An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the oil tank in one degree of freedom, a second mount may fix the oil tank in two degrees of freedom, and a third mount may fix the oil tank in three degrees of freedom. This allows limited rotational and expansion movement while coupling the oil tank to the engine. The mount attachments may be embodied in rubber, with pins, or with spherical joints in a variety of configurations. Frangible pins may be used to absorb energy but still retain the oil tank in the event of a high energy event.

An aiming assembly comprising an instrument and aiming device, the aiming device comprises: a frame, a mobile part comprising a plate, the instrument being fixed onto the plate, the mobile part and the instrument having a centre of gravity, the mobile part being rotationally mobile relative to the frame on a first axis of rotation, and comprising a support configured to cooperate with the plate to allow the plate to be rotationally mobile relative to the frame about a second axis of rotation at right angles to the first axis of rotation, and rotationally mobile relative to the frame on the first axis, the first and second axes of rotation intersecting at a point of intersection. The point of intersection coincides with the centre of gravity of the mobile part and of the instrument, and the support comprises a flexible part configured to compensate for the differential expansions on the second axis of rotation between the frame and the plate.

Turbine nozzles are provided for gas turbine engines. The turbine nozzle includes an arcuate inner band; an arcuate outer band; and a nozzle vane disposed between the arcuate inner band and the arcuate outer band. The radially inner end of the nozzle vane is attached to the arcuate inner band through an interlocking transition zone comprising a plurality of projections alternately extending from the radially inner end of the nozzle vane and the arcuate inner band, respectively, to undetachably couple the nozzle vane and the arcuate inner band. Optionally, the radially outer end of each nozzle vane is also attached to the arcuate outer band through an interlocking transition zone.

A gas turbine engine including a fan, a core including at least one rotatable shaft, and a gearbox mechanically coupling at least one rotatable shaft of the core to the fan is provided. The gas turbine engine also includes a coupling system for mounting the gearbox within the gas turbine engine. The coupling system includes a flexible coupling connected to at least one of a fan frame or a core frame, as well as a torque frame connected to the flexible coupling and the gearbox. Moreover, a deflection limiter is provided, loosely attaching the flexible coupling to the gearbox to provide a predetermined axial range of motion, radial range of motion, and circumferential range of motion between the gearbox and the frame to which the flexible coupling is attached.

There is described an articulatable ducting system 700 for a gas turbine engine. The system comprises a first structure 710, a second structure 720, a first spherical joint 740, a second spherical joint 750 and a conduit 730. The first structure 710 defines a first internal volume 711. The second structure 720 defines a second internal volume 721, with the second structure 720 being movable with respect to the first structure 710. The first spherical joint 740 is associated with the first structure 710 and the second spherical joint 750 is associated with the second structure 720. The conduit 730 extends between the first and second spherical joints 740, 750 and thereby fluidically connects the first internal volume 711 to the second internal volume 721.

There is described an articulatable ducting system 700 for a gas turbine engine. The system comprises a first structure 710, a second structure 720, a first spherical joint 740, a second spherical joint 750 and a conduit 730. The first structure 710 defines a first internal volume 711. The second structure 720 defines a second internal volume 721, with the second structure 720 being movable with respect to the first structure 710. The first spherical joint 740 is associated with the first structure 710 and the second spherical joint 750 is associated with the second structure 720. The conduit 730 extends between the first and second spherical joints 740, 750 and thereby fluidically connects the first internal volume 711 to the second internal volume 721.