ADVANCED TURBOMACHINERY CFD DESIGN AND ANALYSIS PROGRAM

COMPUTATIONAL FLUID DYNAMICS (CFD) TOOLS HAVE NOW DEVELOPED TO THE POINT WHERE THEY CAN BE RELIABLY USED FOR THE DESIGN,EVALUATION, AND ANALYSIS OF SUCH HIGH-PERFORMANCE GAS TURBINES AS THOSE USED IN MODERN AERONAUTICAL PROPULSION SYSTEMS. FOR THESE APPLICATIONS, IT IS NECESSARY TO USE A THREE-DIMENSIONAL VISCOUS CFD CODE THAT COMBINES EFFICIENCY,ACCURACY, AND USER-FRIENDLINESS. FOR AXIAL TURBOMACHINERY, THE PREDICTION AND ANALYSIS OF SECONDARY FLOWS, BLADE HEAT TRANSFER, TRANSITION, AND UNSTEADINESS AT ON- AND OFF-DESIGNCONDITIONS REQUIRE THE USE OF NEW, ADVANCED MODELS LIKE THATPROVIDED BY THE RENORMALIZATION GROUP (RNG) METHODS DEVELOPED BY THE COMPANY. THIS PROJECT WILL DEVELOP ENHANCED SUPERCOMPUTER AND MASSIVELY PARALLEL PROCESSOR VERSIONS OF THE NEKTON CFD CODE WITH RNG MODELS FOR TRANSITION AND TURBULENCE TO ADDRESS TURBOMACHINERY APPLICATIONS. THIS INVOLVES INTEGRATING VARIABLE GEOMETRY, COMPLEX BLADE ROWS, TRANSITION AND TURBULENCE MODELLING, AND SHOCK-BOUNDARY LAYER INTERACTIONS WHILE ADDRESSING CENTRAL COMPRESSOR, DIFFUSER, AND TURBINE DESIGN ISSUES. COMPUTATIONAL FLUID DYNAMICS (CFD) TOOLS HAVE NOW DEVELOPED TO THE POINT WHERE THEY CAN BE RELIABLY USED FOR THE DESIGN,EVALUATION, AND ANALYSIS OF SUCH HIGH-PERFORMANCE GAS TURBINES AS THOSE USED IN MODERN AERONAUTICAL PROPULSION SYSTEMS. FOR THESE APPLICATIONS, IT IS NECESSARY TO USE A THREE-DIMENSIONAL VISCOUS CFD CODE THAT COMBINES EFFICIENCY,ACCURACY, AND USER-FRIENDLINESS. FOR AXIAL TURBOMACHINERY, THE PREDICTION AND ANALYSIS OF SECONDARY FLOWS, BLADE HEAT TRANSFER, TRANSITION, AND UNSTEADINESS AT ON- AND OFF-DESIGNCONDITIONS REQUIRE THE USE OF NEW, ADVANCED MODELS LIKE THATPROVIDED BY THE RENORMALIZATION GROUP (RNG) METHODS DEVELOPED BY THE COMPANY. THIS PROJECT WILL DEVELOP ENHANCED SUPERCOMPUTER AND MASSIVELY PARALLEL PROCESSOR VERSIONS OF THE NEKTON CFD CODE WITH RNG MODELS FOR TRANSITION AND TURBULENCE TO ADDRESS TURBOMACHINERY APPLICATIONS. THIS INVOLVES INTEGRATING VARIABLE GEOMETRY, COMPLEX BLADE ROWS, TRANSITION AND TURBULENCE MODELLING, AND SHOCK-BOUNDARY LAYER INTERACTIONS WHILE ADDRESSING CENTRAL COMPRESSOR, DIFFUSER, AND TURBINE DESIGN ISSUES.