Rotor assembly

A compressor for a gas turbine engine, the compressor comprising:

• a stator assembly comprising at least one circumferential row of stator vanes;
• a rotor assembly configured to rotate relative to the stator assembly about a longitudinal centerline of the gas turbine engine, the rotor assembly comprising:
• a rotor disk comprising a first rotor attachment member comprising a first mount slot and a second rotor attachment member comprising a second mount slot, the rotor disk further comprising an outer diameter surface extending between the first rotor attachment member and the second rotor attachment member;
• a rotor blade comprising an airfoil, a platform, a first mount retained within the first mount slot, and a second mount retained within the second mount slot, the platform comprising an inner platform surface facing the outer diameter surface of the rotor disk, wherein the rotor disk and the rotor blade define a circumferential portion of a circumferentially-extending cavity between the inner platform surface, the outer diameter surface of the rotor disk, the first rotor attachment member, and the second rotor attachment member;
• and
• a seal disposed within the circumferentially-extending cavity, the seal comprising at least one sealing ring disposed about the rotational axis, the at least one sealing ring in contact with the inner platform surface of the platform and radially spaced from the outer diameter surface of the rotor disk;
• wherein each of the first rotor attachment member and the second rotor attachment member extend radially outward from the outer diameter surface of the rotor disk to respective first and second distal ends adjacent the inner platform surface of the platform, wherein the first mount slot and the second mount slot extend a first radial distance from the respective first and second distal ends toward the outer diameter surface of the rotor disk, and wherein the first mount slot and the second mount slot are spaced from the outer diameter surface of the rotor disk by a second radial distance.

A method for assembling a rotor assembly for a piece of rotational equipment, the method comprising:

• radially inserting a rotor blade into a rotor disk comprising a first rotor attachment member comprising a first mount slot and a second rotor attachment member comprising a second mount slot, the rotor disk further comprising an outer diameter surface extending between the first rotor attachment member and the second rotor attachment member;
• and
• axially inserting a first mount of the rotor blade into the first mount slot and a second mount of the rotor blade into the second mount slot, the rotor blade comprising an airfoil and a platform comprising an inner platform surface facing the outer diameter surface;
• wherein the rotor disk and the rotor blade define a circumferential portion of a circumferentially-extending cavity between the inner platform surface, the outer diameter surface, the first rotor attachment member, and the second rotor attachment member, the method further comprising:
• inserting a seal into the circumferentially-extending cavity before the step of radially inserting the rotor blade into the rotor disk, the seal comprising a first sealing ring and a second sealing ring axially adjacent the first sealing ring within the circumferentially-extending cavity.