Apparatus for controlling turbine blade tip clearance and gas turbine including the same
An apparatus for controlling tip clearance between a turbine casing and a turbine blade is provided. The apparatus for controlling tip clearance includes a casing surrounding the turbine blade, a cooling plate installed in a groove, formed in a circumferential direction in the casing, and contracted by cold air supplied thereto, the cooling plate having at least one fin formed on an outer peripheral surface thereof, and a ring segment mounted radially inside the cooling plate.
1. An apparatus for controlling tip clearance between a turbine casing and a turbine blade, the apparatus comprising:
a casing surrounding the turbine blade;
a cooling plate installed in a groove, formed in a circumferential direction in the casing, and contracted by cold air supplied thereto, the cooling plate having at least one fin formed on an outer peripheral surface thereof; and
a ring segment mounted radially inside the cooling plate.
2. The apparatus according to claim 1 , wherein the cooling plate comprises a body disposed in the groove of the casing, a mounting groove formed radially inside the body, a pair of side walls extending outward from both sides on a radially outer peripheral surface of the body, and the fin extending upward from an outer peripheral surface of the body.
3. The apparatus according to claim 2 , wherein the fin is in a form of a rib disposed in a center between the pair of side walls.
4. The apparatus according to claim 3 , wherein the fin is higher than radial heights of the side walls.
5. The apparatus according to claim 2 , wherein the cooling plate further comprises mounting ribs extending outwardly from upper ends of the pair of side walls.
6. The apparatus according to claim 2 , wherein the fin includes two or more ribs formed between the pair of side walls.
7. The apparatus according to claim 6 , wherein the fin includes two ribs having a same height as the side wall and formed between the pair of side walls, and one rib having a height lower than that of the two ribs and formed between the two ribs.
8. The apparatus according to claim 2 , wherein the fin is in a form of a rib disposed in a center between the pair of side walls, and comprises a through-hole formed in a middle of the rib.
9. The apparatus according to claim 8 , wherein the through-hole is formed to be inclined at a predetermined angle with respect to a width direction of the cooling plate.
10. The apparatus according to claim 8 , wherein the pair of side walls have grooves or holes formed on inner surfaces thereof.
11. A gas turbine comprising:
a compressor configured to compress outside air;
a combustor configured to mix fuel with the air compressed by the compressor to burn a mixture thereof;
a turbine comprising a plurality of turbine blades in a turbine casing rotated by combustion gas discharged from the combustor to generate power; and
an apparatus for controlling tip clearance between the turbine casing and the turbine blade, wherein the apparatus for controlling tip clearance comprises:
a casing surrounding the turbine blade;
a cooling plate installed in a groove, formed in a circumferential direction in the casing, and contracted by cold air supplied thereto, the cooling plate having at least one fin formed on an outer peripheral surface thereof; and
a ring segment mounted radially inside the cooling plate.
12. The gas turbine according to claim 11 , wherein the cooling plate comprises a body disposed in the groove of the casing, a mounting groove formed radially inside the body, a pair of side walls extending outward from both sides on a radially outer peripheral surface of the body, and the fin extending upward from an outer peripheral surface of the body.
13. The gas turbine according to claim 12 , wherein the fin is in a form of a rib disposed in a center between the pair of side walls.
14. The gas turbine according to claim 13 , wherein the fin is higher than radial heights of the side walls.
15. The gas turbine according to claim 12 , wherein the cooling plate further comprises mounting ribs extending outwardly from upper ends of the pair of side walls.
16. The gas turbine according to claim 12 , wherein the fin includes two or more ribs formed between the pair of side walls.
17. The gas turbine according to claim 16 , wherein the fin includes two ribs having a same height as the side wall and formed between the pair of side walls, and one rib having a height lower than that of the two ribs and formed between the two ribs.
18. The gas turbine according to claim 12 , wherein the fin is in a form of a rib disposed in a center between the pair of side walls, and comprises a through-hole formed in a middle of the rib.
19. The gas turbine according to claim 18 , wherein the through-hole is formed to be inclined at a predetermined angle with respect to a width direction of the cooling plate.
20. The gas turbine according to claim 18 , wherein the pair of side walls have grooves or holes formed on inner surfaces thereof.