Skip to Main Content
Skip Nav Destination

Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis

Ronald H. Aungier
Ronald H. Aungier
Search for other works by this author on:
No. of Pages:
ASME Press
Publication date:

The nozzle-blade preliminary aerodynamic design procedure described in chapter 10 is easily modified to provide a sound basis for the detailed aerodynamic design also. That approach is almost always sufficient to achieve design objectives for both aerodynamic performance and mechanical integrity. Impeller detailed design is conveniently accomplished using procedures essentially identical to those commonly used for centrifugal compressors. Indeed, this writer uses the detailed design system described in Aungier [1] for both types of impellers. The only modification required to extend the centrifugal compressor impeller detailed design procedure to radial-inflow turbines was to include provision to reverse the geometry exported...

11.1 Nozzle Blade Detailed Design
11.2 A General Approach to Gaspath Detailed Design
11.3 Useful Curve Forms
11.4 Constructing the Annulus and Quasi-Normals
11.5 Constructing the Blade Camberline
11.6 Constructing the Blade Surfaces
11.7 The Blade Passage Throat Geometry
11.8 An Effective Gaspath Design System
11.9 Application to Impeller Design
This content is only available via PDF.
You do not currently have access to this chapter.
Close Modal

or Create an Account

Close Modal
Close Modal