Rolls-royce Corporation

David W Barrett

John Slinger

Christopher M Robson

Philip D Robinson

A turbine blade comprising a pressure wall and a suction wall joined together at leading and trailing edges and having a root portion and a blade tip region, the walls further define a hollow chamber and through which cooling air is directed in use from the root portion to the blade tip region only, characterized in that at least one of the walls defines at least one cooling rib that extends outwardly from the wall into the chamber and at least a portion of the rib tapers between the root portion and a blade tip region.

Aerofoil configuration

A gas turbine engine turbine blade () has cooling air holes () arranged in groups, the holes () in one group and which span that part of the leading edge () that spans the hottest part of the blade (), are more closely spaced than the remainder of the holes (), thereby ensuring the provision of the most cooling air, where it is most needed.

Cooled turbine blade

A stage of turbine blades ( ) in a gas turbine engine ( ) is surrounded by an array of shroud segments ( ). The upstream ends of the segments ( ) have plenum chambers ( ) into which cooling air is fed from a compressor ( ) via one hole ( ) of a pair of holes, the other being numbered ( ). Air from the plenum chambers ( ) passes out to film cool the interior surface of each respective segment ( ). Air from holes ( ) passes out to convection cool the exterior surface of each segment ( ), which effect is enhanced by the provision of ribs ( ) and fences ( ).

Gas turbine structure

An air cooled guide vane ( ) is provided with a stack of ducts ( ) each of which converges towards its outlet end. Air flow turbulators ( ) are positioned in ducts ( ) and pressure losses in the air flow brought about by flowing over the turbulators ( ), is recovered by the constricting effect of the ducts ( ).

Growing community of inventors

Derby, United Kingdom

David W Barrett