Bearing anti-rotation and retention system for a gas turbine engine

A gas turbine engine, comprising:

• a stationary support structure;
• a shaft that rotates within the stationary support structure;
• a bearing between the shaft and the stationary support structure;
• wherein:
• the shaft has a shaft outer surface and a shaft inner surface, and the shaft axially extends from a shaft forward end to a shaft aft end, and the shaft forward end defines axially extending shaft slots that are circumferentially spaced apart from each other;
• and
• the bearing has a first race is ring shaped with a first race outer surface and a first race inner surface, wherein the first race is sized so the first race inner surface fits around the shaft outer surface, and wherein the first race extends axially from a first race forward end to a first race aft end, and
• wherein the first race forward end defines radially inwardly extending bosses that are circumferentially spaced apart from each other and aligned with ones of the axially extending slots of the shaft forward end, whereby the first race is rotationally fixed against the shaft.

A method of arranging an assembly of a gas turbine engine, comprising:

• positioning a first race inner surface of a first race of a bearing against a shaft outer surface of a shaft;
• aligning radially inwardly extending bosses at a first race forward end of the first race, that are circumferentially spaced apart from each other, with ones of axially extending shaft slots at a shaft forward end of the shaft that are circumferentially spaced apart from each other;
• and
• axially moving the first race aft against the shaft until each of the bosses is disposed against a slot aft end of ones of the shaft slots.