Rolls-royce Corporation

Mark Timothy Mitchell

Ian Tibbott

Peter Ireland

Keith C Sadler

Michiel Kopmels

Sean Alan Walters

Edwin Dane

Peter Jeffrey Goodman

Vikram Mittal

Daniel P Moss

Keith Christopher Sadler

Daniel Paul Moss

Described is a seal segment () for a gas turbine engine, comprising: a gas facing wall () having a gas facing surface () and a first internal surface (); an outboard wall () having an outboard facing surface () and a second internal surface () which is radially separated from the first internal surface with a gap therebetween; a first conduit () located between the first and second internal surfaces; and, a second conduit () located between the first and second internal surfaces, wherein the first and second conduits are radially separated by a party wall ().

Heat exchanger seal segment for a gas turbine engine

A gas turbine engine airfoil () has a wall () provided with a cooling effusion hole () therein to facilitate film cooling of the external surface () of the wall (). A member () attached to the internal surface () of the airfoil wall () is provided with an aperture () which at least partially overlaps the cooling effusion hole (). The airfoil wall () and member () are formed from materials having different coefficients of thermal expansion and are mounted such that over a temperature range, the aperture () and cooling effusion hole () interact to a greater or lesser extent to modulate the flow of cooling air therethrough.

Cooling airflow modulation

A component such as a turbine blade of a gas turbine engine has a cooling arrangement comprising a cascade impingement array in which cooling air flows from a supply chamber through impingement passages in webs to an internal passageway comprising first and second limbs. The cooling air flow through the limbs, provides improved heat transfer compared with continued impingement cooling in the chordwise direction of the blade.

Air-cooled component

A wall cooling arrangement comprising on one side of a wall a multiplicity of cooling fluid inlet apertures and on the opposite of the wall a multiplicity of cooling fluid exit apertures, and in the body of the wall linking said inlet and exit apertures a network of multiply branched cooling passages. Flow of cooling fluid through a network is controlled by a throat positioned either at or close to the inlet to the passage network or at a location part way through the network, in which case there may be a plurality of inlet apertures feeding through a single throat to a plurality of outlet apertures.

Wall cooling arrangement

A component comprises a multiplicity of cooling passages arranged in two intersecting arrays to form a multiplicity of cooling passage intersections. Air jet interactions are generated at cooling passage intersections when air is passed through the cooling passages. The spacing of the passages in at least one of the arrays is chosen to provide a predetermined range of intersection density in a selected region or regions of the component.

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Bristol, United Kingdom

Mark Timothy Mitchell