The development of the equation system is presented in essentially summary form resulting in a quasi three-dimensional approach to the aerodynamic design of turbomachinery. The solution of these equations is indicated by utilization of the digital computer, and a unique solution technique is employed for a particular solution of these general equations. 

The veriflcation of this overall design approach is demonstrated by the design, construction, and test of a research low pressure steam turbine consisting of three stages. The performance evaluation of this test vehicle was accomplished by means of overall thermodynamic instrumentation and by means of a radial traverse immediately down stream of the last rotor blade. Comparisons are made of these test data with the design flow conditions obtained from solutions of both the complete set of aero-thermodynamic equations and that corresponding to the particular solution referred to above.