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US 6,638,008 B2Granted
Gas turbine engine blade containment assembly
AssigneeROLLS-ROYCE plc
InventorsSivasubramaniam K Sathianathan, Stephen J Booth
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AssigneeROLLS-ROYCE plc
InventorsSivasubramaniam K Sathianathan, Stephen J Booth
Estimating the term…
A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a transition portion (58) and a blade containment portion (54). The upstream portion (56) has a flange (42) connecting the metal casing (40) to a flange (48) on axially adjacent casing (46). The blade containment portion (54) has a greater thickness (T2) than the thickness (T1) of the upstream portion (54). The transition portion (58) connects the blade containment portion (54) and the upstream portion (56) to transmit loads from the blade containment portion (54) to the flange (42) on the upstream portion (56). The ratio of the thickness (T4) of the flange (42) on the upstream portion (56) to the thickness (T1) of the upstream portion (56) is between 3 to 1 and 6 to 1. The flange (42) on the upstream portion (56) is radially scalloped (41) between adjacent fasteners (49,51) and the upstream portion (54) is relatively thin such that the flange (42) and upstream portion (56) are allowed to deform to reduce impact loads transmitted to the flange (48) on the casing (46).
A gas turbine engine rotor blade containment assembly comprising a containment casing, the containment casing having a flange for connecting the containment casing to a flange on an axially adjacent casing, the flange on the containment casing having a plurality of circumferentially spaced regions, the regions being removably connectable to the flange on the axially adjacent casing, the ratio of the thickness of the flange of the containment casing to the thickness of a portion of the containment casing adjacent to the flange is between 3 to 1 and 6 to 1, the flange on the containment casing being radially scalloped between the adjacent regions to allow the flange on the fan containment casing to deform such that loads transmitted to the fasteners and flange of the axially adjacent casing are at least reduced.
A gas turbine engine rotor blade containment assembly comprising a containment casing, the containment casing having a flange for connecting the containment casing to a flange on an axially adjacent casing, the flange on the containment casing having a plurality of circumferentially spaced regions, the regions being removably connectable to the flange on the axially adjacent casing, the flange on the containment casing being radially scalloped between the adjacent regions to allow the flange on the fan containment casing to deform such that loads transmitted to the fasteners and flange of the axially adjacent casing are at least reduced wherein the containment casing has an upstream portion and a blade containment portion, the flange is on the upstream portion of the containment casing and the ratio of the thickness of the flange on the upstream portion of the containment casing to the thickness of the upstream portion of the containment casing is between 3 to 1 and 6 to 1.
Dependencies are inferred from the claim text.