Cover plate retention slot system and method

A cover plate retention method for a gaspath component of a turbine engine, the gaspath component having a hot side configured for exposure to a hot gaspath of the turbine engine and an opposing non-gaspath side, the method comprising:

• forming a cavity having an opening disposed on the non-gaspath side of the gaspath component, the opening having a pair of parallel side walls, a first end wall, and a second end wall;
• forming a top rail disposed at a top of the first end wall and extending therefrom to terminate at a position between 60% and 80% of a length of the top of each of the parallel side walls;
• and
• forming a bottom rail disposed a fixed or specified distance below the top rail on the first end wall and extending therefrom along at least the major portion of each of the parallel side walls to form a cover plate retention slot.

A cover plate retention system for a ceramic matrix composite (CMC) blade outer air seal (BOAS) segment of a turbine engine, the CMC BOAS segment having a hot side configured for exposure to a hot gaspath of the turbine engine and an opposing non-gaspath side, comprising:

• a cavity having a substantially rectangular opening disposed on the non-gaspath side of the CMC BOAS segment, the opening having a pair of parallel side walls, a first end wall, and a second end wall;
• a top rail disposed at a top of the first end wall and extending therefrom to terminate at a position between 60% and 80% of a length of the top of each of the parallel side walls;
• a bottom rail disposed a fixed or specified distance below the top rail on the first end wall and extending therefrom along at least the major portion of each of the parallel side walls to form a cover plate retention slot;
• and
• a substantially rectangular metal cover plate dimensioned to slidably engage the cover plate retention slot.