Pratt-whitney Canada Corp

Yashiva Dorsamy

Domenico Di Florio

Jasrobin Grewal

Philippe Boyer

Prakul Mittal

An apparatus is provided for a gas turbine engine. This apparatus includes a bladed rotor rotatable about an axis. The bladed rotor includes a rotor disk and a plurality of rotor blades projecting radially out from the rotor disk. The rotor blades are arranged circumferentially around the rotor disk in an array. The array of the rotor blades are divided into a plurality of sectors including a first sector and a second sector. The rotor blades are disposed in the first sector including a plurality of first rotor blades. Each of the first rotor blades includes a first coating. The rotor blades are disposed in the second sector including a plurality of second rotor blades. Each of the second rotor blades includes a second coating that is different from the first coating.

Tailoring rotor blade coating to tune gas turbine engine bladed rotor

An assembly is provided for a gas turbine engine. This assembly includes an integrally bladed rotor and a damper. The integrally bladed rotor is rotatable about an axis. The integrally bladed rotor includes a plurality of rotor blades and a rotor disk. The rotor blades are arranged circumferentially around and project radially out from the rotor disk. The rotor disk includes a flange, a groove and a plurality of slots. The groove extends circumferentially around the axis within the flange. The groove projects radially into the flange from an inner side of the flange. The slots are arranged circumferentially about the axis along the groove. Each of the slots projects radially into the flange from the inner side of the flange. The damper is mounted to the rotor disk and seated within the groove.

Growing community of inventors

St Hubert, Canada

Yashiva Dorsamy