Combustor tile for a combustor of a gas turbine engine

A combustor for a gas turbine engine, the combustor comprising:

• a primary zone;
• a secondary zone downstream of the primary zone;
• and
• a plurality of tiles lining the primary and secondary zone of the combustor, wherein a series of tiles are arranged to extend axially such that a portion of each of the tiles in said series of tiles is in the primary zone and a portion of said same tiles is in the secondary zone.

A combustor for a gas turbine engine, the combustor comprising:

• inner and outer combustor walls defining a primary zone and a secondary zone, the inner and outer combustor walls in the primary zone being arranged at a first angle relative to each other, and the inner and outer combustor walls in the secondary zone being arranged at a second angle relative to each other, the second angle being different to the first angle;
• a fuel injector provided in the primary zone;
• an ignitor provided in the primary zone;
• a plurality of air inlets provided in the secondary zone for injecting air into the fit, combustor;
• and
• a plurality of combustor cooling tiles lining the combustor walls and connected thereto;
• wherein one or more of the combustor cooling tiles extend from the primary zone to the secondary zone such that a portion of the tile is in the primary zone, a portion of the tile is in the secondary zone and the tile extends across a transition from the primary zone to the secondary zone.