Gas turbine engine rotor stage with sealing members

A rotor stage for a gas turbine engine, comprising:

• a first rotor blade (FRB) having an FRB airfoil, an FRB attachment section, an FRB neck section, and an FRB platform, wherein the FRB neck section extends between the FRB attachment section and the FRB airfoil, and wherein the FRB platform extends laterally outward from the FRB neck section, and wherein the FRB platform has an FRB platform inner radial surface and an FRB platform outer radial surface;
• a second rotor blade (SRB) having an SRB airfoil, an SRB attachment section, an SRB neck section, and an SRB platform, wherein the SRB neck section extends between the SRB attachment section and the SRB airfoil, and wherein the SRB platform extends laterally outward from the SRB neck section, and wherein the SRB platform has an SRB platform inner radial surface and an SRB platform outer radial surface;
• a disk configured for rotation about a rotational axis, the disk having a forward axial end surface, an aft axial end surface, an outer radial surface that extends between the forward axial end surface and the aft axial end surface, a first disk slot configured to receive the FRB attachment section, and a second disk slot configured to receive the SRB attachment section, wherein the first disk slot and the second disk slot are circumferentially adjacent one another;
• wherein the rotor stage is configurable in an assembled state and in the assembled state the FRB attachment section is fully received in the first disk slot, and the SRB attachment section is fully received in the second disk slot, and in the assembled state the FRB platform, the SRB platform, and the outer radial surface of the disk form at least one slot;
• and
• a seal member that includes a central segment and an axial locator tab, wherein in the assembled state, the central segment is disposed for engagement with the FRB platform inner radial surface and the SRB platform, and the axial locator tab is disposed in the at least one slot;
• wherein the outer radial surface of the disk includes at least one tab surface;
• and
• wherein in the assembled state, the axial locator tab mates with a tab surface of the at least one tab surface of the outer radial surface of the disk.