Gas turbine engine with variable area fan nozzle
First Claim
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1. A nacelle assembly for a gas turbine engine comprising:
- a core nacelle defined about an engine centerline axis;
a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path;
a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan nozzle having a first fan nacelle section and a second fan nacelle section, said first fan nacelle section defines an intermittent trailing edge which defines a multiple of ports and said second fan nacelle section defines a multiple of doors, each of said multiple of doors match each of said multiple of ports such that a fan nacelle trailing edge is continuous when said second fan nacelle section is in a closed position relative to said first fan nacelle section; and
an actuator operable to move said variable area fan nozzle between the closed position and an open position, said actuator including an actuator input engaging a mating actuator receiver, at least one of said actuator input and said actuator receiver extending through an access slot in a circumferential fairing.
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Abstract
A nacelle assembly for a bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The variable area fan nozzle is in communication with a fan bypass flow path, the first fan nacelle section defines an intermittent trailing edge which defines a multiple of ports and the second fan nacelle section defines a multiple of doors, each of the multiple of doors match each of the multiple of ports such that a fan nacelle trailing edge is continuous when the second fan nacelle section is selectively translated to a closed position relative to the first fan nacelle section.
109 Citations
19 Claims
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1. A nacelle assembly for a gas turbine engine comprising:
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a core nacelle defined about an engine centerline axis; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path; a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan nozzle having a first fan nacelle section and a second fan nacelle section, said first fan nacelle section defines an intermittent trailing edge which defines a multiple of ports and said second fan nacelle section defines a multiple of doors, each of said multiple of doors match each of said multiple of ports such that a fan nacelle trailing edge is continuous when said second fan nacelle section is in a closed position relative to said first fan nacelle section; and an actuator operable to move said variable area fan nozzle between the closed position and an open position, said actuator including an actuator input engaging a mating actuator receiver, at least one of said actuator input and said actuator receiver extending through an access slot in a circumferential fairing. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A gas turbine engine comprising:
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a core engine defined about an axis; a turbofan mounted about said axis; a core nacelle defined at least partially about said core engine; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path; a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan nozzle having a first fan nacelle section and a second fan nacelle section, said first fan nacelle section defines an intermittent trailing edge which defines a multiple of ports and said second fan nacelle section defines a multiple of doors, each of said multiple of doors match each of said multiple of ports such that a fan nacelle trailing edge is continuous when said second fan nacelle section is selectively translated to a closed position relative to said fixed first fan nacelle section, said first fan nacelle section including a circumferential fairing having an access slot therein and said second fan nacelle section including a gear rack aligned with said access slot; and an actuator including a pinion gear meshing with said gear rack through said access slot, said actuator operable to translate said second fan nacelle section and move said multiple of doors relative to said multiple of ports. - View Dependent Claims (13, 14, 15, 16)
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17. A method of varying a nozzle of a gas turbine engine comprising:
using an actuator, selectively translating a second fan nacelle section that defines a multiple of doors relative a first fan nacelle section having a multiple of ports such that a fan nacelle trailing edge is continuous when the second fan nacelle section is at a closed position and is intermittent when at an open position, said actuator including an actuator input engaging a mating actuator receiver, at least one of said actuator input and said actuator receiver extending through an access slot in a circumferential fairing. - View Dependent Claims (18, 19)
Specification