Rolls-royce Corporation

James R Woolford

Stephen J Mills

Kevin A White

A wall element of a gas turbine engine having an inner hot surface, and an outer cooler surface, during use. A plurality of projections is provided on the outer surface to facilitate heat transfer to a coolant flow during use. The projections are arranged in a first density pattern and in a second higher density pattern for increased cooling. The second higher density pattern is positioned adjacent a hotter region of the tile than the first density pattern to reduce the thermal gradient throughout the wall element.

Wall elements for gas turbine engine combustors

The invention relates to a wall element for a wall structure of a gas turbine engine combustor. The wall element has an inner, in use, hot surface, and an outer, in use, cooler surface. A plurality of projections is provided on the outer surface to facilitate heat transfer to a coolant flow. The wall element comprises a means to direct more coolant flow at a hot-spot on an adjacent tile than the remainder of the adjacent tile and thereby reducing the thermal gradient across the adjacent tile.

A combustor wall element arrangement for a gas turbine engine comprises an upstream wall element (A) overlapping a downstream wall element (B) and defining a gap () and an outlet () therebetween. In use, a coolant flow exits the outlet () to provide a coolant film (D) across at least a part of the downstream wall element (B). The outlet () has a smaller dimension, normal to the downstream wall element (B), than the gap () thereby increasing the velocity of the coolant flow across at the downstream wall element (B). The resultant film coolant flow is effective further across the downstream wall element.

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Bristol, United Kingdom

James R Woolford