Patent ID: 9399922
Filing Date: 2016-07-26
CPC Classification: F01D,F02K,F04D,F05D,Y02T,Y10T

Claim Text:
1. A gas turbine engine rotor assembly comprising: a disk having a disk rim, a plurality of dovetail slots, and a plurality of disk posts, each disk post having at least one disk post hook, wherein the disk posts are circumferentially disposed around the rim and the dovetail slots are disposed circumferentially between disk posts; a plurality of fan blades having dovetail roots disposed in the dovetail slots, a plurality of fan platforms, each of the fan platforms having a forward portion having a forward interface surface facing axially forward, an aft portion having an aft interface surface facing radially outward, and a transition portion having at least one mounting feature, the mounting feature having at least one engagement tang, wherein the transition portion is connectively disposed between the forward portion and aft portion, wherein the fan platforms are circumferentially disposed between the fan blades; and a plurality of captured clips, each captured clip having an engagement end, wherein each of the captured clips are circumferentially disposed between the fan blades and radially disposed between the disk and the fan platform, whereby the engagement end couples the engagement tangs to the disk post hooks.