Rolls-royce Corporation

Other

Stephen J Mills

Kevin A White

James R Woolford

Jochen Rupp

John E Rimmer

Michael A Macquisten

Lynn I Steward

Robin D Monico

Murthy V Ravikanti

Andrew J Bradley

A gas turbine engine combustion chamber arrangement includes an annular outer wall and annular inner wall including an upstream and a downstream row of tiles. The downstream end of each tile in the upstream row of tiles has a rail extending towards and sealing with the outer wall and a lip extending in a downstream direction towards the tiles in the downstream row of tiles. The outer wall has a row of apertures to direct coolant onto the lips of the tiles in the upstream row of tiles. The downstream end of each tile in the upstream row of tiles has a plurality of fences extending in a downstream direction from the rail and each fence extends from the outer surface of the lip towards the outer wall. The row of apertures in the annular outer wall is arranged to direct coolant onto the lip between two circumferentially adjacent fences.

Combustion chamber with fences for directing cooling flow

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.

Gas turbine engine clearance control

The problem of excessive clearances being generated by rub occurring between the tips of turbine blades and the linings on shroud segments which surround the blades is addressed by way of providing a valve 42 of a metal of different coefficient of expansion than the shroud control ring 24. On ground running prior to take off of an associated aircraft, the valve diverts a cooling airflow away from the ring 24, thus causing it to run hot and expand radially. The shrouds 22 are thus moved away from the blade tips 40 and on take off, are sufficiently far away from the tips 42 as to avoid deep penetration of the lining 38 thereby. The higher temperature generated by take off affects the valve 40 and makes it expand rapidly, to open the cooling airflow paths to the ring 24 via the holes 46 and 50.

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Ashbourne, United Kingdom

Stephen J Mills