Abstract: An annular vane assembly for a gas turbine engine is provided. The assembly includes a vane segment, the vane segment includes an arcuate rail and a vane that extends radially inwardly from the arcuate rail. The assembly also includes a hollow cylindrical casing, the inside curved surface of which an annular groove is formed that receives the arcuate rail. The arcuate rail is secured in the annular groove using a resilient strip interposed between the rail and the groove. The resilient strip includes a planar main body and sprung wings that extend to either side of the main body. The wings are angled with respect to the plane of the main body. The resilient strip is moveable circumferentially between a first position in which the strip exerts a force radially on the arcuate rail and a second position in which the wings occupy recesses in the assembly.

Abstract: A diffuser for decelerating a compressed gas, is provided, which includes a ring divided at circumferential positions around the ring into several arcuate sections, the complete ring is assembled from these sections. The ring defines one or more passages, the cross-section of which increases in the direction of flow of a fluid through the diffuser. The interface between adjacent sections is configured so that relative movement between the sections is prevented. The interface is configured to have a series of interlocking serrations along the axial length of the diffuser. In an embodiment, there are two arcuate sections involving two interfaces, and the peaks and troughs of the serrations of each of the two sections are arranged at an angle to a longitudinal axis of the diffuser. A small relative movement between the sections is achieved when the two angles at the two interfaces have opposite signs.