Dual actuation system for cascade and thrust reverser panel for an integral cascade variable area fan nozzle
A cascade-variable area fan nozzle system (the “CVAFN System”) is provided. The CVAFN system may comprise a cascade portion and a variable area fan nozzle (“VAFN”) portion. The VAFN portion may include a VAFN panel. The cascade and VAFN panel may be integrally formed with one another. The CVAFN system may include an actuation system (e.g., a jack screw) that is configured to translate the cascade and VAFN panel forward and aft. The cascade and VAFN panel may be translated aft in response to activation of the thrust reverser and/or CVAFN system.
1. A variable area fan nozzle (“VAFN”) system, comprising:
a cascade;
a translating sleeve circumferentially covering the cascade;
a VAFN panel coupled to the cascade;
a first actuation system comprising a scissor jack, the scissor jack coupled to the cascade and configured to translate the cascade, the translating sleeve and VAFN panel forward and aft;
a second actuation system comprising a jack screw, the jack screw configured to translate the translating sleeve.
2. The VAFN system of claim 1 , wherein the VAFN panel defines a port through a portion of the VAFN panel.
3. The VAFN system of claim 2 , wherein the port is configured to exhaust air radially outward.
4. The VAFN system of claim 1 , wherein the cascade and the VAFN panel are in a stowed position in a cruise configuration.
5. The VAFN system of claim 1 , wherein the cascade and the VAFN panel are in a deployed condition in response to at least one of a thrust reverser being activated and the VAFN system being activated.
6. The VAFN system of claim 1 , wherein the cascade includes a catch.
7. The VAFN system of claim 6 , wherein the catch is configured to engage a torque box of a nacelle in response to at least one of a thrust reverser being activated and the VAFN system being activated.
8. A nacelle, comprising:
a first hemisphere comprising:
a torque box;
a first actuation system, comprising a scissor jack, the scissor jack coupled to the torque box and configured to translate a cascade;
a translating sleeve comprising an outer portion and an inner portion, the translating sleeve coupled to a second actuation system;
the cascade disposed between the outer portion and the inner portion;
a variable area fan nozzle (“VAFN”) panel integrally formed to the cascade; and
the second actuation system, comprising a jack screw, the jack screw coupled to the torque box and the translating sleeve, the second actuation system configured to translate the translating sleeve forward and aft.
9. The nacelle of claim 8 , wherein the VAFN panel is configured with a radial exhaust port.
10. The nacelle of claim 9 , wherein the inner portion defines a flow surface that aligns with the radial exhaust port in response to the VAFN panel being actuated aft.
11. The nacelle of claim 9 , wherein the radial exhaust port is configured to cause an increase in the effective exhaust area of a bypass duct of the nacelle.