Combustor panel endrail interface

A gas turbine engine comprising:

• a combustor shell comprising a diffuser side facing a diffuser chamber and a combustor side facing a combustor chamber;
• a first combustor panel coupled to the combustor side of the combustor shell, the first combustor panel comprising a first endrail;
• and
• a second combustor panel coupled to the combustor side of the combustor shell, the second combustor panel comprising a second endrail;
• wherein
• an annular cooling cavity is defined between the combustor shell and the first and second combustor panels and a channel is defined between the first endrail and the second endrail, wherein
• a first gap is defined between the combustor shell and a first surface of the first endrail closest to the combustor shell, and having a first distance,
• a second gap is defined between the combustor shell and a second surface of the second endrail closest to the combustor shell, and having a second distance being the same as the first distance, and
• the annular cooling cavity is fluidly connected to the channel via the first gap and the second gap such that the channel fluidly connects the annular cooling cavity to the combustor chamber, wherein
• direct line-of-sight through the channel from the annular cooling cavity to the combustor chamber is obstructed such that a centerline axis of the channel extending from at least one of the first gap and the second gap to the combustor chamber is non-linear.

A method of assembling a gas turbine engine, the method comprising:

• coupling a first combustor panel to a combustor shell, the first combustor panel comprising a first endrail, wherein
• a first gap is defined between the combustor shell and a first surface of the first endrail closest to the combustor shell, and having a first distance;
• positioning a second combustor panel adjacent the first combustor panel such that a channel is defined between the first endrail of the first combustor panel and a second endrail of the second combustor panel, wherein
• direct line-of-sight through the channel from an annular cooling cavity defined between the combustor shell and the first and second combustor panels to a combustor chamber is obstructed;
• and
• coupling the second combustor panel to the combustor shell, wherein
• a second gap is defined between the combustor shell and a second surface of the second endrail closest to the combustor shell, and having a second distance being the same as the first distance, and
• a centerline axis of the channel extending from at least one of the first gap and the second gap to the combustor chamber is non-linear.