System and method for sealing a gas path in a turbine

A seal 10 for placement in a slot 18 between two turbine components 20 of a gas turbine 110 to seal a gap 19 between the components may include a sealing element 14 sized so as to be capable of placement within the slot 18 and of substantially sealing the gap 19 during operation of the gas turbine 110. A sacrificial coating 16 may be located on the sealing element 14. The sacrificial coating 16 may be configured with a size substantially conforming to a size of the slot 18, the sacrificial coating 16 including a material that is removable from the sealing element 14 via heating to a temperature achieved during operation of the gas turbine 110. Related gas turbine assemblies and methods of assembly are also disclosed.