Abstract: A combustion chamber arrangement has an annular outer wall and an annular inner wall having an upstream row of tiles and a downstream row of tiles. The outer wall has a concave bend which is less than 175°. The downstream end of the upstream tiles and the upstream end of the downstream tiles are adjacent the concave bend. The downstream ends of the upstream tiles are spaced at a greater distance from the inner surface of the annular outer wall than the upstream end of the downstream tiles. The upstream tiles have curved lips extending in a downstream direction which overlap but are spaced radially from the upstream ends of the downstream tiles. The outer wall has a row of apertures to direct coolant onto the outer surfaces of the curved lips and the upstream tiles has a row of apertures extending to the inner surfaces of the curved lips.

Abstract: A combustion chamber arrangement has an annular outer wall and an annular inner wall having an upstream row of tiles and a downstream row of tiles. The outer wall has a concave bend which is less than 175°. The downstream end of the upstream tiles and the upstream end of the downstream tiles are adjacent the concave bend. The downstream ends of the upstream tiles are spaced at a greater distance from the inner surface of the annular outer wall than the upstream end of the downstream tiles. The upstream tiles have curved lips extending in a downstream direction which overlap but are spaced radially from the upstream ends of the downstream tiles. The outer wall has a row of apertures to direct coolant onto the outer surfaces of the curved lips and the upstream tiles has a row of apertures extending to the inner surfaces of the curved lips.

Abstract: A combustion chamber has an outer wall supporting a number of wall elements or tiles. The tiles are located on the wall by bosses so that a cooling space is provided between the wall and the tiles. Air holes are provided through the wall and the tiles and a flow passage is provided adjacent the air holes. A flow passage is defined by changing the profiles of the air holes in the outer wall and/or the location features to provide a localized gap through which cooling air is directed to cool regions subject to overheating and extend service life.

Abstract: A combustion chamber has an outer wall supporting a number of wall elements or tiles. The tiles are located on the wall by bosses so that a cooling space is provided between the wall and the tiles. Air holes are provided through the wall and the tiles and a flow passage is provided adjacent the air holes. A flow passage is defined by changing the profiles of the air holes in the outer wall and/or the location features to provide a localised gap through which cooling air is directed to cool regions subject to overheating and extend service life.

Abstract: A wall structure for a gas turbine engine combustor has an inner wall and an outer wall defining a duct, the wall structure including an outer wall having a radial step and an inner wall overlapping the radial step, a duct being defined between the inner and outer walls for the passage of cooling air; the wall structure being characterised in that the inner wall has a local thickening opposing the radial step. The velocity of cooling air through the duct is maintained and heat transfer subsequently improved.

Abstract: A wall structure for a gas turbine engine combustor has an inner wall and an outer wall defining a duct. The duct diverges as it extends in the general direction of fluid flow within the combustor. Cooling air is fed into the duct through angled cooling holes which provide a film of fluid over the outer wall of the combustor should the inner wall be eroded because of the high temperatures in the combustor.