Abstract: A method of assembling a mounting device for an electrical harness of a gas turbine engine is provided. The electrical harness has a wire bundle. The method includes providing a first shell and providing a second shell. The method further includes coupling the first shell to the second shell with the wire bundle disposed between the first shell and the second shell such that movement of the first shell and the second shell along the wire bundle is restricted.

Abstract: A method and a system for a mounting device are provided. The mounting device includes at least two shells, each shell having an inner surface and an outer surface wherein the outer surface includes a first banding zone, a second banding zone, and a clamping zone extending between the first banding zone and the second banding zone and a pair of shoulders bounding each of the first banding zone and second banding zone. The mounting device also includes an intermediary material circumscribing the wire bundle including at least one of a substantially non-porous material, a vulcanizing tape, and a silicone material. The mounting device further includes at least one fastener configured to engage the first banding zone or second banding zone to couple the first shell and the second shell to the wire bundle and the intermediary material.

Abstract: A method of assembling a mounting device for an electrical harness of a gas turbine engine is provided. The electrical harness has a wire bundle. The method includes providing a first shell and providing a second shell. The method further includes coupling the first shell to the second shell with the wire bundle disposed between the first shell and the second shell such that movement of the first shell and the second shell along the wire bundle is restricted.

Abstract: A combustion system for a gas turbine engine is disclosed. Fluid transfer and premixing techniques are developed. The combustion system is specifically adapted, in one embodiment, to an engine having a centrifugal or an axial/centrifugal compressor including a pipe diffuser at the downstream end thereof. Flow transfer tubes are shown between the pipe diffuser and a radial inflow combustor.