Patent ID: 11933221
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A gas turbine engine comprising:
a core including a compressor section fluidly connected to a combustor via a primary flowpath and a turbine section connected to the combustor via a core flow path;
an assembly disposed within the gas turbine engine, the assembly including a first part connected to a second part via a radial stack joint, the first part including a radially inward facing surface contacting a corresponding radially outward facing surface of the second part over an extent, and one of the contacting radially inward facing surface and the radially outward facing surface being a tongue extending from an associated one of the first and second part;
a fastener extends through the radially inward facing surface of the first part and the radially outward facing surface of the second part in the extent and configured to maintain the relative positions of the first part and the second part; and
a channel disposed on at least one of the radially inward facing surface and the radially outward facing surface positioned radially between the radially inward facing surface and the radially outward facing surface and positioned between the fastener and a circumferential edge of the first part, the channel being connected to at least one cooling air source; and
wherein the first and second parts are combustor panels in the combustor.