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: The invention relates to an aircraft engine having an outlet housing (12) arranged downstream of a low-pressure turbine (10) and having at least one follow-up guide ring (16) which is arranged within an annular chamber (14) of the outlet housing (12) and which serves for diverting a swirling hot-gas flow (18) emerging from the low-pressure turbine (10). The follow-up guide ring (16) comprises at least one blade (20) which is arranged in the annular chamber (14) and has an upstream leading edge (22), which leading edge (22) is designed such that, from its radially inner end in the direction of a radially externally situated housing wall (24) of the outlet housing (14), it runs so as to advance in the downstream direction. In this case, the leading edge (22) is configured so as to run at an angle ? of from 15° to 35° with respect to a radial line r that lies on a plane (38) formed perpendicular to an engine axis (26).

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).