Blade for a gas turbine
View Patent ↗The blade for a gas turbine includes a blade airfoil having a leading edge and a trailing edge and extending in the blade longitudinal direction up to a blade tip, and at the blade tip the blade airfoil merges into a shroud segment, wherein on the shroud segment a first rib, projecting upwards, is arranged in the flow direction, extending transversely to the flow direction, and upstream of the first rib, in the region of the leading edge of the blade airfoil, a winglet is formed on the shroud segment for guiding of the hot gas flow in this region. With such a blade, a longer service life is achieved by provision being made for direct cooling of the winglet.
1. A blade for a gas turbine, comprising:
a blade airfoil having a leading edge and a trailing edge extending in a blade longitudinal direction up to a blade tip, and at the blade tip the blade airfoil merges into a shroud segment;
a first rib, projecting upwards, arranged on the shroud segment in a flow direction of a hot gas flow, extending transversely to said flow direction;
a winglet formed on the shroud segment upstream of the first rib, in a region of the leading edge of the blade airfoil, for guiding a hot gas flow in this region; and
a plurality of cooling holes which extend inside the winglet for direct cooling of the winglet, wherein the winglet comprises a leading terminal edge for arranging transversely to the flow direction of the hot gas flow wherein the entire leading terminal edge is curved, the plurality of cooling holes being led up to the curved portion of the leading terminal edge of the winglet obliquely, and
wherein the cooling holes are in communication with a cooling passage arranged in an interior of the blade airfoil and below a central portion of the first rib for supply with a cooling medium, the cooling holes leading up to the leading terminal edge of the winglet obliquely from the central portion of the first rib only to portions of the winglet on either side of the blade airfoil.
2. The blade as claimed in claim 1 , wherein the cooling holes are guided to the leading terminal edge of the winglet so that a plurality of cooling holes are arranged on both sides of the blade airfoil.
3. The blade as claimed in claim 2 , wherein the cooling holes are in communication with an interior of the blade airfoil for supply with a cooling medium.
4. The blade as claimed in claim 1 , wherein the cooling medium is air.
5. The blade as claimed in claim 3 , wherein the cooling medium is air.
6. The blade as claimed in claim 1 , in combination with a gas turbine.
7. A blade for a gas turbine, comprising:
a blade airfoil having a leading edge and a trailing edge extending in a blade longitudinal direction up to a blade tip, and at the blade tip the blade airfoil merges into a shroud segment;
a first rib, projecting upwards, arranged on the shroud segment in a flow direction, extending transversely to said flow direction;
a winglet formed on the shroud segment upstream of the first rib, in a region of the leading edge of the blade airfoil, for guiding a hot gas flow in this region, the winglet including a leading terminal edge flow wherein the entire leading terminal edge is arc-shaped; and
a plurality of cooling holes which extend inside the winglet for direct cooling of the winglet,
wherein the cooling holes are guided to the arc-shaped portion of the leading terminal edge of the winglet so that a plurality of cooling holes are arranged on both sides of the blade airfoil, and
wherein the cooling holes are in communication with a cooling passage arranged in an interior of the blade airfoil and below a central portion of the first rib for supply with a cooling medium, the cooling holes leading up to the leading terminal edge of the winglet obliquely from the central portion of the first rib only to portions of the winglet on either side of the blade airfoil.
8. The blade as claimed in claim 7 , wherein the cooling holes are arranged obliquely to the flow direction of the hot gas flow.
9. The blade as claimed in claim 7 , wherein the cooling holes are in communication with an interior of the blade airfoil for supply with a cooling medium.
10. The blade as claimed in claim 7 , wherein the cooling medium is air.
11. The blade as claimed in claim 8 , wherein the cooling medium is air.
12. The blade as claimed in claim 7 , in combination with a gas turbine.