Abstract: A high temperature mounting system useful, for example for ceramic composite flameholders in a gas turbine engine reheat system uses dovetail clamping. A flameholder carries a dovetail projection which is clamped against a further ceramic, intermediate member by wedge blocks on opposite sides of the dovetail. The intermediate member has raised edges with angled faces opposite the dovetail projection against which the wedge blocks bear. The assembly is clamped to a metal support or flange by clamp bolts which pass through each of the wedge blocks and the intermediate member. The included angle of the contact faces is determined by principles of DAZE geometry to keep the bolts from loosening due to differential thermal expansion. Each wedge block is clamped by single bolt and relative expansion between the bolts is absorbed by bolt bending or nut sliding.

Abstract: A seal for use at high temperatures in an interface between a ceramic component and a metal component has a multi-layer construction arranged so that the seal expands disproportionately more in cross-section than in elongation at increasing operating temperatures. The seal comprises a central core made up of a bundle of elongate ceramic fibers surrounded by a layer of braided metal wire and an outer sheath of braided ceramic fiber. The seal may be formed as an O-ring.

Abstract: A mounting arrangement for a composite material flameholder in teh reheat system of a gas turbine engine provides for a flameholder to be suspended from a flameholder bracket in the jet pipe by a means of pivotal mounting and to be restrained from movement by a leaf spring mounted trunnion attached between the bracket and the flameholder at a second mounting spaced a short distance away from the first. The resilience of the leaf spring allows movement in directions parallel to a line through the axes of the two mountings in order to accommodate differential thermal growth of the composite flameholders and their metallic supporting structure.

Abstract: A reheat system for a gas turbine engine includes a plurality of radial flameholders constructed of non-metallic material, such as a ceramic composite or carbon/carbon reinforced material, mounted on a metallic support structure in the engine jet pipe. The metallic support structure may be cooled by air from the engine bypass duct, and the non-metallic flameholders are capable of withstanding higher exhaust gas temperatures in the jet exhaust beyond the capability of currently used metal alloy materials. However, the mounting assembly must be capable of absorbing the considerable differential thermal expansion which will take place.

Abstract: In a reheat system of an aircraft gas turbine engine there is provided a cantilever mounting for a ceramic tubular flameholder 10 on a metal bracket 11, the bracket being provided with a face having an upstanding annular flange 16 adapted to mate with the outer surface 19 of an end portion of the flameholder, there being further provided fastener means 12 adapted to retain the end face of said end portion of the flame holder adjacent and facing said face of the bracket, characterized in that said end portion of the flameholder is provided by a frusto-conical section 27 having first and second surfaces 18, 19 of different angles such that line extensions of each surface coincide at respective imaginary vertices on the axis of the flame holder.