Air impingement cooling system
AssigneeROLLS-ROYCE plc
InventorsGeoffrey M. Dailey, Changmin Son
Life of this patent
Estimating the term…
Abstract
Where gas turbine engine structure eg combustion equipment, is to be air impingement cooled, the surface which receives the air jets is so shaped as to produce boundary layer separation zones 34, 38 and 44 in the cooling air, as it spreads across the surface. Mixing of the boundary layer with the remainder of the air flow results, followed by the re-establishment of the boundary layer. The new boundary layer is cooler than the original layer and so provides more effective cooling.
Claims10
An air impingement cooling system comprising, spaced apart members in superimposed relationship, one perforated, the other having a surface portion directly under each respective perforation, each said surface portion being of fluctuating shape, so as to cause air received thereby via respective perforations, and deflected laterally there across, to flow over said fluctuations, said fluctuating shape being such that the boundary layer of said air flow over said surface portion is caused to separate from said surface portion in the region of said fluctuations and subsequently reform downstream of said separation.
Dependencies are inferred from the claim text.