Alstom (switzerland) Ltd

Alstom Technology Limited

Igor A Bekrenev

Sergey Vladimirovich Trifonov

Arkadi Fokine

Igor Ossipov

Frank Hummel

A sealing arrangement for a rotor of a turbomachine includes a blade (), a heat shield () and a sealing element () for sealing between the blade () and the heat shield () when the blade (), heat shield () and sealing element () are assembled for use in the rotor. The heat shield () includes a first slot () for accommodating a first member () of the sealing element (), and a root portion of the blade () includes a second and third slot () for accommodating a second member () of the sealing element (). The first slot () extends in a direction which is substantially mutually perpendicular to a direction in which the second and third slot () extends, and the first member () extends in a direction which is substantially mutually perpendicular to a direction in which the second member () extends.

Sealing arrangement for a rotor of a turbo machine

A stator vane in an axial flow turbine can be fixed to the stator casing by means of force-fit attachment elements. The stator vane root has a hollow profile and includes radially inner platform matched to the contour of the flow channel, a radially outer platform matched to the contour of the stator casing, and two essentially parallel sidewalls. The outer platform has at least one hole for the attachment element. In one embodiment, the outer platform is detachably connected to the vane root. In other embodiments, a cavity is formed with vane root walls and with stator casing walls and is essentially tightly sealed from hot gas passing through the flow channel, allowing cooling of the cavity with little coolant loss, and allowing vanes without any seals between platforms and other vane root parts. In another embodiment, bearing surfaces of each vane are provided at different levels.

Stator vane for an axial flow turbine

The invention relates to an arrangement of guide vane platforms forming the inner contour of the flow channel in an axial-throughflow gas turbine and to a method for reducing the gap losses and for the improved cooling of the wall segments. In order to avoid the disadvantages of the generic solutions, particularly to achieve reduced thermal stress on the stator housing and on the connected vane platforms and subsequently to introduce the cooling air expended for this purpose into the flow channel in such a way that the gap losses of the shrouds of the moving blades are reduced, it is proposed, according to the invention, by dispensing with heat shields, to form the inner contour of the flow channel at least predominantly by means of the guide vane platforms and and to arrange the transitional regions between the platforms and within the cavity formed by the continuous sealing ribs and of the shroud . For this purpose, the guide vane platforms possess, on both sides, prolongations , in the direction of the respectively adjacent moving blade row and extend into the region delimited by its sealing ribs and . According to a preferred embodiment, the guide vane carriers are designed as a hollow profile, and cooling air acts at least partially on the wall voids formed between the stator housing and platforms. In a particularly preferred embodiment of the invention, the cooling air is introduced at least from the wall void into the cavity of the shroud under a pressure which is above that in the surrounding flow channel

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Moscow, Russia

Igor A Bekrenev