Abstract: The present invention provides a casing assembly for a gas turbine engine comprising a radially inner casing and a radially outer casing. The assembly further comprises an axial mounting arrangement for mounting the inner casing and outer casing in a fixed axial relationship. The axial mounting arrangement allows radial movement of the outer casing relative to the inner casing such that distortion of the inner casing as a result of engine carcass loads on the outer casing is obviated as the inner casing is radially isolated from the outer casing.

Abstract: The present invention provides a casing assembly for a gas turbine engine comprising a radially inner casing and a radially outer casing. The assembly further comprises an axial mounting arrangement for mounting the inner casing and outer casing in a fixed axial relationship. The axial mounting arrangement allows radial movement of the outer casing relative to the inner casing such that distortion of the inner casing as a result of engine carcass loads on the outer casing is obviated as the inner casing is radially isolated from the outer casing.

Abstract: A sealing ring for controlling gas leakage through the annular space between two rotating concentric members; for example engine shafts. The sealing ring 20 has a generally trapezoidal cross section and an overlapping scarf joint. The sealing ring improves sealing by providing continuous lines of contact at edges between inner and outer coaxial shaft members.

Abstract: Conventionally gas turbine engine compressors have fixed inlet guide vanes to give a predetermined swirl to incoming air at an engine design speed, so that air enters the compressor at an optimum angle. At speeds much lower, for example, than the design speed the guide vane is less efficient. The guide vanes are thereby made variable in camber. Each vane comprises a number of spanwise hinged members which can be moved relative one to another to vary the vane camber.