ASSEMBLY FOR A COMPRESSOR SECTION OF A GAS TURBINE ENGINE

Assemblies and methods for directing a flow of air (56) through a compressor section (14) of a gas turbine engine (10) are disclosed. A method includes receiving the flow of air (56) over a strut (42A) extending radially across a substantially annular gas path (22) of the gas turbine engine (10), and at least partially confining and modifying a strut wake (68) generated in the flow of air (56) by the strut (42A) using one or more variable orientation guide vanes (24).