Abstract: A sealing arrangement for a rotor of a turbomachine includes a blade (2), a heat shield (3, 4) and a sealing element (5, 6) for sealing between the blade (2) and the heat shield (3, 4) when the blade (2), heat shield (3, 4) and sealing element (5, 6) are assembled for use in the rotor. The heat shield (3, 4) includes a first slot (7, 8) for accommodating a first member (11, 12) of the sealing element (5, 6), and a root portion of the blade (2) includes a second and third slot (9, 10) for accommodating a second member (13, 14) of the sealing element (5, 6). The first slot (7, 8) extends in a direction which is substantially mutually perpendicular to a direction in which the second and third slot (9) extends, and the first member (11, 12) extends in a direction which is substantially mutually perpendicular to a direction in which the second member (13, 14) extends.

Abstract: A sealing arrangement for a rotor of a turbomachine includes a blade (2), a heat shield (3, 4) and a sealing element (5, 6) for sealing between the blade (2) and the heat shield (3, 4) when the blade (2), heat shield (3, 4) and sealing element (5, 6) are assembled for use in the rotor. The heat shield (3, 4) includes a first slot (7, 8) for accommodating a first member (11, 12) of the sealing element (5, 6), and a root portion of the blade (2) includes a second and third slot (9, 10) for accommodating a second member (13, 14) of the sealing element (5, 6). The first slot (7, 8) extends in a direction which is substantially mutually perpendicular to a direction in which the second and third slot (9) extends, and the first member (11, 12) extends in a direction which is substantially mutually perpendicular to a direction in which the second member (13, 14) extends.

Abstract: 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.

Abstract: 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 13 at least predominantly by means of the guide vane platforms 9 and 10 and to arrange the transitional regions 16 between the platforms 9 and 10 within the cavity 12 formed by the continuous sealing ribs 3 and 4 of the shroud 2.

Abstract: The invention relates to the design of the root of a stator vane in an axial flow turbine, for fixing the stator vane (3) to the stator casing (1) by means of attachment elements, preferably by means of attachment screws (9), which act with a force fit. In order to avoid the disadvantages of solutions of this generic type, in particular in order to reduce the thermal stress on the attachment elements and on the stator casing, the invention proposes that the stator vane root be designed as a hollow profile, comprising a radially inner platform (4) matched to the contour of the flow channel (19) and, at a distance from it, a radially outer platform (5) matched to the contour of the stator casing (1), as well as two essentially parallel sidewalls (6) and (7), wherein the outer platform (5) is equipped with at least one hole to accommodate an attachment element (9) preferably a screw, originating from the stator casing (1).

Abstract: 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.