An axial compressor loss and deviation model that was developed and presented during previous research has now been used to develop a computer program for multistage compressor design. A set of input data including overall parameters such as pressure ratio and mass flow rate and the first-stage parameters such as inlet flow coefficient and rotor tip Mach number are used to determine a number of stages and their geometry, speed and relevant flow properties. Then a subsequent redistribution of parameters for separate stages can be carried out in order to increase the stability indicators and efficiency over a desired operating range. A selected stage vortex law determines velocity triangles and blading geometry for hub and tip sections, which allows the generation of a realistic flow path shape. The developed program is considered to be a flexible and stable tool useful for tasks of manual or automated optimization when combined with an external optimization algorithm. This paper presents a basic mathematical model and the level of accuracy achieved. This is demonstrated through examples of manual design and redesign cases, while automated optimization will be included in future research.

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