Abstract: The present invention provides a gas turbine engine comprising a tubular containment casing surrounding a rotary fan blade assembly. The radially outer perimeter (and optionally the radially inner perimeter) of the radial cross-sectional profile of the containment casing is non-circular e.g. polygonal, corrugated, fluted or wavy.

Abstract: A fan casing assembly comprising an annular casing member for circumferentially surrounding a fan, and an annular fan track liner comprising a plurality of circumferentially adjacent liner panels. The annular fan track liner is positioned radially inward of the annular casing member. A tilting arrangement is provided and configured to selectively circumferentially tilt one or more of the liner panels, such that, in the event of a fan blade being released from a fan, the tilting arrangement can initiate tilting of one or more liner panels so that the liner panels can trim one or more of the remaining fan blades.

Abstract: A gas turbine engine comprising a stator, wherein the stator comprises laminated oscillating heat pipes.

Abstract: A fan casing assembly comprising an annular casing member for circumferentially surrounding a fan, and an annular fan track liner comprising a plurality of circumferentially adjacent liner panels. The annular fan track liner is positioned radially inward of the annular casing member. A tilting arrangement is provided and configured to selectively circumferentially tilt one or more of the liner panels, such that, in the event of a fan blade being released from a fan, the tilting arrangement can initiate tilting of one or more liner panels so that the liner panels can trim one or more of the remaining fan blades.

Abstract: This invention relates to a stator aerofoil for a gas turbine engine, comprising: a body portion; at least one panel which forms at least part of one of either the pressure or section surface of the aerofoil; at least one internal chamber which is bounded by the body portion and panel; and, at least one elastomeric component within the at least one internal chamber, wherein the elastomeric component at least partially defines a cell within the internal chamber, wherein the cell is in fluid communication with the exterior of the aerofoil.

Abstract: An injection-molded thermoplastic mini-platform is adhesively bonded, in use, to the aerofoil surfaces of a fan blade in a gas turbine engine. The mini-platform is divided into a number of leaves, to increase its flexibility, and ribs beneath the leaves provide additional stiffness in the radial direction. In the event that a fan blade is released in operation, the mini-platform is designed to detach from the blade and/or to break apart, so that damage to other components of the engine is minimized.

Abstract: A securing arrangement 32 for securing an actuating lever 20 to a spindle 14, for example a spindle 14 of a variable inlet guide vane 10 in a gas turbine engine, comprises a fastening formation 38 rotatably co-operable, in use, with a corresponding fastening formation 30 on the spindle 14. The securing arrangement 32 is rotatable relative to the spindle 14 to a securing position in which the respective fastening formations 30, 38 co-operate so that the securing arrangement 32 secures the actuating lever 20 to the spindle 14. The securing arrangement 32 includes anti-rotation means 42, preferably in the form of anti-rotation tabs 44, for preventing rotation of the securing arrangement 32 from the securing position.

Abstract: A guide vane arrangement 20 for a gas turbine engine (10, FIG. 1) includes a vane member 21 extending between inner and outer platforms 22, 24 which are respectively mounted on inner and outer mounting members 42, 34. One of the inner and outer platforms 22, 24 includes a resilient that abuts the respective inner or outer platform 22, 24 to permit relative movement between the inner or outer platform 22, 24 and the respective inner or outer mounting member 42, 34.

Abstract: An axial flow compressor (16) comprises a plurality of variable stator vanes (32) circumferentially spaced apart and extending radially. Each variable stator vane (32) is rotatably mounted on a compressor casing (28). A control ring (38) surrounds the compressor casing (28). Each variable stator vane (32) is connected to the control ring (38) by a respective one of a plurality of operating levers (40) and the control ring (38) is spaced from the compressor casing (28) by a clearance. A plurality of bimetallic strips (50) are arranged circumferentially and are positioned radially between the control ring (38) and the compressor casing (28) and the bimetallic strips (50) control the clearance between the control ring (38) and the compressor casing (28) whereby any error of the variable stator vane (32) angular position is reduced. Each bimetallic strip (50) extends radially outwardly from the compressor casing (28) towards the control ring (38).

Abstract: A vane arrangement for a compressor of a gas turbine engine comprises a plurality of circumferentially arranged vanes, a plurality of levers and a control ring. Each vane comprises a fixed upstream portion secured to a casing and a movable downstream portion pivotally mounted to the casing. The movable portion of each vane is pivotally mounted at the upstream end of the movable portion adjacent the fixed portion of the respective vane. The movable portion of each vane has a spindle extending through an aperture in the casing. Each aperture in the casing has an elongate shape in cross-section and each aperture has a bush arranged within the aperture and around the spindle to fill the elongate shaped aperture. The downstream end of the fixed portion of each vane has substantially the same shape as the upstream end of the movable portion of the respective vane.

Abstract: A seal (30) is provided for reducing the gap between alternate wall members (20) and adjacent blades (14) that are arranged circumferentially in a rotor (12). The seal (30) has a flange portion (36), which is inclined radially inward. The flange portion (36) of the seal (30) is in the form of rubber bellows (32) which have a cavity (34) therein. In operation the flange portion (36) of the seal (30) is deflected radially outwards by centrifugal forces acting thereon. The seal (30) is open at one end to allow air compressed by the rotor (12) to pass into the cavity (34) and inflate the seal (30). Inflation of the seal (30) ensures that the gap between the edge (26) of the wall member (20) and the blade (14) is filled. A good seal is thus maintained throughout operation of the rotor (12) and prevents the air in void (28) passing into the blade passage.