초록

A method of varying a fan duct throat area of a gas turbine engine may include non-pivotably moving a fan nozzle outwardly relative to a longitudinal axis of the gas turbine engine during axially aft translation of the fan nozzle without activating a thrust reverser.

대표청구항 ▼

1. A method of varying a fan duct throat area of a gas turbine engine having a longitudinal axis and a thrust reverser having movable blocker doors configured to block fan flow through the fan duct when the thrust reverser is activated, comprising the step of: non-pivotably moving a fan nozzle radia

1. A method of varying a fan duct throat area of a gas turbine engine having a longitudinal axis and a thrust reverser having movable blocker doors configured to block fan flow through the fan duct when the thrust reverser is activated, comprising the step of: non-pivotably moving a fan nozzle radially outwardly along a direction diverging from the longitudinal axis while simultaneously translating the fan nozzle in an axially aft direction without activating the thrust reverser. 2. The method of claim 1 further comprising the step of: moving the fan nozzle outwardly during axially aft translation and inwardly during axially forward translation between stowed and deployed positions. 3. The method of claim 2 further comprising the step of: maintaining an orientation of the fan nozzle relative to the longitudinal axis when moving the fan nozzle between the stowed and deployed positions. 4. The method of claim 2 wherein the gas turbine engine includes a cowl assembly and a fan duct outer wall, the fan nozzle defining at least a portion of the fan duct outer wall, the method further comprising the step of: substantially maintaining continuity of the fan duct outer wall across the cowl assembly and the fan nozzle when moving the fan nozzle between the stowed and deployed positions. 5. The method of claim 4 wherein the cowl assembly includes a translating sleeve, the method further comprising the steps of: moving the translating sleeve axially aft for thrust reversal; andextending the fan nozzle aftwardly from the translating sleeve when moving the translating sleeve axially aft. 6. The method of claim 5 wherein the translating sleeve has a sleeve aft edge defining a tangency line, the method further comprising the step of: moving the fan nozzle along a direction parallel to the tangency line. 7. The method of claim 1 further comprising the step of: moving the fan nozzle to a predetermined position corresponding to an operating parameter of the gas turbine engine. 8. The method of claim 1 further comprising the step of: sliding the fan nozzle along a fan nozzle slider mechanism slidably connecting the fan nozzle to a cowl assembly. 9. A method of varying a fan duct throat area of a gas turbine engine having a longitudinal axis and a thrust reverser, the thrust reverser having movable blocker doors configured to block fan flow through the fan duct when the thrust reverser is activated, comprising the steps of: non-pivotably moving a fan nozzle radially outwardly along a direction diverging from the longitudinal axis while simultaneously translating the fan nozzle in an axially aft direction to vary the fan duct throat area; andmoving the fan nozzle without activating the thrust reverser.