| 摘要 |
The invented cooling and feather seal arrangement of a gas turbine engine (10) having an axial gas flow (12) therethrough comprises a plurality of circumferentially adjacent segments (18), each segment (18) has a first surface (24) being in contact with hot gas flow (12) and an opposite surface (26) being in contact with a supply of cool air (28). Each segment (18) has two side surfaces wherein each side surface (30) abuts a side surface (30) of an adjacent segment (18) leaving a gap (20) between abutting segments (18). Each side surface (30) is provided with a slot (22) complementary to the slot (22) in the side surface (30) of the adjacent segment (18) and each said slot (22) has a hot side surface (36) and a cold side surface (38). A feather seal (34) fits into said slots (22) between adjacent segments (18). A plurality of hot grooves (40) is performed in each hot side surface (26) of said slots (22). Each hot groove (40) is in fluid contact with said supply of cool air (28) and has an opening into said gap (20) which is staggered with respect to hot groove (40) openings in adjacent segments (18) so that, in use, each hot groove (40) discharges cooling air into said gap (20) at a location that is staggered with respect to the air that is discharged from hot grooves (40) in the adjacent segment (18). |
