Abstract: A seal carrier for a turbomachine for sealing a gap between a stator section and a rotor section, having a base body, which is provided on one side with a run-in coating; the base body at least having one hollow space, which is open via at least one opening to the run-in coating, creating a Helmholtz resonator; the area of the run-in coating, which is provided with the at least one opening, providing the oscillating mass of the Helmholtz resonator, and the at least one hollow space, the spring volume thereof.

Abstract: A method for designing a turbine having a plurality of stages disposed axially one behind the other in the direction of flow through the turbine, each stage being formed of a stationary row of a plurality of stator vanes and a rotating row of a plurality of rotor blades. The row of rotor blades of at least one of these stages has a plurality of rotor blade clusters each formed of at least two rotor blades (A1, B1; A2, B2) having different airfoil profiles and/or different distances (?A, ?B) from adjacent rotor blades following in the direction of rotation. A vane-to-blade-cluster ratio (V/(B/P)) parameter indicates the ratio of the number of stator vanes (V) to the quotient (B/P) of the number of rotor blades (B) of the stage divided by the number of rotor blades per rotor blade cluster (P).

Abstract: A method for designing a turbine of a gas turbine, in particular of an aircraft engine, which has a last stage having a rotating last rotor grid, having a plurality of rotating blades, and an adjacent, downstream, stationary exit guide grid, having a plurality of guide vanes; with the last stage being characterized by a vane-to-blade ratio characteristic quantity, which indicates the ratio of the number of guide vanes to the number of rotating blades.

Abstract: The present invention relates to a method for designing a turbine of a gas turbine, in particular of an aircraft engine, which has a last stage having a rotating last rotor grid, having a plurality of rotating blades (1), and an adjacent, downstream, stationary exit guide grid, having a plurality of guide vanes (2); with the last stage being characterized by a vane-to-blade ratio characteristic quantity ((V/B)TEC, 1; (V/B)TEC, 2), which indicates the ratio of the number of guide vanes to the number of rotating blades.

Abstract: A method for designing a turbine having a plurality of stages disposed axially one behind the other in the direction of flow through the turbine, each stage being formed of a stationary row of a plurality of stator vanes and a rotating row of a plurality of rotor blades. The row of rotor blades of at least one of these stages has a plurality of rotor blade clusters each formed of at least two rotor blades (A1, B1; A2, B2) having different airfoil profiles and/or different distances (?A, ?B) from adjacent rotor blades following in the direction of rotation. A vane-to-blade-cluster ratio (V/(B/P)) parameter indicates the ratio of the number of stator vanes (V) to the quotient (B/P) of the number of rotor blades (B) of the stage divided by the number of rotor blades per rotor blade cluster (P).