Raytheon Technologies Corporation

Joanne V Rampersad

San Quach

John R Battye

Kristy Rose Riley

A deflector panel for a combustor of a gas turbine engine includes an outer radial edge, an inner radial edge, and two circumferential edges extending between the outer radial edge and the inner radial edge. Each circumferential edge including a panel scallop at least partially defining a deflector opening receptive of a fuel nozzle of the combustor. A combustor of a gas turbine engine includes a combustor shell at least partially defining a combustion zone therein, and a deflector assembly operably connected to the combustor shell. The deflector assembly includes a plurality of circumferentially abutted deflector panels. Each deflector panel includes an outer radial edge, an inner radial edge, and two circumferential edges extending between the outer radial edge and the inner radial edge. Each circumferential edge includes a panel scallop at least partially defining a deflector opening. A fuel nozzle extends through the deflector opening.

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Manchester, CT, United States of America

Joanne V Rampersad