Liner element for a combustor, and a related method

A liner element for a gas turbine combustor having a structural wall with fixing apertures provided therethrough, the liner element having a unitary construction defining a cooling side and combustion side, and a plurality of effusion holes extending between a cooling side surface of the element and a combustion side surface of the element;

• the liner element being configured to be affixed to the structural wall of a combustor with its cooling side surface spaced from the wall to define a chamber between the cooling side surface and the wall and having a peripheral flange configured to engage said wall of the combustor when the liner element is affixed thereto, wherein the liner element further includes integrally formed and non-threaded protuberances on its cooling side, the protuberances being arranged to engage and extend through respective fixing apertures in the combustor wall and at least some of said protuberances projecting from said flange;
• and one or more fixing elements, each fixing element configured to mechanically engage a respective protuberance in an interlocking manner.