Shaft-supported composite high-strength machine element and method of making the same
Thermal-mechanical working of wrought non-hardenable nickel alloy
Gas turbine engine combustor splash ring construction Patent #: 4566280
ApplicationNo. 07/185309 filed on 04/20/1988
US Classes:60/757, In an axial direction60/754Porous
ExaminersPrimary: Casaregola, Louis J.
Assistant: Thorpe, Timothy S.
International ClassesB23K 1/14 (20060101)
B23K 1/18 (20060101)
F23R 3/08 (20060101)
F23R 3/00 (20060101)
F23R 3/04 (20060101)
AbstractAn assembly of stacked rings is provided to form the cylindrical section of a combustor such as used in a gas turbine engine. Each ring is force-fitted into its adjacent ring and joined to it, as by brazing, to form a unitary structure. The rings are configured to assure proper alignment when fitted together and provide a space for holding brazing material immediately adjacent to the mating surfaces to be joined so that the brazing material, when fused in a vacuum furnace, flows evenly between the surfaces. To assure proper distribution of the brazing material when fused, one of the mating surfaces may be upset, as by knurling, to a dimension assuring a light force-fit of the parts to be joined. Each ring also includes a shaped portion projecting into the interior of the assembly for directing cooling air, introduced through the side walls of the rings, along the interior surfaces of the assembly to protect it from high temperature gases generated by combustion of fuel within the combustor.