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AssigneeMTU Aero Engines AG
InventorsHans-Peter Borufka, Hernan Victor Arrieta, Klemens Hain
Estimating the term…
A shroud for the rotating blades of a turbo machine, particularly a gas turbine, in which shroud is arranged along the circumference of a row of several rotating blades disposed on a rotor and has at least one separation gap along its circumference. The separation gap is formed in zigzag shape and has at least three damping gaps that are distanced from one another and extend at an angle relative to an axis of rotation of the rotor, and adjacent to these, has connection gaps each connecting damping gaps or extending the latter in the direction of shroud edges, wherein, when the rotor rotates, the gap width of damping gaps is reduced until the gap walls forming the damping gaps come to rest against each other.
A shroud for the rotating blades of a turbo machine wherein a shroud (10) is arranged along the circumference of a row of several rotating blades (14, 50) disposed on a rotor (12) and has at least one separation gap (16, 16′, 16″) along its circumference, the at least one separation gap (16, 16′, 16″) is formed in zigzag shape and has at least two damping gaps (20, 22, 24, 26, 28) which are distanced from one another and extend at an angle to an axis of rotation (18) of rotor (12), and adjacent thereto, one of the damping gaps (28) running at an acute angle to remaining damping gaps (20, 22, 24, 26) which are aligned at an angle of 60° to 90° relative to the axis of rotation (18) of rotor (12), has connection gaps (30, 32, 34, 36, 38, 40), each connecting damping gaps (20, 22, 24, 26, 28) or extending them in the direction of the edges of the shroud (54, 56), is hereby characterized in that, when rotor (12) rotates, the gap width of damping gaps (20, 22, 24, 26, 28) is reduced until the gap walls (42, 44) forming the damping gaps (20, 22, 24, 26, 28) come to rest against each other.
A shroud for the rotating blades of a turbo machine wherein a shroud (10) is arranged along the circumference of a row of several rotating blades (14, 50) disposed on a rotor (12) and has at least one separation gap (16, 16′, 16″) along its circumference, the at least one separation gap (16, 16′, 16″) is formed in zigzag shape and has at least five damping gaps (20, 22, 24, 26, 28) which are distanced from one another and extend at an angle to an axis of rotation (18) of rotor (12), and adjacent thereto, wherein a total of four damping gaps (20, 22, 24, 26) are aligned parallel to one another and another damping gap (28) runs at an acute angle to the four damping gaps (20, 22, 24, 26), has connection gaps (30, 32, 34, 36, 38, 40), each connecting damping gaps (20, 22, 24, 26, 28) or extending them in the direction of the edges of the shroud (54, 56), is hereby characterized in that, when rotor (12) rotates, the gap width of damping gaps (20, 22, 24, 26, 28) is reduced until the gap walls (42, 44) forming the damping gaps (20, 22, 24, 26, 28) come to rest against each other.
Dependencies are inferred from the claim text.