Patent ID: 7399164

Claim:
A turbine engine, comprising: a compression stage including a rotor and a plurality of turbine blades positioned side by side in a circumferential direction of the rotor, each turbine blade having a blade root, each turbine blade being securable via the blade root in a retainer groove which extends in the circumferential direction of the rotor, each turbine blade being insertable with its blade roots into the retainer groove via a filling groove, the width of the blade roots and the width of the filling groove being greater in the circumferential direction than one-half of the width of a desired, nominal blade pitch; wherein the plurality of turbine blades include a first plurality of turbine blades and a second plurality of turbine blades, the first plurality of turbine blades having the desired, nominal blade pitch and the second plurality of turbine blades having a blade pitch greater than the desired nominal blade pitch, the second plurality of turbine blades being in an area of the filling groove, the first plurality being greater in number than the second plurality.