Guide vane, guide vane cluster, and housing for a gas turbine as well as gas turbine having a platform with an arched wall section to receive a damper
The invention relates to a guide vane for a gas turbine, comprising an airfoil, a platform arranged at a radial end of the airfoil, an upstream flange extending radially from the platform, and a downstream flange extending radially from the platform, wherein the flanges, together with a section of the platform lying between the flanges, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damping element. A surface of the section of the platform bounding the groove is arched radially at least in regions thereof in the direction of an opening of the groove. The invention further relates to a guide vane cluster, a housing for a gas turbine, as well as to a gas turbine.
1 . A guide vane for a gas turbine, comprising an airfoil having a radial outer end and a radial inner end:
a platform connected to the radial outer end of the airfoil and the radial inner end of the airfoil being exposed,
an upstream flange extending radially from the platform, and
a downstream flange extending radially from the platform,
wherein the flanges, together with a section of the platform lying between the flanges, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damper,
wherein a wall section of the platform, between the upstream flange and the downstream flange and bounding the groove, has a radially arched shape at least in regions thereof in the direction of an opening of the groove; the wall section of the platform having a middle section, an axial upstream section and an axially downstream section; the middle section being more radially outward than the axial upstream section and the axial downstream section; a surface of the platform facing away from the groove being arched radially at least in regions thereof in the direction of the groove.
2 . The guide vane according to claim 1 , wherein, in cross section, the wall section of the platform has a uniform wall thickness.
3 . The guide vane according to claim 1 , wherein the airfoil has an exposed vane tip with respect to the platform.
4 . The guide vane according to claim 1 , wherein the upstream flange has a downstream overhang in the groove, and/or in that the downstream flange comprises an upstream overhang in the groove, and/or in that the upstream flange has an upstream overhang, which, together with the platform, forms a further groove extending in the circumferential direction of the gas turbine, and/or the downstream flange has a downstream overhang, which, together with the platform, forms a further groove extending in the circumferential direction of the gas turbine.
5 . A guide vane cluster for the gas turbine, in which at least two guide vanes according to claim 1 , are connected to one another by way of at least one common platform for the radial bounding of a flow channel of the gas turbine.
6 . An aircraft engine with at least one guide vane cluster according to claim 5 .
7 . An aircraft engine with at least one guide vane according to claim 1 .
8 . A housing for a gas turbine, with a flow channel, comprising:
a plurality of guide vanes each including:
a radial outer end and a radial inner end,
a platform connected to the radial outer end of the airfoil and the radial inner end of the airfoil being exposed,
an upstream flange extending radially from the platform, and
a downstream flange extending radially from the platform,
wherein the flanges, together with a section of the platform lying between the flange, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damper,
wherein a wall section of the platform, between the upstream flange and the downstream flange and bounding the groove, has a radially arched shape at least in regions thereof in the direction of an opening of the groove; the wall section of the platform having a middle section, an axial upstream section and an axially downstream section; the middle section being more radially outward than the axial upstream section and the axial downstream section; a surface of the platform facing away from the groove being arched radially at least in regions thereof in the direction of the groove;
and/or a plurality of guide vane clusters each including:
at least two of the guide vanes connected to one another by way of at least one common platform for the radial bounding of a flow channel of the gas turbine;
are arranged in a cascade manner, wherein the grooves of the guide vanes and/or the guide vane clusters extending in the circumferential direction of the gas turbine are aligned flush with one another, and wherein at least one damper is arranged in at least one of the grooves.
9 . The housing according to claim 8 , wherein the at least one damper has a recess in the region of the section of the associated platform arched radially in the direction of an opening of the groove, and/or, in cross section, the damper is U-shaped or O-shaped or clamp-shaped in design, and/or the damper is configured and arranged to be linear in the circumferential direction.
10 . The housing according to claim 8 , wherein, in cross section, the damper has at least three contact points in the groove, and/or the damper has at least two contact points with the housing.
11 . The housing according to claim 8 , wherein the damper is arranged in a bridging manner between at least two mutually adjacent guide vanes and/or guide vane clusters.
12 . An aircraft engine with at least the housing according to claim 8 .