초록 ▼

A gas turbine moving blade is provided which prevents occurrence of cracks caused by thermal stresses due to temperature differences between a blade and a platform while the gas turbine is being stopped. During steady operation time of the moving blade, cooling air enters cooling passages to flow th

A gas turbine moving blade is provided which prevents occurrence of cracks caused by thermal stresses due to temperature differences between a blade and a platform while the gas turbine is being stopped. During steady operation time of the moving blade, cooling air enters cooling passages to flow through other cooling passages for cooling the blade, and then to flow out of the blade. A recessed portion having a smooth curved surface is provided in the platform near a blade fitting portion on the blade trailing edge side. A fillet of the blade fitting portion on the blade trailing edge side has a curved surface with curvature larger than that of a conventional blade fitting portion. A hub slot below the fillet, for blowing air, has a cross sectional area larger than other slots of the blade trailing edge. A thermal barrier coating is applied to the blade surface. By the above construction, thermal stresses due to temperature differences between the blade and the platform during gas turbine stoppage are made smaller and occurrence of cracks is prevented.

대표청구항 ▼

1. A gas turbine moving blade comprising:a platform including an interior platform cooling passage; a blade fitted to said platform at a blade fitting portion of said blade on a trailing edge side of said blade, said blade including an interior blade cooling passage and also including cooling air bl

1. A gas turbine moving blade comprising:a platform including an interior platform cooling passage; a blade fitted to said platform at a blade fitting portion of said blade on a trailing edge side of said blade, said blade including an interior blade cooling passage and also including cooling air blow holes provided in and around said blade, and said blade fitting portion including a fillet exterior with a curved surface; and a recessed portion in an end face portion of a rear side portion of said platform near said blade fitting portion, said recessed portion having a smooth curved surface and extending in an orthogonal direction relative to a turbine axial direction, wherein said cooling air blow holes include holes in a trailing edge of said blade, with one of said holes in the trailing edge of said blade being located in a hub portion of said blade and being a lowermost hole that is positioned beneath each other of said holes in the trailing edge of said blade, said lowermost hole having a cross-sectional area that is larger than that of said each other of said holes in the trailing edge of said blade, such that when said blade is to be cooled, cooling air is flown through said platform cooling passage, through said blade cooling passage, and out of said blade through said cooling air blow holes.