A GAS TURBINE VANE COMPRISING AN IMPINGEMENT COOLED INNER SHROUD

The present technique presents a vane 1 for a gas turbine 10. The vane 1 has an inner shroud 100 having a pressure-wall side 102, a suction-wall side 104, a leading-edge side 106 and a trailing-edge side 108. A seal unit 70 disposed at the lower surface 100b of the inner shroud 100 and defines a first region R1 and a second region R2 at the lower surface 100b of the inner shroud 100. A first impingement unit 110 is arranged in the first region R1 and has a first impingement plate 112 facing the inner shroud 100 defining a first impingement chamber 110c thereinbetween, wherein the first impingement plate 112 receives cooling air 5 and emits impingement jets into the first impingement chamber 110c. A second impingement unit 120 is arranged in the second region R2 and comprising a second impingement plate 122 facing the inner shroud 100 defining a second impingement chamber 120c thereinbetween. At least one connector flow channel directs cooling air 5 from the first impingement chamber 110c to the second region R2. The second impingement plate 122 receives cooling air 5 from the connector flow channel 130 and forms impingement jets directed into the second impingement chamber 120c.