Turbomachine having a gas flow aeromechanic system and method

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 path, and a second stage having a second plurality of airfoil members (40,42), arranged along the gas path (15) downstream from the first stage. The first plurality of airfoil members (30,32) are configured to intercept combustion gases (50) from the combustor portion at a first momentum and create a wake zone (60) having a second momentum that is lower than the first momentum. The turbomachine includes a gas flow aeromechanics system (80) configured and disposed to improve gas flow aeromechanics along the gas path by circumferentially clocking the second plurality of airfoil members (40,42) relative to the first plurality of airfoil members (30,32) to intercept the wake zone (60) at the second momentum.