OpenLaval

This program fill calculate Supersonic Impulse Turbine Blade Design

Required parameters are Specific heat ratio and inlet Mach numbers

Licence are written in the file.

Usage

Write the necessary parameters in the setting.ini file and save it before executing the following

python openLaval.py

Results are saved in the result folder.

Reference

This program was based on below papers

1. NACA RM L52B06, APPLICATION OF SUPERSONIC VORTEX-FLOW THEORY TO THE DESIGN OF SUPERSONIC IMPULSE COMPRESSOROR TURBINE-BLADE SECTIONS
2. DESIGN OF TURBINE BLADES SUITABLE FOR SUPERSONIC RELATIVE INLET VELOCITIES AND THE INVESTIGATION OF THEIR PERFORMANCE IN CASCADES: PART I-THEORY AND DESIGN
3. DESIGN OF TURBINE BLADES SUITABLE FOR SUPERSONIC RELATIVE INLET VELOCITIES AND THE INVESTIGATION OF THEIR PERFORMANCE IN CASCADES: PART 11-EXPERIMENTS, RESULTS AND DISCUSSION
4. NASA TN D-4421, ANALYTICAL INVESTIGATION OF SUPERSONIC TURBOMACHINERY BLADING: I - Computer Program for Blading Design
5. NASA TN D-4422, ANALYTICAL INVESTIGATION OF SUPERSONIC TURBOMACHINERY BLADING: II - Analysis of Impulse Turbine-Blade Sections

Done

1. Characteristic lines can be drown
2. Inlet Mach number and Gas Cp are taken in account to generate turbine blade
3. Leading Edge Cutoff partially done

Future works

1. Asymetry Blade
2. Evaluation Function Enrichment (Function are there but seems invalid yet)

of cource with constant bug fix