Gas turbine engine having variable flow through a bifurcation having an intake with multiple louvers
A turbofan engine pylon structure has a fan variable area nozzle defined by a variable area flow system between a pylon intake and a pylon exhaust to selectively adjust a bypass flow through the pylon structure. The variable area flow system changes the physical area and geometry of a pylon nozzle exit area to manipulate the bypass flow by opening and closing an additional flow area of the variable area flow system.
1. A method of varying flow through a pylon nozzle exit area of a gas turbine engine comprising the steps of:
(A) varying a variable area flow system in communication with a flow passage through an engine nacelle pylon to change a volume of bypass flow through the engine nacelle pylon and control flow through a pylon nozzle exit area in response to a flight condition, said variable area flow system movable toward an open position to increase flow through said pylon nozzle exit area and toward a closed position to decrease flow through said pylon nozzle exit area
(B) having at least one bifurcation that has a variable pylon intake and a variable pylon exhaust, wherein said variable pylon intake comprises a plurality of turning vanes having variable heights relative to each other; and
(C) forming the flow passage as an internal passage within a body of the bifurcation, with the internal passage extending from the variable pylon intake to the variable pylon exhaust.
2. A method as recited in claim 1 , wherein said step (A) further comprises: opening the variable area flow system in response to a non-cruise flight condition.
3. A method as recited in claim 1 , wherein said step (A) further comprises: (a) opening the variable area flow system in response to a non-cruise flight condition.
4. A method as recited in claim 1 , including associating a first actuator with the variable pylon intake, associating a second actuator with the variable pylon exhaust, and independently controlling the first and second actuators.
5. A method as recited in claim 1 , wherein the body of the bifurcation includes at least one internal component duct comprising a communication path for connecting core engine components and wing components, and including forming the flow passage within the body of the bifurcation and around at least a portion of the internal component duct.
6. A nacelle assembly for a gas turbine engine comprising:
a core nacelle defined about an axis;
a fan nacelle mounted at least partially around said core nacelle; and
a pylon mounted to said core nacelle and said fan nacelle, said pylon having a variable area flow system comprising a variable intake and a variable exhaust; said variable intake comprising an adjustable system with multiple louvers; said variable area flow system in communication with a flow passage to control a volume of bypass flow through said pylon and vary flow through a pylon nozzle exit area, said variable area flow system movable toward an open position to increase flow through said pylon nozzle exit area and toward a closed position to decrease flow through said pylon nozzle exit area.
7. The assembly as recited in claim 6 , wherein said pylon includes an upper bifurcation.
8. The assembly as recited in claim 6 , wherein said pylon includes a lower bifurcation.
9. The assembly as recited in claim 6 , wherein said variable area flow system is closed to define a cruise position flow through a fan nozzle exit area.
10. The assembly as recited in claim 6 , wherein said flow passage passes through said pylon, said flow passage operable to increase a volume of bypass flow in response to said variable area flow system being in an open position.
11. The assembly as recited in claim 6 , wherein said pylon includes at least one bifurcation that includes said variable intake and said variable exhaust with said flow passage comprising an internal passage that is formed within a body of said bifurcation to extend from said variable intake to said variable exhaust.
12. The assembly as recited in claim 11 , wherein said variable intake and said variable exhaust are configured to be independently controlled of each other.
13. The assembly as recited in claim 11 , including a first actuator associated with said variable intake and a second actuator associated with said variable exhaust, said first and second actuators being independently controlled by a controller.
14. The assembly as recited in claim 11 , wherein said multiple louvers have variable heights.
15. The assembly as recited in claim 11 , wherein said body of said bifurcation includes at least one internal component duct comprising a communication path for connecting core components and wing components, and wherein said flow passage is formed within said body of said bifurcation and is defined at least partially around said internal component duct.
16. A gas turbine engine comprising:
a core engine defined about an axis;
a gear system driven by said core engine;
a turbofan driven by said gear system 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; and a pylon mounted to said core nacelle and said fan nacelle, said pylon having a variable area flow system comprising a variable intake and a variable exhaust; said variable intake comprising an adjustable system with multiple louvers; said variable area flow system in communication with a flow passage to control a volume of bypass flow through said pylon and vary flow through a pylon nozzle exit area, said variable area flow system is movable toward an open position to increase flow through said pylon nozzle exit area and is movable toward a closed position to decrease flow through said pylon nozzle exit area.
17. The engine as recited in claim 16 , further comprising a controller in communication with said variable intake and said variable exhaust to control said bypass flow in response to a flight condition.
18. The engine as recited in claim 17 , wherein said controller is in communication with said variable area flow system to control said volume of bypass flow in response to a flight condition such that an angle of attack of said turbo fan is maintained generally at a design incidence.
19. The engine as recited in claim 16 , wherein said pylon includes at least one bifurcation that includes said variable intake and said variable exhaust with said flow passage comprising an internal passage that is formed within a body of said bifurcation to extend from said variable intake to said variable exhaust.
20. The engine as recited in claim 19 , including a first actuator associated with said variable intake and a second actuator associated with said variable exhaust, said first and second actuators being independently controlled by a controller.
21. The engine as recited in claim 19 , wherein said adjustable system with multiple louvers comprises a plurality of turning vanes having variable heights relative to each other.
22. The engine as recited in claim 19 , wherein said body of said bifurcation includes at least one internal component duct comprising a communication path for connecting core engine components and wing components, and wherein said flow passage is formed within said body of said bifurcation and is defined at least partially around said internal component duct.