INTEGRATED FRONT PANEL FOR A BURNER OF A GAS TURBINE ENGINE

A gas turbine engine (10) includes a compressor (14) and a turbine (26) with a burner (22) and a combustor (24) between the compressor (14) and the turbine (26). The burner (22) is downstream of the compressor (14) and upstream of the turbine (26). The burner (22) is connected to the combustor (24) at a front panel (100) of the burner (22). The front panel (100) includes a frame (102), a rim (112) extending around a central aperture (114) within the frame (102), and a seal segment (116). The frame (102), the rim (112), and the seal segment (116) are all integrally formed as a single unitary body.