Method for profiling blades of an axial turbomachine

A method for profiling blades of an axial turbomachine comprising:

• a) preparing a geometric model of a blade profile (R, −1, +1);
• b) determining an oscillation mode of the geometric model;
• c) calculating a time profile of a position-dependent disruptive pressure p({right arrow over (x)}, t)=pges({right arrow over (x)}, t)−p0({right arrow over (x)} ) in a channel between two adjacent blade profiles over an oscillation period of an oscillation belonging to the oscillation mode,
• wherein in order to calculate the profile it is assumed that the position-dependent disruptive pressure p({right arrow over (x)}, t) in the channel is proportional to a magnitude of a surface ({right arrow over (x)}, t) which extends in the channel and is arranged perpendicular to the flow lines between blade surfaces bounding the channel, and perpendicular to these blade surfaces,
• wherein {right arrow over (x)} is a coordinate on one of the two blade surfaces,
• t is time,
• p0({right arrow over (x)}) is a position-dependent pressure when the blade profile is stationary, and
• pges({right arrow over (x)}, t) is a position-dependent total pressure;
• d) determining a damping of an oscillation caused by the position-dependent disruptive;
• e) changing the geometric model and determining a different oscillation mode for the changed geometric model, as well as carrying out step c) with the changed geometric model and the different oscillation mode;
• and
• f) determining a damping of an oscillation using the disruptive pressure profile p({right arrow over (x)}, t) calculated in step e) and accepting the changed geometric model for the case that the damping of the oscillation turns out to be greater than damping of the oscillationin step d), otherwise repeating steps e) and f) with another changed geometric model.