| 摘要 |
A gas turbine engine composite disk (12) includes dovetail slots (14) between disk posts (16) extending radially inwardly from a periphery (15), a hub ring (20) of composite plies (24) circumscribed about a centerline axis (8), and radial plies (43) extending radially away from hub ring (20) into disk posts (16). A segmented intermediate ring (30) concentric with and located radially outwardly of hub ring (20) includes intermediate ring segments (36) having nested plies (37) with annular bases (38) circumscribed about centerline axis (8) and substantially radially extending clockwise and counter-clockwise radial ply arms (40, 42). An outer segmented ring (90) may be concentric with and located radially outwardly of intermediate ring (30), include annular outer ring segments (92) with circumferentially stacked composite plies (96) disposed within intermediate ring segments (36) between clockwise and counter-clockwise radial ply arms (40, 42) and radially outwardly of annular bases (38). An outer skin (101) of outermost composite covering plies (98) may extend circumferentially around composite disk (12). Circumferential and radial composite plies (110, 116) may include circumferentially and radially oriented fibers (112, 118). |
