Turbomachine and turbomachine stage

A turbomachine stage comprising:

• guide vanes and at least one of a radially inner and radially outer guide vane airfoil platform defining a guide vane cascade, the guide vane airfoil platform having a guide vane platform cascade region and a guide vane gap region;
• and
• rotor blades and at least one of a radially inner and radially outer rotor blade airfoil platform defining a rotor blade cascade, the rotor vane airfoil platform having a rotor vane platform cascade region and a rotor vane gap region, the rotor blade cascade being adjacent to the guide vane cascade,
• the guide vane gap region and the rotor vane gap region at least one of radially and axially bounding an axial gap extending axially between the guide vane cascade and the rotor blade cascade,
• a contour of at least one of the guide vane and rotor vane gap regions varying in at least one of the radial and axial direction around a circumference,
• at least one of (a) and (b) being true:
• (a) a maximum extent of the contour in the radial direction toward a spoke-like pattern of the respective guide vane or rotor vane cascade being circumferentially spaced from a respective airfoil edge of the respective guide vane or rotor vane cascade by no more than 50% of the pitch of the respective guide vane or rotor vane cascade, a maximum variation of the contour in the radial direction being no more than 50%, of the pitch of the respective guide vane or rotor vane cascade;
• and
• (b) a maximum extent of the contour in the axial direction away from the spoke-like pattern is circumferentially spaced from the respective airfoil edge of the respective guide or rotor vane cascade by no more than 50%, a maximum variation of the contour in the axial direction being no more than 50% of the pitch of the respective guide vane or rotor vane cascade.