYING ASSUMPTIONS AND MODELLING TECHNIQUES NEED TO BE INTRODUCED WHICH IDEALLY INCORPORATE VISCOSITY EFFECTS.

THE SOLUTION METHODS USED TO SOLVE THE NAVIER-STOKES EQUATIONS IN THIS PROJECT ARE DIFFERENT, BUT COMPLEMENTARY. ONE IS A FINITE VOLUME SOLUTION METHOD, THE OTHER IS A FINITE DIFFERENCE METHOD. THE NUMERICS OF BOTH METHODS WILL BE IMPROVED TO CALCULATE THE FLOWS UNDER CONSIDERATION, IN PARALLEL WITH THE IMPLEMENTATION AND DEVELOPMENT OF SEVERAL DIFFERENT TURBULENT MODELS.

THE DATA OBTAINED FROM AERODYNAMIC EXPERIMENTS WILL BE COMPARED WITH THE PREDICTIONS FROM BOTH THE NUMERICAL CODES, WITH A RANGE OF TURBULENCE MODELS. LEADING FROM THESE DEVELOPMENTS, IT SHOULD BE POSSIBLE TO DETERMINE A "DOMAIN OF CORRECTNESS" FOR EACH TURBULENCE MODEL, IN THE CONTEXT OF THE TWO SEPARATE PREDICTION METHODS. THIS WILL HIGHLIGHT AREAS WHERE NO EXISTING TURBULENCE MODEL IS ADEQUATE, AND MAY SUGGEST THE REQUIRED STRUCTURE OF NEW MODELS INCORPORATING VISCOSITY. CENTRAL TO THE DEVELOPMENT OF THE CODES IS THE INDUSTRIAL REQUIREMENT FOR A PRACTICAL, RAPID, FULLY VISCOUS PREDICTION METHOD FOR BOTH COMPRESSOR AND TURBINE AERODYNAMIC DESIGN.

Funding Scheme

CSC - Cost-sharing contracts

Coordinator

Bertin et Cie S.A.
Address
59,Rue Pierre Curie 59
78373 Plaisir
France

Participants (2)

GEC Alsthom Ltd
United Kingdom
Address
Lichfield Road
ST17 4LN Stafford
NATIONAL TECHNICAL UNIVERSITY OF ATHENS
Greece
Address
Iroon Polytechnioy 5
15780 Athens