| CPC F01D 11/008 (2013.01) [F01D 5/3007 (2013.01); F01D 11/006 (2013.01); F01D 5/22 (2013.01); F05D 2220/323 (2013.01); F05D 2240/55 (2013.01); F05D 2240/80 (2013.01)] | 20 Claims |
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1. A rotor assembly for an aircraft engine, comprising:
blades circumferentially distributed about a central axis, the blades having airfoils and roots protruding from opposite sides of platform segments;
a rotor disc having a peripheral face and slots extending radially inward from the peripheral face toward the central axis, the peripheral face extending from an upstream axial face of the rotor disc to a downstream axial face of the rotor disc, the roots of the blades being received within the slots along a blade insertion direction extending between the upstream axial face and the downstream axial face, the peripheral face defining recesses proximate the downstream axial face, a recess of the recesses located between two adjacent ones of the slots, the recess bounded by a step, the recess located axially between the step and one of the upstream axial face and the downstream axial face relative to the central axis;
feather seals located radially between the peripheral face of the rotor disc and the platform segments of the blades, a feather seal of the feather seals having a core axially extending from a trailing end proximate one of the upstream axial face and the downstream axial face to a leading end proximate the other of the upstream axial face and the downstream axial face along the blade insertion direction, the core circumferentially overlapping a gap defined between two adjacent ones of the platform segments and tabs protruding from the core, the tabs including:
trailing tabs proximate the trailing end of the core and positioned axially outside the recess; and
leading tabs proximate the leading end of the core, a leading tab of the leading tabs extending from a root at the core to a tip, the leading tab extending radially and circumferentially away from the core relative to the central axis from the root to the tip, the leading tab located within the recess and having:
a radially-inner edge face at the tip, the radially-inner edge face facing the recess and facing a radially inward direction towards the central axis;
a lateral edge face extending in a direction having a radial component relative to the central axis from the core towards the tip, the lateral edge face facing a direction having an axial component relative to the central axis; and
a fillet at an intersection between the radially-inner edge face and the lateral edge face of the leading tab, the fillet at least partially received inside the recess, the fillet facing the step and configured to abut the step during a movement of the leading tab in a blade removal direction opposite the blade insertion direction.
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