Abstract: A gas turbine engine combustion arrangement includes an annular combustion chamber, an annular discharge nozzle, an array of turbine nozzle guide vanes and an annular casing. The nozzle is between the downstream end of an outer annular wall of the annular combustion chamber and the array of turbine nozzle guide vanes. The annular casing surrounds the annular combustion chamber, the annular discharge nozzle and the array of turbine nozzle guide vanes. The upstream end of the annular discharge nozzle has an annular axially extending slot and the downstream end of the outer annular wall of the annular combustion chamber locates in the annular axially extending slot in the upstream end of the nozzle. The upstream ends of the radially outer platforms of the turbine nozzle guide vanes are adjacent the downstream end of the annular discharge nozzle and a support structure is connected to the nozzle and the annular casing.

Abstract: A rear outer discharge nozzle for a gas turbine engine, the rear outer discharge nozzle forming a loop around an axis and comprising: a first part; a second part wrapped around the first part; and a radial slit, having first and second side walls; wherein the first part is shaped to provide the first side wall of the radial slit, and the second part is shaped to provide the second side wall of the radial slit; and wherein the second part comprises a break, splitting the second part in the axial part.