Gas turbine with honeycomb seal
View Patent ↗A gas turbine includes a compressor, a combustor, and a turbine. The turbine includes a honeycomb seal disposed so as to be secured to a casing side in a clearance between the casing and turbine blades rotating around a rotating shaft and a seal fin that is provided on an end face of each of the turbine blades facing the honeycomb seal. The seal fin extends in a direction perpendicular to the rotating shaft. The honeycomb seal is formed by a plurality of corrugated sheet metals overlapped with each other at walls of nodes thereof and the walls of the nodes are blazed with each other. Each of the corrugated sheet metals has trapezoids formed in alternating fashion. A longer direction of each wall of the nodes of the honeycomb seal is angled with respect to the rotational direction of the turbine blades.
1. A gas turbine comprising:
a compressor,
a combustor, and
a turbine which includes
a honeycomb seal disposed so as to be secured to a casing side in a clearance between a casing and a turbine blade rotating around a rotating shaft extending in a longitudinal direction of the casing, and
a seal fin provided on an end face of the turbine blade facing the honeycomb seal, the seal fin extending in a direction perpendicular to the rotating shaft, wherein
the honeycomb seal is formed by a plurality of corrugated sheet metals overlapped with each other, the honeycomb seal having nodes of walls where the corrugated sheet metals overlap with each other, the walls of the nodes being brazed with each other, each of the corrugated sheet metals having a trapezoid alternately continued,
a longer direction of each wall of the nodes of the honeycomb seal is angled with respect to a rotational direction of the turbine blade,
each wall of the nodes is tilted at a tilt angle in the rotational direction of the turbine blade with respect to a vertical axis perpendicular to the rotating shaft such that an inner peripheral end of the wall is positioned behind of an outer peripheral end of the wall in the rotational direction, and
the tilt angle is within a range of 15 to 45 degrees.
2. The gas turbine according to claim 1 , wherein the longer direction of each wall of the nodes of the honeycomb seal is angled with respect to the rotational direction of the turbine blade in a range from 30 to 90 degrees.
3. The gas turbine according to claim 2 , wherein the longer direction of each wall of the nodes of the honeycomb seal is angled with respect to the rotational direction of the turbine blade at 90 degrees.
4. The gas turbine according to claim 1 , wherein the seal fin has a thickened portion formed by overlaying an abrasion-resistant alloy or ceramics.
5. The gas turbine according to claim 1 , wherein an abrasion-resistant alloy or ceramics is coated on a surface of the seal fin.