Patent ID: 8632299

Claim:
A gas turbine engine having a compressor, the engine comprising: an annular outer case surrounding at least a section of the gas turbine engine; an annular core case concentrically positioned within the outer case and radially outwardly of the compressor, the core case having an annular leading edge providing a splitter to divide an air flow duct from an inlet of the engine into a bypass air flow duct and a core air flow duct, the splitter defining an annular passage therein, the passage communicating with the core air flow duct through a plurality of nozzle orifices configured on the splitter; and a plurality of circumferentially spaced struts radially extending from the outer case to the core case, the struts including at least one having an internal passage therein in fluid communication with the annular passage defined in the splitter, the at least one strut internal passage communicating also with an inlet configured on the outer case to receive a flow of washing fluid from a source external to the engine, and directing the flow of washing fluid through the annular passage and the nozzle orifices into the core air flow duct to blades of the compressor.