US Patent 11867400 Combustor with fuel plenum with mixing passages having baffles

A combustor for a gas turbine engine includes a liner surrounding a fuel and air mixing body. A gaseous fuel supply passage delivers gaseous fuel into the mixing body. A wall of the mixing body has air openings to communicate air into mixing passages. At least one fuel opening in each of the mixing passages allows fuel to flow into the mixing passages and mix with the air. There are passage sections downstream of a location of the fuel openings, such that the mixed air and fuel travel downstream of the location and into a combustion chamber. The passage sections have baffles that create a tortuous path. A gas turbine engine is also disclosed.