Development of a more satisfactory method of estimating deviation angles was attempted using analytical procedures. Solutions for inviscid, irrotational flow in the blade-to-blade plane were obtained with a finite-difference calculation method. Deviation angles for three cascades with rounded trailing edges were estimated using the inviscid flow solutions and four existing trailing edge hypotheses. The estimated deviation angles were compared with experimental values for a range of incidence angle and inlet flow angle. None of the hypotheses were satisfactory at all incidence angles for all the cascades considered. An alternative hypothesis is presented which is suitable for one of the cascade profiles over a range of incidence and blade setting angle.

In the early 1990s, a team of Honeywell fan, compressor, and turbine aerodynamic designers concluded that major savings in design time and cost could be achieved with a new aero design system. The range of turbomachinery in company engines, the manufacturing methods used for airfoils, and the different design activities set the scope of the new aerodynamic design system. Emphasis was placed on making the system general, flexible, and easy to use. The end result was a new aero design system with a lot of functionality packed into a single, easy to use program. The new system contains both geometry generators and a 2-D through-flow solver. The system has many special features that have provided savings from productivity improvements and reductions in design cycle time. Overall, use of the system has provided a net cumulative savings of over $6 million since 1992.

A new, comprehensive, flexible, integrated design system for the aerodynamic design of fans, compressors, and turbines was developed during the past decade. It operates in both batch and interactive modes. The system contains a flow path generator, a through-flow solver, a stacked airfoil geometry generator, and a flank-milled airfoil geometry generator. This paper describes the interactive interface in more detail. In particular, it describes the design considerations, appearance, and functionality of the interactive interface. Top level requirements were established before the interface was designed. These requirements are explained and some of the key reasoning that drove the high level design of the interface is discussed. The four principal windows in the interface are described in detail. The interactive interface that was developed has significantly increased the productivity of fan, compressor and turbine aero designers.

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A new aerodynamic design system has been developed that includes geometry generators for fans, axial compressors, and centrifugal compressors. This paper describes geometry generators for both arbitrary and flank-milled airfoils in axial, radial and mixed gas paths. Both geometry generators have the special feature that airfoil sections are constructed on construction curves, not on flow paths or streamlines. Construction curves are independent of flow path curves and streamlines, but can be defined to coincide with them. This makes high-flowing and low-flowing designs very easy. A special feature specific to the flank milled airfoil geometry generator is an undercutting analysis to reveal any unwanted contact with the conical cutter. This special feature and others have provided major savings from productivity improvements and reductions in design cycle time.