The Design of a Transonic Gas Turbine Stator.
Abstract
A turbine stator profile that is analytically predicted to exhibit good aerodynamic performance over a wide range of transonic operating conditions has been designed for the Air Force Aero Propulsion Laboratory's Heat Transfer Facility. Analytical Turbine Design System computer programs developed by General Electric Company were used to generate blade profiles/coordinates and perform 2-Dimensional cascade through-flow calculations (streamline curvature technique). Two aerodynamic performance standard were applied to pressure distribution predictions of the blade contours produced from a parametric variation study; 1) equal flow expansion over both the suction and pressure surfaces, and 2) minimum suction surface diffusion. The influence of he following geometric parameters upon the design of a transonic turbine stator were investigated; axial location of maximum section thickness, stagger angle, leading edge bluntness factor, and trailing edge taper factor. Results of this study show that a good transonic turbine stator design must have a convergent-divergent flow passage and a flat suction surface aft of the throat location. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1978
- Accession Number
- ADA081903
Entities
People
- Robert N. Gamache
Organizations
- Air Force Institute of Technology