| 摘要 |
A rotating assembly for a turbine engine comprises: a disc 10; axially engaged blades 12 radially extending from the disc having lateral platforms 22 and fir-tree roots 14 (Fig. 1) that engage slots 16 and teeth 18 of the disc; and a downstream shroud 34 which includes an outer sealing lip 38, an inner annular sealing lip 40, and an intermediate sealing lip 48, where in the intermediate annual sealing lip 48 is opposite the downstream faces of the disc teeth 18 and the blade roots and radially located between an outer slot cavity 20a and an inter-blade cavity 26 formed by platforms laterally extending from the blades and being circumferentially arranged end-to-end, forming inter-blade cavities 26. The rotating assembly may furthermore incorporate an upstream shroud, a high pressure turbine, air cooling transfer means and be for a turbine. The assembly is for reducing heating of cooling air around turbines. |
