Alstom Technology Limited

James Ritchie

Andreas Boegli

Slawomir Slowik

Bruno Benedetti

Alexander Mahler

Joergen Ferber

Christopher John Hulme

Patrick Wolfgang Schnedler

Heinrich Stuessi

Christopher Hulme

A turbomachine (), in particular a turbine or compressor, includes a rotor () which has at least one moving blade row () with a plurality of moving blades (), and a stator () which has at least one guide vane row () with a plurality of guide vanes (), at least in one of the blade or vane rows () all the blades or vanes () each having a shroud plate (). In order to simplify the maintenance of the turbo-machine (), the shroud plates () are separate components with respect to the respective blade or vane () and are mounted on the respective blade or vane (), shroud plates () adjacent in the circumferential direction () being coupled to one another for the transmission of tensile forces in the circumferential direction ().

Turbomachine

A blade for a turbo machine has a blade section and a shroud element terminating the blade section in the blade section longitudinal direction. The blade section has a suction face and a pressure face. The shroud element extends essentially at right angles to the blade section longitudinal direction and has a first platform section projecting beyond the blade section and a second platform section projecting beyond the blade section. The platform sections are asymmetric with respect to one another. At least the first platform section of the shroud element is arranged at an additional inclination angle with respect to a normal alignment of the first platform section, with the additional inclination angle being in the opposite direction to the bending torque which acts on the first platform section during operation.

Blade with shroud

A guide vane ring of a turbomachine, in particular of an axial-throughflow turbine, includes a vane group () having a plurality of vanes (). The vane group () has a vane root () which has two flanges (). The vane group () is fastened to a vane carrier by means of the flanges (). In order to reduce stresses in the vanes () which occur during deformations of the vane carrier, one flange () has on a front end portion () and on a rear end portion (), radially on the inside and radially on the outside, in each case a contact zone () which bears against the vane carrier. The other flange () has on one end portion (), radially on the inside, a contact zone () which bears against the vane carrier, and is spaced apart from the vane carrier radially on the outside. Moreover, this flange () has on the other end portion (), radially on the outside, a contact zone () which bears against the vane carrier, and is spaced apart from the vane carrier radially on the inside. Furthermore, the flanges (), between their end portions (), are spaced apart from the vane carrier radially on the inside and radially on the outside.

Guide vane ring of a turbomachine and associated modification method

A turbomachine blade is disclosed having a shroud element, wherein plastic deformations and lifting of the shroud element on one side result during operation under centrifugal load. This load may result in high-temperature creep of the blade. A sealing strip which is arranged on the shroud element can be configured with a thickness varying in a circumferential direction. The mass of the shroud element and thus the asymmetrical centrifugal load and the lifting of the shroud element on one side resulting therefrom can be reduced by material removal at regions lying on the outside in the circumferential direction.

Turbomachine blade

A method of reconditioning a rotating blade () with a shroud () following the operation in a gas turbine, includes the application of a barrier () placed on the edge of the shroud () facing the edge of a shroud () of an adjacent blade having creep deformation. The barrier () prevents hot gas ingestion into a shroud cavity (). It is pre-fabricated or built-up layer-by-layer by welding or laser cladding or other methods. Additionally, the mass of the shroud () is reduced in order to re-establish the initial mass of the shroud. A thermal barrier coating () is additionally applied to the surfaces of the shroud () that are exposed to the hot gas of the turbine. The method significantly increases the lifetime of the blade ().

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Ennetbaden, Switzerland

James Ritchie