Blading Design for Axial Turbomachines
Abstract
The efficiency and performance of the turbomachinery components of future aero engines can considerably be improved by applying recent advances in understanding the flow behavior of axial compressor and turbine bladings. Thus, the optimal profile pressure distribution as input for new blading design methods has an important effect on losses and flow deflection. The boundary- layer behaviour has to be carefully taken into account with respect to laminar/ turbulent transition, shock/boundary-layer interaction and separation effects. In addition to these aerodynamical questions, unsteady effects and the limitations from structural and vibrational conditions also have to be taken into account. The Lecture Series deals with two main topics: -design methods and their principles, limitations - application to axial compressors and turbines, experience. Contents: Review of Turbomachinery Blading Design Problems; Design Criteria for Optimal Blading Design; Overview on Blading Design Methods; Performance Prediction for Axial-Flow Compressor and Turbine Blading; Blading Design for Multi-Stage HP Compressors; Transonic and Supersonic Compressor Blading Design; Blading Design for Cooled High-Pressure Turbines; and Aerodynamic Design of Low Pressure Turbines.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1989
- Accession Number
- ADA211103
Entities
Organizations
- AGARD