Abstract: It is known with regard to particularly cavities below high pressure turbine discs that mixing of hot gas leakage flows through an inner seal with cooling flows can diminish the effectiveness of that cooling flow when presented to other parts for cooling. By providing a path within a wall which is particularly shaped in portions it is possible to provide entrainment of a hot leakage gas flow away from entry into the cavity. Thus, the cooling flow retains a higher cooling effect and maintains its swirling nature in comparison with prior arrangements where mixing with the hot leakage flow occurred.

Abstract: A rotor assembly for a gas turbine engine, the rotor assembly comprises at least two rotors defining a cavity therebetween. A first rotor defines a cooling air inlet in its radially inward portion. A second rotor defines a cooling air outlet in its radially outward portion, such that the cooling air passes radially outwardly through the cavity.

Abstract: Flow restrictors (4), (14) are widely utilised with regard to providing flow control in such situations as with respect to sealing and pressurisation of bearing chambers in gas turbine engines. The restrictor (4), (14) restricts a flow (5), (15) but with prior arrangements may be susceptible to deposition upon flank surfaces of the restrictor (4). These depositions may fragment and block an aperture (7), (17) of the restrictor (4), (14) reducing operational effectiveness. By provision of a deflector (18) having a deflector surface (19) flows (15) can be presented such that a greater proportion of the flow including droplets or other matter which may result in surface deposition or errosion will pass directly through an aperture (7, 17) rather than impinge upon the flank surfaces of the restrictor (14). Furthermore, the deflector (18) is dimensioned such that surfaces which may be susceptible to deposition have dimensions smaller than the aperture (17).

Abstract: A gas turbine engine comprising a rotor and a stator which define first, second and third cavities; the rotor and stator define a seal therebetween and which is located for sealing between the second and third cavities, the rotor comprises an aperture through which a gas flow passes from the first cavity to the second cavity characterized in that the seal comprises a deflector that extends axially over at least a portion of the aperture to deflect at least a part of the gas towards the rotor.

Abstract: It is known with regard to particularly cavities below high pressure turbine discs that mixing of hot gas leakage flows through an inner seal with cooling flows can diminish the effectiveness of that cooling flow when presented to other parts for cooling. By providing a path within a wall which is particularly shaped in portions it is possible to provide entrainment of a hot leakage gas flow away from entry into the cavity. Thus, the cooling flow retains a higher cooling effect and maintains its swirling nature in comparison with prior arrangements where mixing with the hot leakage flow occurred.

Abstract: A rotor assembly for a gas turbine engine, the rotor assembly comprises at least two rotors defining a cavity therebetween. A first rotor defines a cooling air inlet in its radially inward portion. A second rotor defines a cooling air outlet in its radially outward portion, such that the cooling air passes radially outwardly through the cavity.

Abstract: A cooling arrangement comprises a support (20) for a plurality of blades (22). The support (20) comprises a plurality of blade mounting members (28) provided between adjacent blades (22). The blades (22) are mounted upon the blade mounting members (28). The cooling arrangement defines a pathway (36) for a cooling fluid. The cooling arrangement further includes a fluid directing formation (40, 44, 44A) to direct the cooling fluid across the blade mounting member (28).

Abstract: A cooling arrangement comprises a support (20) for a plurality of blades (22). The support (20) comprises a plurality of blade mounting members (28) provided between adjacent blades (22). The blades (22) are mounted upon the blade mounting members (28). The cooling arrangement defines a pathway (36) for a cooling fluid. The cooling arrangement further includes a fluid directing formation (40, 44, 44A) to direct the cooling fluid across the blade mounting member (28).

Abstract: A Lower Leg Walker for the treatment of ankle fractures and a variety of other injuries to the foot and ankle, has a foot platform base comprising a rigid chassis of more or less parallelepiped shape. The chassis is substantially a plurality of ribs disposed at right angles, forming a grid and is over-moulded with resilient materials forming a shoe shape. The foot platform base supports and accommodates the human foot and has a distinctive, low, double rocker profile on its underside. The lower leg walker is provided with attachment hinges for securing a pair of upright side-members to the foot platform base and these are covered with hook and loop attachment material which releasably secures them to a wrap which is lined with terry material and encloses the foot, ankle and lower leg. The device is secured to the patient with a series of straps.