Patent ID: 7353647
Filing Date: 2008-04-08
Classification: F02C,F05D

Abstract:
1. A method for assembling a gas turbine engine, said method comprising: providing a fan assembly; coupling a compressor downstream from the fan assembly and in flow communication with the fan assembly; coupling a high-pressure turbine to the compressor; coupling a low-pressure turbine to the fan assembly such that the low-pressure turbine is downstream from the high-pressure turbine; and coupling a bypass system to the gas turbine engine, wherein the bypass system has a plurality of circumferentially-spaced bypass ducts each having an upstream end coupled upstream from the low-pressure turbine to a transition duct downstream of the high pressure turbine having an upstream end and downstream end, the transition duct diverging from an engine centerline axis such that at the downstream end, the duct is positioned substantially radially further from the axis than at the upstream end, each said bypass duct having a downstream end coupled to the gas turbine engine downstream from the low-pressure turbine such that a portion of the airflow discharged from the high-pressure turbine is channeled through the upstream end of each respective bypass duct, bypassed around the low-pressure turbine, and is discharged through the downstream end of each respective bypass duct and is directed into the gas flowpath downstream from the low-pressure turbine to facilitate controlling gas turbine engine thrust.