| 摘要 |
A gas turbine engine blade includes a dovetail 20 having retention lobes 24 and fillets 32. Compression means 40 are provided in the dovetail for introducing compressive prestresses at the fillets for reducing tensile stresses at the fillets due to loads in the blade such as centrifugal tension loads. The compression means may comprise a cavity 46 in the dovetail and an insert 48 disposed therein in an interference fit for generating compressive stresses at the cavity and at the fillets. The cavity may be in the form of a rectangular or trapezoid a channel in the base 30 of the dovetail or a cylindrical cavity, with corresponding inserts to match. In the case of a double-lobed dovetail (figure 6) two cavities with respective inserts may be provided. An asymmetric arrangement is also disclosed (Figure 7). <IMAGE>
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