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Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis
Ronald H. Aungier
Ronald H. Aungier
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ASME Press
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An effective preliminary aerodynamic design system provides substantial benefits in terms of quality and productivity for all types of turbomachinery stages. This was demonstrated in chapter 6 for axial-flow turbine stages. Similar benefits have been demonstrated for centrifugal compressors [1, 94] and axial-flow compressors [2]. The definition of a set of stage components that are well matched to each other for the stage design conditions is a very time-consuming process if done manually. Practical time constraints usually terminate such manual efforts with something acceptable rather than optimum. The computer can accomplish nearly all of the most of the time-consuming steps in this process once a logical preliminary design strategy is established. This permits the designer to explore a wide range of alternatives in a very brief period of time. When properly interfaced to an aerodynamic performance analysis, this also establishes well-qualified preliminary geometry to initiate the detailed aerodynamic design of the various components in the stage.

10.1 Preliminary Aerodynamic Design Strategy
10.2 Rotor Tip Sizing
10.3 Rotor Design Specifications
10.4 Rotor Sizing
10.5 Evaluating the Rotor Design
10.6 Rotor End-Wall Contours
10.7 Straight-Line Element Rotor Blade Camberlines
10.8 Radial Element Rotor Blade Camberlines
10.9 Nozzle Blade Geometry
10.10 Nozzle Row Sizing
10.11 Evaluating the Nozzle Design
10.12 Initial Estimates of the Nozzle Design Specifications
10.13 Volute Preliminary Design
10.14 Exhaust Diffuser Sizing
10.15 A Typical Preliminary Design Example
10.16 A Computerized Preliminary Design System
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