A turbomachine including an improved backflow margin includes a combustor portion fluidly connected to a turbine portion. The turbine portion (6) includes a gas path, a first stage having a first plurality of airfoil members (30,32) arranged along the gas ...

Multiple compression stages (ST1-ST5) are arranged one behind the other between the compressor inlet (14) and the compressor outlet (15). Each stage has one ring of rotor blades (R) and one ring of stator blades (S). A change in the geometry of the blades ...