| 摘要 |
A retainer device 20 for locking a blade 26, preferably a compressor blade, into a rotor disc 28 of a gas turbine engine (10, fig 1) locatable in the cavity 22 formed therebetween. The retainer includes a first end 30, having a retaining feature 32, which may lock a retaining ring 33 in place, wherein the retaining feature 32 may be bent from a co-planar formation to enclose the ring 33. At the second end 34 there includes means 36 for sealing the end of the cavity 22, so as to reduce axial leakage of working fluid between stages. The sealing means 36 may comprise a lip feature 44, which may be deformable. A plurality of devices 20 (and 120, fig 5) of varying masses may be used with a plurality of blades in order to improve balance of the overall arrangement.
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