Patent ID: 11867402
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 15:
16. A gas turbine engine, comprising:
a combustor section having a plurality of combustor assemblies arranged circumferentially about an engine axis;
at least one of the combustor assemblies having a liner panel arranged within a combustion chamber, the liner panel including:
a first portion and a second portion extending in a substantially axial direction, the first portion axially forward of the second portion, and
a step connecting the first portion and the second portion, the step arranged at an angle to the second portion that is less than 90° such that the step slants axially forward from the second portion to the first portion, the step joining to the first portion at a first fillet and joining to the second portion at a second fillet, the first and second fillets arranged on surfaces of the liner panel facing into the combustion chamber;
wherein a step height is defined between the first portion and the second portion, and a ratio of a radius of the second fillet to the step height is between 0.3 and 0.5; and
wherein the liner panel is a ceramic matrix composite material.