Abstract: A fuel injector head for a gas turbine engine the head comprising a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bounding a duct through which in use a fuel injected by the pilot injector flows. The splitter is hollow to improve cooling and has a radially inner surface which defines a first portion which tapers radially inwardly to a throat and a second portion which tapers radially outwardly from the throat with the angle of the radially outwards taper being such that a flow of air in use over the radially inner surface remains attached over the length of the surface.

Abstract: A fuel injector head for a gas turbine engine the head comprising a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bounding a duct through which in use a fuel injected by the pilot injector flows. The splitter is hollow to improve cooling and has a radially inner surface which defines a first portion which tapers radially inwardly to a throat and a second portion which tapers radially outwardly from the throat with the angle of the radially outwards taper being such that a flow of air in use over the radially inner surface remains attached over the length of the surface.

Abstract: A fuel injector for a gas turbine engine has a swirl slot that supplies fuel to a prefilmer. The swirl slot has an upstream lip and a downstream lip that are arranged eccentrically. The slot is thus provided with an area of high static pressure and an area of low static pressure caused by the flowing over the eccentrically arranged lips.

Abstract: A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.

Abstract: A wall structure for a gas turbine combustor arranged to have a general direction of fluid flow therethrough includes inner and outer walls defining a space therebetween. The inner wall is made up of a plurality of tiles having axial edges aligned generally with the direction of fluid flow, a gap being defined between axial edges of adjacent tiles. Orifices are provided within the axial edges to direct leakage air passing through the gaps to give the leakage air a flow component in the general direction of fluid flow through the combustor.

Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

Abstract: A wall element (29A, 29B) for a combustor (20) of a gas turbine engine (10). The wall element (29A, 29B) defines an axis. In use, the axis is arranged generally parallel to the principal axis of the engine (10). In one aspect, the length of the wall element (29B) along the axis is at least substantially 20% of the length of the wall element (29B) transverse to the axis. In another aspect, the wall element (29A, 29B) has a first pair of opposite edges extending transverse to the axis and a second pair of opposite edges (48, 50) extending transverse to the first pair, at least one of the second pair of edges (48, 50) being angled relative to the axis of the wall element (29A, 29B).

Abstract: A fuel injector assembly designed to withstand a predetermined impact load resulting from ingestion of a bird or other foreign object into the combustion stage of a gas turbine engine comprises a body member adapted to be mounted adjacent to and to extend into the combustion chamber and an abutment member disposed downstream of the injector assembly in the direction of air flow through the combustion stage, the arrangement being such that the body member moves into contact with the abutment member when subjected to an impact load in excess of the impact load it is designed to withstand.

Abstract: A wall structure for a gas turbine combustor arranged to have a general direction of fluid flow therethrough includes inner and outer walls defining a space therebetween. The inner wall is made up of a plurality of tiles having axial edges aligned generally with the direction of fluid flow, a gap being defined between axial edges of adjacent tiles. Orifices are provided within the axial edges to direct leakage air passing through the gaps to give the leakage air a flow component in the general direction of fluid flow through the combustor.

Abstract: A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.

Abstract: A double wall structure for a gas turbine engine has an inner wall comprising a number of tiles. The outer wall is provided with a number of apertures through which air is directed into the space between the two walls. Inclined apertures are provided in the tiles so that cooling air can pass into the combustion chamber and form a cooling film underneath the tile. Each tile is provided with a number of pedestals. The orientation of the inclined apertures is such that the axis of each aperture lies upon an unobstructed channel between the pedestals.