公开(公告)号：US20200024993A1

公开(公告)日：2020-01-23

申请号：US16294211

申请日：2019-03-06

Applicant: ROLLS-ROYCE PLC

Inventor： Prabhu I.S KUMAR ,  Thomas G. MULCAIRE ,  Dasthagiri R. THUMMALURU

IPC: F01D9/04 ,  F23R3/50 ,  F01D11/00

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.