PURPOSE: To enhance heat resistant fatigue property of a shroud and thermal efficiency of a gas turbine by oppositely arranging shrouds with a fine clearance at the tip of a turbine blade, and specifying thickness of the shroud and composition of a heat resistant cast alloy being a material thereof respectively.
CONSTITUTION: A plurality of turbine disks 4 are connected to a turbine stub shaft 11, and shrouds 1 are arranged opposite to each other at a tip of a turbine blade 3 embedded in the turbine disk 4. A plurality of compressor disks 6 are connected to a turbine distant piece 20 connected to the turbine disk 4, and a compressor blade 7 is embedded in the compressor disk 6. The shroud 1 is determined 40mm or more in thickness, and formed of a heat resistant cast alloy composed of C 0.15-0.35%, Si 0.2-2%, Mn 0.4=1.5%, Cr 20-35%, Ni 20-40% and Fe the remainder in weight.
KASHIMURA TETSUO
FUKUI HIROSHI
KUNIHIRO MASATSUGU
TORITANI HAJIME
| JPS6017821A | 1985-01-29 | |||
| JPH02298605A | 1990-12-11 | |||
| JPS6153423A | 1986-03-17 |