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Chapter 10
Preliminary Aerodynamic Design of Radial-Inflow Turbine Stages

Excerpt

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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