| 摘要 |
PROBLEM TO BE SOLVED: To reduce axial stress on a high pressure turbine disk hub. SOLUTION: A first stage turbine disk section 14 for a gas turbine engine, including a centrally disposed disk hub 21 having an integrally-formed, radially outwardly extending web 18 terminating at an outer end. The disk hub 21 has a convex, curved hub surface 22 exposed to high pressure, high temperature compressor bleed and discharge gases during engine operation, and the convex, curved hub surface 22 acts to reduce the axial constraint at the location of peak axial stress, thereby mitigating the formation of undesirable axial stress in the disk hub 21 and allows separation of the peak axial and hoop stresses, thereby reducing the magnitude of the peak hub surface effective stress. COPYRIGHT: (C)2007,JPO&INPIT
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