Abstract: A sealing assembly is provided for sealing against a component. The sealing assembly comprises a seal carrier and a continuous seal element that is attached to the seal carrier at at least two discrete positions of attachment. The seal element is provided with a sealing surface that is arranged to seal against the component. The seal element is further provided with a thermal expansion slot that is located between the discrete positions of attachment and which extends from a first edge of the seal element over a portion of the width of the seal element. This allows the seal carrier and seal element to thermally expand in the length direction at different rates.

Abstract: A fastener (2) comprising an elongate core (4) and made of titanium or titanium alloy, and a sleeve (6) made of a different material and having an external thread (26), the core (4) being disposed within the sleeve (6) and fixed with respect to the sleeve (6).

Abstract: A vane fixing apparatus for removably fixing a vane plate (14) to a web (12) is described. The vane fixing apparatus comprises a mounting bracket (16) attached to the vane plate (14), and a mounting block (20,30) held on the web (12) by at least one fastener (18), wherein the mounting block (20,30) is moveable between a first configuration in which the mounting bracket (16) may engage and disengage the mounting block (20,30) and a second configuration in which the mounting block (20,30) securely retains the mounting bracket (16) relative to the web (12), and wherein the mounting block (20,30) is moveable between the first and second configurations by operation of the fastener (18).

Abstract: A gas turbine engine transition duct 34 is used to convey exhaust gas and bypass air away from the engine, towards an exhaust nozzle (not shown). The duct 34 defines the outer extremity of the path for gas and/or air through the duct. The duct comprises a plurality of flat panel members 36 which together define the outer extremity of the path.

Abstract: A fastener (2) comprising an elongate core (4) and made of titanium or titanium alloy, and a sleeve (6) made of a different material and having an external thread (26), the core (4) being disposed within the sleeve (6) and fixed with respect to the sleeve (6).

Abstract: A sealing assembly is provided for sealing against a component. The sealing assembly comprises a seal carrier and a continuous seal element that is attached to the seal carrier at at least two discrete positions of attachment. The seal element is provided with a sealing surface that is arranged to seal against the component. The seal element is further provided with a thermal expansion slot that is located between the discrete positions of attachment and which extends from a first edge of the seal element over a portion of the width of the seal element. This allows the seal carrier and seal element to thermally expand in the length direction at different rates.

Abstract: A vane for use in a duct, such as an exhaust duct in a gas turbine engine, comprises a shear web arranged to extend substantially across the duct and to be fixedly attached to at least one wall thereof, and one or more vane plates removably mountable on the web. On each side of the web three retaining plates are secured to the web by bolts 18. A plurality of mounting brackets, are permanently fixed to the vane plates by riveting with countersunk-head rivets. Mounting brackets have tangs which are arranged for slidable engagement with the retaining plates in a direction opposite to arrow A. Thus, the vane plates may be slid along the web from a trailing edge of the vane to a leading edge, and back. Once the vane plates are in the required position on the web they may be secured against further sliding movement by a pair of limiting brackets, one on each side of the web.

Abstract: A vane fixing apparatus for removably fixing a vane plate (14) to a web (12) is described. The vane fixing apparatus comprises a mounting bracket (16) attached to the vane plate (14), and a mounting block (20,30) held on the web (12) by at least one fastener (18), wherein the mounting block (20,30) is moveable between a first configuration in which the mounting bracket (16) may engage and disengage the mounting block (20,30) and a second configuration in which the mounting block (20,30) securely retains the mounting bracket (16) relative to the web (12), and wherein the mounting block (20,30) is moveable between the first and second configurations by operation of the fastener (18).

Abstract: A hose assembly comprising a flexible hose and at least one co-extending flexible member. The hose and the member are secured together for tandem movement by means of at least one intermediate resilient mounting means. In operation tension and/or compression induced in the hose assembly by relative motion of the hose and co-extending flexible member is reduced by the compression and/or expansion of the at least one resilient mounting means.

Abstract: A longitudinal seal in the form of a strip member for sealing a gap between adjacent jet pipe liner panels, for example. The liner panels are individually suspended from the internal wall of the jet pipe by separate supports with narrow clearance gaps between neighbouring panels which have to be sealed. A seal has to be provided between adjacent panels which is capable of accommodating relative movements and misalignments between adjacent structures. The seal disclosed essentially comprises a long strip of a metal alloy folded lengthwise several times to form a compliant section in the form of a box pleat between two edge portions which may be engaged in lengthwise slots on the two supporting structures facing each other.

Abstract: A joint seal for articulated joints between contra-rotating sections of a gas turbine engine exhaust duct. The illustrated embodiment comprises a plurality of contra-rotatable exhaust duct sections leading to a vectorable final nozzle. The joint seal is located internally of a bearing around its inner circumference. An exhaust section may have an internal wall spaced internally from the outer wall, thus forming an annular space for conducting relatively cool air surrounding the hot gas stream. The joint seals preferably are located between adjacent ends of these inner walls.

Abstract: A jet pipe liner for a gas turbine engine comprises of an inner skin consisting of a multiplicity of longitudinally extending sections arranged edge-to-edge in a circumferential direction and suspended along their edges by a multiplicity of longitudinally extending A-frame members. The supporting members are attached to the inside of the jet pipe and the inner skin sections are clamped along their long edges by double-skinned distal ends of the links of the A-frame members.

Abstract: A ceramic shroud ring is located within a gas turbine engine in abutment with the inner surface of the metal engine case. The ring is characterized in that it is divided by a split extending between the radially inner and outer surfaces. The natural resilience of the ring is such that it tends to open out when unconstrained, the ring thereby following the contour of the engine case as its diameter changes according to temperature. The engine case is provided with a pair of circumferential flanges directed inwardly and abutting respectively against high pressure upstream and low pressure downstream portions of the ring to define an annular cavity about the ring, and the ring is provided on its downstream face with at least one radial slot giving low pressure air access to the annular cavity. Within the thickness of the ring a slot extends from the upstream face to the downstream face and intersects the split in the ring. A seal strip occupies the slot.

Abstract: In a gas turbine engine having a ceramic nozzle guide vane and a metal engine casing, a nozzle guide vane mounting comprises on the radially outermost end of the vane a circumferential flange extending at right angles to the long axis of the vane, a first spring means for applying a radially inward force to the radially outer surface of the flange, a second spring means for applying a radially outward force to the radially inner surface of the flange, and structural members of the engine casing to nip the first and second spring means between the structural members and the flange. The spring means may be C-ring seals made of a resilient material.

Abstract: In a gas turbine engine having a ceramic nozzle guide vane supported by a metal turbine casing the radially outer end of the vane is provided with opposed frustoconical sections which converge towards each other onto a middle cylindrical section. A metal split ring surrounds the cylindrical section, and the radially inner and outer ends of the ring abut the frustoconical sections. The split ring is provided with a flange which cooperates with a groove structure on the turbine casing, thus enclosing the split ring to the casing. A bolt means fastens together two sections of the casing either side of the vane, thereby holding the split ring against the vane. On increase in temperature the split ring expands more than does the vane. The ends of the split ring therefore slide against the frustoconical surfaces of the vane to take up the expansion, and in so doing maintain contact with the vane.