Back to results
US 8,006,479 B2Granted
Thrust reversing variable area nozzle
AssigneeUnited Technologies Corporation
InventorAlfred M. Stern
Life of this patent
Estimating the term…
Abstract
A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap between the first nozzle section and the second nozzle section. A movable door between the first nozzle section and the second nozzle section selectively opens or closes the gap.
Claims23
A gas turbine engine system, comprising:
- a first nozzle section associated with a gas turbine engine bypass passage;
- a second nozzle section having a plurality of positions relative to the first nozzle section such that there is a gap between the first nozzle section and the second nozzle section in at least one of the positions;
- a moveable door at least partially between the first nozzle section and the second nozzle section for selectively opening and closing the gap, wherein an entire radially outer surface of the moveable door is radially inward of a radially outer surface of the first nozzle section and a radially outer surface of the second nozzle section, wherein the movable door is located radially outwards of the gas turbine engine bypass passage relative to the engine centerline axis;
- and
- a thrust reverser blocker door for thrust reversing connected for movement with the moveable door.
2 more elements
A gas turbine engine system, comprising:
- a fan;
- a combustion section downstream of the fan;
- a turbine section downstream of the combustion section;
- a fan bypass passage downstream from the fan;
- a nozzle associated with the fan bypass passage, the nozzle having a first nozzle section and a second nozzle section having a plurality of positions relative to the first nozzle section such that there is a gap between the first nozzle section and the second nozzle section in at least one of the positions;
- a moveable door at least partially between the first nozzle section and the second nozzle section for selectively opening and closing the gap, wherein an entire radially outer surface of the moveable door is radially inward of a radially outer surface of the first nozzle section and a radially outer surface of the second nozzle section, wherein the movable door is located radially outwards of the gas turbine engine bypass passage relative to the engine centerline axis;
- and
- a thrust reverser blocker door for thrust reversing connected for movement with the moveable door.
5 more elements
A method of controlling a gas turbine engine nozzle having a first nozzle section and a second nozzle section, comprising:
- selectively moving the second nozzle section relative to the first nozzle section to establish a desired axial bypass flow through the nozzle and establish a gap between the first nozzle section and the second nozzle section;
- and
- selectively moving a door that is located at least partially between the first nozzle section and the second nozzle section to open or close the gap, wherein an entire radially outer surface of the door is radially inward of a radially outer surface of the first nozzle section and a radially outer surface of the second nozzle section, wherein the door is located radially outwards of a gas turbine engine bypass passage relative to a engine centerline axis;
- and
- selectively moving a thrust reverser blocker door connected for movement with the door.
2 more elements
A gas turbine engine system, comprising:
- a first nozzle section associated with a gas turbine engine bypass passage;
- a second nozzle section having a plurality of positions relative to the first nozzle section such that there is a gap between the first nozzle section and the second nozzle section in at least one of the positions;
- a movable door at least partially between the first nozzle section and the second nozzle section for selectively opening and closing the gap, wherein the movable door is radially inward of a radially outer surface of the first nozzle section and a radially outer surface of the second nozzle section, wherein the movable door is located radially outwards of the gas turbine engine bypass passage relative to the engine centerline axis;
- and
- a thrust reverser blocker door for thrust reversing attached to an inner cowl and connected for movement with the moveable door.
2 more elements
Dependencies are inferred from the claim text.