Fan including a platform and a locking bolt

A fan for a gas turbine engine comprising:

• a fan disc having an upstream face, a radial face configured to receive a series of fan blades and a yoke extending radially from the radial face,
• an inter-blade platform, said platform comprising:
• a base having a first surface configured to delimit a flow path in the fan and a second surface opposite to the first surface, and
• a tab extending radially with respect to an axis of revolution of the fan disc, the tab being adjacent to the second surface, and
• a lock having a downstream edge extending radially with respect to the axis of revolution of the fan disc, the downstream edge of the lock configured to bear against the tab of the platform,
• wherein one of the downstream edge of the lock and an upstream face of the yoke comprises a pin, a first orifice being formed in the other one among the downstream edge of the lock and the upstream face of the yoke of the fan disc,
• wherein a second orifice is formed in the tab,
• wherein the pin is configured to enter the first orifice and the second orifice so as to block motion of the inter-blade platform with respect to the fan disc,
• wherein the base of the inter-blade platform has an upstream end in which a through passage is formed, and
• wherein the lock comprises an upstream edge configured to enter the through passage when the downstream edge of the lock bears against the tab.