Abstract: This invention relates to sealing rings for use in gas turbines and methods of making them. In one embodiment the method consists in forming a sealing ring for a gas turbine including: (a) forming a ring to the in use dimensions less a coating thickness of the ring; and (b) depositing a coating having a thickness between about 0.125 mm and 0.077 mm. wherein the ring requires no further machining after step (b). Additionally or alternatively a shot peened sealing surface may be used.
Abstract: A Brush Seal element 10 has a backing plate 11 designed to project into a gap 12 between a fixed sleeve 13 and a shaft 14 and a bristle array 15 comprising a pack of bristle layers which is held in the sleeve 13 by support 16. The bristle 15 and non-linear portion 17, 18, which define cavities 19 and 20 between the array 15 and the plate 10. These cavities can become filled with high pressure fluid so that there is a substantial pressure balance across the array 15.
Abstract: A Brush Seal element 10 has a backing plate 11 designed to project into a gap 12 between a fixed sleeve 13 and a shaft 14 and a bristle array 15 comprising a pack of bristle layers which is held in the sleeve 13 by support 16. The bristle 15 and non-linear portion 17, 18, which define cavities 19 and 20 between the array 15 and the plate 10. These cavities can become filled with high pressure fluid so that there is a substantial pressure balance across the array 15.