Abstract: There is disclosed a seal assembly (32) for a machine such as a gas turbine engine. The seal assembly has a support structure (38) to which a resiliently deformable seal member (34) is mounted. A seal land (40) is opposingly spaced from the support structure (38) to define a gap therebetween, wherein the height of the seal member (34) in an undeformed condition is greater than the height (36) of the gap such that the seal member is deformingly pressed against the seal land (40) by the support structure to seal the gap therebetween in use. The support structure (38) and/or seal land (40) comprise an actuable member (40; 44; 46), said member being actuable in a direction towards the other of the support structure and seal land to improve the resistance of the seal assembly (32) to an adverse condition in use, such as a fire.

Abstract: There is disclosed a seal assembly (32) for a machine such as a gas turbine engine. The seal assembly has a support structure (38) to which a resiliently deformable seal member (34) is mounted. A seal land (40) is opposingly spaced from the support structure (38) to define a gap therebetween, wherein the height of the seal member (34) in an undeformed condition is greater than the height (36) of the gap such that the seal member is deformingly pressed against the seal land (40) by the support structure to seal the gap therebetween in use. The support structure (38) and/or seal land (40) comprise an actuable member (40; 44; 46), said member being actuable in a direction towards the other of the support structure and seal land to improve the resistance of the seal assembly (32) to an adverse condition in use, such as a fire.

Abstract: A gas turbine engine 10 is suspended via a casing 15 from a pylon 12 by a front mount 20 and a rear mount 40. The front mount 20 comprises a bracket 22, having a plurality of pins 26,28 and 30 integral therewith, which is bolted to the underside 11 of the pylon 12. The first pin 26 engages an annular flange 16 around the casing 15 to support the engine 10 in a vertical plane. Any vertical loads act peripherally of the casing 15 through the annular flange 16 to minimise the distortion of the casing 15. The second pin 28 engages with the casing 15 directly to prevent axial and lateral movement of the engine 10 relative to the pylon 12. The third pin 30 is provided as a failsafe. In normal operation the third pin 30 carries no load, however if the first pin 26 should break the third pin 30 then supports the engine 10 in a vertical plane. Any vertical loads then act peripherally of the engine casing 15 through an annular flange 18.

Abstract: When a breakage occurs to the connecting links which connect a gas turbine engine to aircraft structure, the engine drops onto a fail/safe mounting. The drop is minimal in magnitude and the invention provides a visual means for appreciating that the drop and therefore the breakage, has occurred. Relative movement between engine and airframe frees a pop up member and enables it to project beyond the engine envelope, for observation by inspection.