Moving blade row of high peripheral speed for thermal axial-flow turbo machines

Claim 2

A moving blade row of high peripheral speed for thermal axial flow turbo machines, especially for the last stage of condensing steam turbines, in which each of the blades of said blade row has a suction surface side and a pressure surface side and when viewed in radial direction has a middle region and an outer region located in the range of transonic flow, said middle region starting from the trailing edge being formed by two straight sections respectively located on said suction surface side and on said pressure surface side, the straight section on said suction surface side merging in a steady manner with the remaining suction surface side which latter curves in a steady manner toward said pressure surface side, and said straight section at said pressure surface side near the trailing edge of each of said blades merging with the remaining surface side while forming therewith a distinct angle, the improvement therewith whereby space between adjacent blades from the suction surface side of one blade to the pressure surface side of the adjacent blade at one location has a narrowest cross section forming a flow passage therebetween in boundaries defined by intersection of a straight section and the trailing edge of one blade as well as defined by point intersection of a straight section and the pressure surface side of the adjacent blade, with an angle formed between the latter straight section and a tangent to the pressure surface side at the point intersection being matched to supersonic flow regime.

Claim 3

A moving blade row of high peripheral speed for thermal axial flow turbo machines, especially for the last stage of condensing steam turbines, in which each of the blades of said blade row has a suction surface side and a pressure surface side and when viewed in radial direction has a middle region and an outer region located in the range of transonic flow, said middle and outer regions starting from the trailing edge being formed by two straight sections respectively located on said suction surface side on said pressure surface side, the straight section on said suction surface side merging in a steady manner with the remaining suction surface side which latter curves in a steady manner toward said pressure surface side, and said straight section at said pressure surface side near the trailing edge of each of said blades merging with the remaining surface side while forming therewith a distinct angle, the improvement therewith whereby space between adjacent blades from the suction surface side of one blade to the pressure surface side of the adjacent blade at one location has a narrowest cross section forming a flow passage therebetween in boundaries defined by intersection of a straight section and the trailing edge of one blade as well as defined by point intersection of a straight section and the pressure surface side of the adjacent blade with an angle formed between the latter straight section and a tangent to the pressure surface side at the point intersection being matched to supersonic flow regime.

Claim 4

A moving blade row of high peripheral speed for thermal axial flow turbo machines, especially for the last stage of condensing steam turbines, in which each of the blades of said blade row has a suction surface side and a pressure surface side and when viewed in radial direction has a middle region and an outer region located in the range of transonic flow, said middle and outer regions starting from the trailing edge being formed by two straight sections respectively located on said suction surface side on said pressure surface side, the straight section on said suction surface side merging in a steady manner with the remaining suction surface side which latter curves in a steady manner toward said pressure surface side, and said straight section at said pressure surface side near the trailing edge of each of said blades merging with the remaining surface side while forming therewith a distinct angle, the improvement therewith whereby space between adjacent blades from the suction surface side of one blade to the pressure surface side of the adjacent blade at one location has a narrowest cross section forming a flow passage therebetween in boundaries defined by intersection of a straight section and the trailing edge of one blade as well as defined by point intersection of a straight section and the pressure surface side of the adjacent blade with an angle formed between the latter straight section and a tangent to the pressure surface side at the point intersection being matched to supersonic flow regime.

Claim 5

A moving blade row according to claim 1, wherein said distinct angle occurs to provide discontinuity at the pressure surface side causing part of corner expansion generally at the trailing edge of the blade to be shifted into the passage between the blades.

Claim 6

A moving blade row according to claim 3, wherein the straight section of the pressure surface side is substantially shorter than that of the trailing edge.

Claim 7

A moving blade row according to claim 4, wherein steam enters the blade row at subsonic velocity and accordingly flow is transonic in middle and outer parts of the blade row only to leave the blade row after a marked deflection at supersonic velocity.

Claim 8

A moving blade row according to claim 5, wherein lower profile losses occur at outlet Mach numbers between 1 and 1.5 and smaller outlet angles are permitted.

Claim 9

A moving blade row according to claim 2, wherein said distinct angle occurs to provide discontinuity at the pressure surface side causing part of corner expansion generally at the trailing edge of the blade to be shifted into the passage between the blades.

Claim 10

A moving blade row according to claim 7, wherein the straight section of the pressure surface side is substantially shorter than that of the trailing edge.

Claim 11

A moving blade row according to claim 8, wherein steam enters the blade row at subsonic velocity and accordingly flow is transonic in middle and outer parts of the blade row only to leave the blade row after a marked deflection at supersonic velocity.

Claim 12

A moving blade row according to claim 9, wherein lower profile losses occur at outlet Mach numbers between 1 and 1.5 and smaller outlet angles are permitted.