COMPRESSOR SECTION FOR A GAS TURBINE ENGINE, CORRESPONDING GAS TURBINE ENGINE AND METHOD OF OPERATING A COMPRESSOR SECTION IN A GAS TURBINE ENGINE

摘要

A compressor section (52) for a gas turbine engine comprises an upstream portion (82) that includes at least one upstream rotor stage (60) und a downstream portion (84) that includes at least one downstream rotor stage (60) configured to rotate with the upstream rotor stage (60). A transition duct (88) separates the upstream portion (82) from the downstream portion (84). A method of operating a compressor section in a gas turbine engine (20) comprises the steps of:rotating at least one upstream rotor stage (60) of the compressor section (52) at the same rotational speed as at least one downstream rotor stage (60) of the compressor section (52); and reducing a tip speed of the at least one downstream rotor stage (60) relative to a tip speed of the at least one upstream rotor stage (60) by locating a transition duct (88) axially between the at least one upstream rotor stage (60) and the at least one downstream rotor stage (80).