Hey guys and gals! first time poster so be gentle....I'm wanting to make a small jet turbine from scratch but im totally baffled by how to design the compressor and turbine stages for compressing the air and extracting power from the exhaust gas to drive the compressor. i would ideally like a two stage compressor with a compression ratio of about 2, although the higher the better (but no more than two stages) and an blade diameter of 20 cm. Im having difficulty with the blade angles. As iv never done aerodynamics before i need a dummies guide on how to derive the angles of the blades from compression ratio and blade diameter (if thats possible). also can someone explain what the "turning angle" of the blade is? any information on this is much appreciated!!!!