Gas turbine split ring
AssigneeMitsubishi Heavy Industries, Ltd.
InventorsTatsuaki Fujikawa, Yasuoki Tomita, Shunsuke Torii, Ryotaro Magoshi, Masamitsu Kuwabara, Shinichi Inoue
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Abstract
In the gas turbine split ring, on an outer peripheral surface 1b between two cabin attachment flanges, a circumferential rib which extends in the circumferential direction and an axial rib which extends in the axial direction and has a height taller than that of the circumferential rib are, respectively, formed in plural lines, so that it is possible to suppress heat deformation in the axial direction which largely contributes to reduction of the tip clearance compared to head deformation in the circumferential direction more efficiently.
Claims3
A gas turbine split ring which is provided on a peripheral surface in a cabin at a predetermined distance with respect to a tip end of a moving blade, the split ring comprising a plurality of split structure segments connected in a circumferential direction to form a circular ring shape, each split structure segment having cabin attachment flanges extending in the circumferential direction on both of an upstream side and a downstream side of the split ring,
- wherein on an outer peripheral surface between the two cabin attachment flanges of the split structure segment, a circumferential rib which extends in the circumferential direction and an axial rib which extends in a direction parallel to an axis of the circular ring shape and has a height taller than the circumferential rib are formed in plural lines.
Dependencies are inferred from the claim text.