Integrated Environment for Gas Turbine Preliminary Design

This paper presents structure and capabilities of new integrated environment for axial and radial turbines and compressors preliminary design. The environment makes possible to find number of different designs with inverse task solver, basing on initially specified boundary conditions, closing conditions and design variables. Design space explorer provides easy and visual comparison for range of obtained design in customizable coordinate axes. Solution filtering on different parameters, such as number of stages, meridional and axial dimensions, maximal blades weight, saving the time to choose from thousands obtained solutions the only one right design. Flexibility of presented approach allows to built-up complete gas turbine flow path from consequence of individual elements: stationary and rotating elements, ducts, heat exchangers, and analyze it in common environment. Joint turbine and compressor performances calculation “on the fly” is the next essential step of gas turbine or aircraft engine design and performances analysis to evaluate their operating modes and working ranges lines. Complete control of all aspects of aerodynamic flow path quality, structural reliability, and integral performances on design and offdesign conditions is performing throughout all design process. This gives full interaction between user and system for immediate correction and enhancement of current design data using various optimization capabilities to feel the impact of changes on each design step. Proposed system significantly shortening the design cycle time from initial machine concept to finalized design with all offdesign performances details already calculated.