Abstract: An improved runner is disclosed, of the type associated with a boot portion to form an ice skate and defining, in use, a pair of edges, spaced-apart from one another along a lateral axis and, in use, forming the ice-engaging surfaces of the skate. The improvement comprises a pair of metal plates, one or more metal webs and a rigid polymeric portion. The plates are generally parallel to one another and axially spaced apart. Each plate defines a respective one of said edges in use. The webs extend between and rigidly connect the plates to define, with the plates, one or more voids between said plates, said voids including a channel having an opening directed, in use, away from the boot portion, said channel being bounded laterally by said plates. The polymeric portion is disposed in said channel and engages the plates to stiffen the runner.

Abstract: In order to improve cooling of a blade 31, 41/disc 32, 42 combination, a pre-swirler feature 40, 50 is utilised in order to present coolant air through presentational pathways typically incorporating holes 37 or grooves/slots such that coolant air displaces hotter air leaked past a seal 35, 45. The swirler features 40, 50 are located within stationary housing components 34, 44 such that the coolant air is propelled at substantially the same rotational speed as the disc 32, 42 whilst presentation of the coolant air flow A, C, E is such that hot air displacement is achieved at least adjacent front faces 36, 46 of blade roots 33, 43.

Abstract: A seal system comprises a rotor and a stator. First and second cavities are defined between the rotor and the stator. A plurality of seals for inhibiting a flow of gas through the cavities are provided. Relative motion between the rotor and the stator can cause a flow of gas through the cavities via the seals. The seals are arranged such that an increase in pressure in one of the first and second cavities is offset by a decrease in pressure in the other of the first and second cavities.

Abstract: A seal arrangement 32 between a turbine shroud seal segments 38,40 in a gas turbine engine. The arrangement 32 comprises facing slots 34, 36 provided respectively in the segments 38,40 with offset spaces 42, 44 provided between the segments 38,40. A strip 46 is cemented into the slot 36 such that the flow path 50 passes through the space 42, around the free end of the strip 46, and out through the offset space 44, thereby providing a longer flow path.

Abstract: A mounting arrangement 31 incorporates a blade pocket cavity 35, 135, 235 between a blade platform 34, 134, 234 and a rotor disc post 53. Coolant air is presented within the cavity 35, 135, 235 in order to provide cooling of the platform 34, 134, 234. In order to inhibit ingress of hot air from adjacent wheel spaces 36, an air curtain is created across an open end 45, 145 whereby coolant air is contained within the cavity 35, 135, 235. Air flow from the air curtain itself may pass along a surface 48, 148 to provide more direct cooling for the platform 34, 134, 234. Apertures 49, 50 may be provided in order to bleed coolant air from the cavity 35 and also draw an air flow 51 across the surface 48 for greater cooling efficiency.

Abstract: Seal arrangements are arranged to provide a seal edge suspended on suspension mountings to accommodate for axial movements in a component against which the edge acts. The edge is associated with a backing member so that the edge extended to a desired degree beyond the backing member to provide a good sealing function by suspending the edge it is allowed to float and so does not become excessively worn due to axial movements or excursions by the component 6, 36, 46, 56 whilst retaining the seal edge 4, 34, 44, 54 at an appropriate position for sealing efficiency. Typically, the seal edge is formed from bristles of a brush seal. A number of seal arrangements 1, 31, 41, 51 are normally arranged in a seal assembly 63.