Blade, cut-back of blade or vane and gas turbine having the same
A cut-back of a blade or vane in a gas turbine may comprise a first sidewall; a plurality of trailing ribs extended from the first sidewall and arranged along an end of the first sidewall; a second sidewall separated from the first sidewall, having a longer tail than the first sidewall and in contact with the plurality of trailing ribs; and one or more cut-back blocks extended between two trailing ribs along the inner surface of the second sidewall. The cut-back of the blade or vane may reduce the weight through the trailing ribs and the cut-back blocks formed at the trailing edge, and improve a heat transfer effect while retarding crack growth.
1. A blade of a gas turbine, comprising:
a first sidewall constituting a pressure side of an airfoil having a leading edge and a trailing edge;
a second sidewall opposing the first sidewall and constituting a suction side of the airfoil, the second sidewall having a tail that is longer than a tail of the first sidewall such that a tail end of the first sidewall is separated from a tail end of the second sidewall in a direction of a chord line of the airfoil;
a plurality of trailing ribs that are arranged along the trailing edge and that extend from the tail end of the first sidewall to the tail end of the second sidewall; and
a plurality of cut-back blocks each of which extends from a first inner wall of one of a pair of adjacent trailing ribs among the plurality of trailing ribs to a second inner wall of the other of the pair of adjacent trailing ribs and is disposed obliquely with respect to the tail end of the second sidewall.
2. The blade of claim 1 , wherein each cut-back block of the plurality of cut-back blocks includes a pair of parallel cut-back block members respectively extending between the first and second inner walls.
3. The blade of claim 2 , wherein the each of the pair of parallel cut-back block members has a shape protruding from an inner surface of the tail of the second sidewall.
4. The blade of claim 3 , wherein the shape includes a front surface and a rear surface, the front surface having a gentler slope than the rear surface.
5. The blade of claim 4 , wherein the front and rear surfaces are flat.
6. The blade of claim 5 , wherein the shape further includes a top surface that is parallel to the inner surface of the tail of the second sidewall.
7. The blade of claim 4 , wherein the front and rear surfaces are curved.
8. The blade of claim 7 , wherein the shape further includes a curved top surface.
9. The blade of claim 1 , wherein the plurality of trailing ribs further extend from an inner surface of the tail of the first sidewall to an inner surface of the tail of the second sidewall.
10. The blade of claim 1 , further comprising a pillar-shaped fin extended between the inner surface of the tail of the first sidewall and the inner surface of the tail of the second sidewall.
11. The blade of claim 1 , wherein each of the plurality of trailing ribs has a width that gradually decreases from the tail end of the first sidewall to the tail end of the second sidewall.
12. The blade of claim 1 , wherein the plurality of trailing ribs are spaced apart from each other at regular intervals extending between a top and a bottom of the trailing edge.
13. The blade of claim 12 ,
wherein the adjacent trailing ribs include at least one upper pair of adjacent trailing ribs arranged at the top of the trailing edge and central adjacent trailing ribs arranged in a central portion of the trailing edge between the top and the bottom of the trailing edge,
wherein the plurality of cut-back blocks include upper cut-back blocks disposed between the at least one upper pair of adjacent trailing ribs, and
wherein there are no cut-back blocks disposed between any of the central adjacent trailing ribs.
14. The blade of claim 12 ,
wherein the adjacent trailing ribs include at least one lower pair of adjacent trailing ribs arranged at the bottom of the trailing edge and central adjacent trailing ribs arranged in a central portion of the trailing edge between the top and the bottom of the trailing edge,
wherein the plurality of cut-back blocks include lower cut-back blocks disposed between the at least one lower pair of adjacent trailing ribs, and
wherein there are no cut-back blocks disposed between any of the central adjacent trailing ribs.
15. The blade of claim 1 , wherein the trailing edge of the airfoil is formed by a continuous surface including an outer surface of the tail of the first sidewall, an outer surface of the plurality of trailing ribs, the tail end of the second sidewall, and an outer surface of the tail of the second sidewall.
16. The blade of claim 1 , wherein the tail end of the first sidewall is separated from the tail end of the second sidewall by a distance that is greater than a height of any one of the plurality of cut-back blocks.
17. A cut-back of a blade in a gas turbine, the cut-back comprising:
a first sidewall;
a second sidewall opposing the first sidewall and having a tail that is longer than and separated from a tail of the first sidewall;
a plurality of trailing ribs that are spaced apart from each other at regular intervals along a trailing edge of the blade and that extend from the tail end of the first sidewall to the tail end of the second sidewall; and
a plurality of cut-back blocks each of which extends from a first inner wall of one of a pair of adjacent trailing ribs among the plurality of trailing ribs to a second inner wall of the other of the pair of adjacent trailing ribs and is disposed obliquely with respect to the tail end of the second sidewall.
18. The cut-back of claim 17 , wherein each cut-back block of the plurality of cut-back blocks includes a pair of cut-back block members respectively extending between the first and second inner walls, and the cut-back block members are parallel to each other such that each cut-back block member is disposed obliquely with respect to the tail end of the second sidewall.
19. A gas turbine comprising:
a compressor section configured to compress working fluid, the compressor section including a rotor disk having an outer circumferential surface of which a compressor blade is mounted;
a combustor configured to produce combustion gas by mixing the compressed working fluid with fuel and combusting the mixture; and
a turbine section configured to produce power using the combustion gas, the turbine section including a rotor disk having an outer circumferential surface of which a turbine blade is mounted,
wherein at least one of the compressor blade and the turbine blade comprises:
a first sidewall constituting a pressure side of an airfoil having a leading edge and a trailing edge;
a second sidewall opposing the first sidewall and constituting a suction side of the airfoil, the second sidewall having a tail that is longer than a tail of the first sidewall such that a tail end of the first sidewall is separated from a tail end of the second sidewall in a direction of a chord line of the airfoil;
a plurality of trailing ribs that are arranged along the trailing edge and that extend from the tail end of the first sidewall to the tail end of the second sidewall; and
a plurality of cut-back blocks each of which extends from a first inner wall of one of a pair of adjacent trailing ribs among the plurality of trailing ribs to a second inner wall of the other of the pair of adjacent trailing ribs and is disposed obliquely with respect to the tail end of the second sidewall.
20. The gas turbine of claim 19 , wherein each cut-back block of the plurality of cut-back blocks includes a pair of cut-back block members respectively extending between the first and second inner walls, and the cut-back block members are parallel to each other such that each cut-back block member is disposed obliquely with respect to the tail end of the second sidewall.