Patent ID: 9097140
Filing Date: 2015-08-04
Classification: F01D,F02C,F02K,F05D,Y02T

Abstract:
1. A ventilation arrangement for a substantially annular cavity located about a core engine of a gas turbine, the annular cavity having an inner wall located about the core engine and an outer wall radially spaced from the inner wall, the outer wall being interposed between the cavity and an engine bypass duct, the ventilation arrangement comprising: one or more ventilation ducts passing through said outer wall so as to allow fluid communication between the bypass duct and the cavity; and, a flow diverter arranged at an oblique angle to the outer wall, the flow diverter having a flow exit opening that is separated from the outer wall such that the flow diverter is configured to induce, in the ventilation flow from the ventilation ducts, a vortical flow within the cavity about the inner wall, the vortical flow having a vortex width of magnitude substantially equal to that of a diameter of the annular cavity.