GAS TURBINE COMBUSTOR WITH TONGUE JOINT AND METHOD TO COOL SAID JOINT

A gas turbine engine (20) including a core having a compressor section (24) fluidly connected to a combustor (56) via a primary flowpath and a turbine section (28) connected to the combustor (56) via the core flow path (C). An assembly is disposed within the gas turbine engine (20) and includes a first part (110) connected to a second part (120) via a radial stack joint. The first part (110) includes a radially inward facing surface (112) contacting a corresponding radially outward facing surface (126) of the second part (120). A fastener (130) protrudes through the first part (110) and the second part (120) and is configured to maintain the relative positions of the first part (110) and the second part (120). A channel (140) is disposed on at least one of the radially inward facing surfaces (112, 126) and is positioned between the fastener (130) and a circumferential edge of the first part (110). The channel (140) is connected to at least one cooling air source (150).