초록 ▼

A gas turbine engine system includes a fan (14), a housing (28) arranged about the fan, a gas turbine engine core having a compressor (16) at least partially within the housing, and a fan bypass passage (30) downstream of the fan for conveying a bypass airflow (D) between the housing and the gas tur

A gas turbine engine system includes a fan (14), a housing (28) arranged about the fan, a gas turbine engine core having a compressor (16) at least partially within the housing, and a fan bypass passage (30) downstream of the fan for conveying a bypass airflow (D) between the housing and the gas turbine engine core. A nozzle (40) associated with the fan bypass passage includes a first nozzle section (54a) that is operative to move in a generally axial direction to influence the bypass airflow, and a second 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. An actuator (42) selectively moves the first nozzle section and the second nozzle section to influence the bypass airflow and provide thrust reversal.

대표청구항 ▼

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 turb

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; andan 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. 2. The gas turbine engine system as recited in claim 1, wherein the second nozzle section includes at least one blocker door that is pivotable between the stowed position and the thrust reverse position, where the at least one blocker door pivots into the bypass passage in the thrust reverse position. 3. The gas turbine engine system as recited in claim 1, wherein the second nozzle section includes a curved leading end section for diverting the bypass airflow in the thrust reversing direction. 4. The gas turbine engine system as recited in claim 1, further comprising at least one cascade section between the second nozzle section and the housing, the cascade section having louvers for diverting the bypass airflow. 5. The gas turbine engine system as recited in claim 1, wherein the first telescoping section is concentric with the second telescoping section. 6. The gas turbine engine system as recited in claim 1, wherein the plurality of positions includes a closed position wherein the first nozzle section is sealed against the second nozzle section and an open position wherein the first nozzle section is spaced apart from the second nozzle section. 7. The gas turbine engine system as recited in claim 1, wherein the second nozzle section is sealed against the housing when the second nozzle section is in the stowed position and the second nozzle section is spaced apart from the housing when the second nozzle section is in the thrust reverse position. 8. The gas turbine engine system as recited in claim 1, further comprising a controller operative to command the actuator to move the first nozzle section between the plurality of positions in response to an aircraft take-off condition and to command the actuator to move the second nozzle section to the thrust reverse position in response to an aircraft landing condition. 9. A nozzle for use in a gas turbine engine, comprising: a first nozzle section operative to move in a generally axial direction relative to an engine centerline between a plurality of positions that influence a bypass airflow through a fan bypass passage;a second nozzle section adjacent the first nozzle section that is operative to also move in a generally axial direction relative to an engine centerline between a stowed position and a thrust reverse position that diverts the bypass airflow in a thrust reversing direction; andan 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. 10. A method of controlling a gas turbine engine system including a nozzle having a first nozzle section that is moveable to control a bypass airflow within a bypass passage and a second nozzle section having a stowed position and a thrust reverse position for slowing a vehicle and, the method comprising: (a) selectively independently moving the first nozzle section in an axial direction between an open position and a closed position using a first telescoping section of an actuator that is coupled with the first nozzle section such that the first nozzle section moves in unison with the first telescoping section to vary an effective cross-sectional area of the nozzle to control the bypass airflow; and(b) selectively independently moving the second nozzle section in the axial direction between the stowed position and the thrust reverse position using a second telescoping section of the actuator that is coupled with the second nozzle section such that the second nozzle section moves in unison with the second telescoping section to reverse a direction of the bypass flow and produce a thrust reversal force, wherein the first telescoping section is telescopically received within the second telescoping section. 11. The method as recited in claim 10, wherein said step (b) includes pivoting at least one blocker door of the second nozzle section from the stowed position to the thrust reverse position, where the at least one blocker door pivots into the bypass passage in the thrust reverse position. 12. The method as recited in claim 10, wherein said step (b) includes diverting the bypass airflow in a thrust reversing direction using a curved leading end section of the second nozzle section. 13. The method as recited in claim 10, including moving the first telescoping section relative to the second telescoping section that is concentric with the first telescoping section to move the first nozzle section. 14. The method as recited in claim 10, wherein said step (a) includes moving the first nozzle section from the closed position wherein the first nozzle section is sealed against the second nozzle section to the open position wherein the first nozzle section is spaced apart from the second nozzle section to increase the effective cross-sectional area. 15. The method as recited in claim 14, wherein said step (a) includes increasing the effective cross-sectional area in response to an aircraft take-off condition. 16. The nozzle as recited in claim 9, wherein the first telescoping section is directly coupled to the first nozzle section and the second telescoping section is directly coupled to the second nozzle section. 17. The nozzle as recited in claim 9, wherein movement of the first nozzle section in an axial direction to an open position provides an opening between an axially trailing end of the second nozzle section and an axially leading end of the first nozzle section. 18. The nozzle as recited in claim 9, wherein movement of the first nozzle section in an axial direction to an open position provides an opening between an axially trailing end of the second nozzle section and an axially leading end of the first nozzle section, and movement of the second nozzle section in an axial direction to an open position provides another opening between a leading end of the second nozzle section and a nacelle.