Patent ID: 8104261
Filing Date: 2012-01-31
Classification: F02K,Y02T

Abstract:
1. A gas turbine engine system comprising: a fan rotatable about an axis; a housing arranged about the fan; a gas turbine engine core having a compressor at least partially within the housing; a fan bypass passage downstream of the fan for conveying a bypass airflow between the housing and the gas turbine engine core; a nozzle having a first nozzle section operative to move in a generally axial direction relative to the axis between a plurality of positions that influence the bypass airflow, and a second nozzle section adjacent the first nozzle section that is operative to also move in a generally axial direction between a stowed position and a thrust reverse position that diverts the bypass airflow in a thrust reversing direction; and an actuator including a telescoping member having a first telescoping section coupled with the first nozzle section such that the first nozzle section is moveable in unison with the first telescoping section and a second telescoping section coupled with the second nozzle section such that the second nozzle section is moveable in unison with the second telescoping section, wherein the first telescoping section is telescopically received within the second telescoping section, and wherein the first telescoping section and the second telescoping section are moveable independently of each other to selectively independently move the first nozzle section and the second nozzle section.