Thrust reverser configuration for a short fan duct
View Patent ↗A thrust reverser comprises a translating sleeve, a torque beam, a plurality of cascades, a plurality of blocker doors, and a plurality of actuators. The translating sleeve is positioned at the rear of an aircraft nacelle and is translated rearward during thrust reverser deployment. The torque beam is positioned within the nacelle and configured to prevent airflow into the nacelle during thrust reverser deployment. The plurality of cascades are positioned around the circumference of the torque beam during thrust reverser stowage and are translated rearward during thrust reverser deployment. The plurality of blocker doors are positioned in alignment with the plurality of cascades and direct airflow through the plurality of cascades during thrust reverser deployment. The plurality of actuators are coupled to the forward edge of the sleeve and configured to translate the sleeve rearward during thrust reverser deployment.
1. A thrust reverser for use with an aircraft nacelle, the thrust reverser comprising:
a sleeve positioned at a rear of the aircraft nacelle and configured to translate rearward during thrust reverser deployment;
a fan ramp positioned within the aircraft nacelle including an arcuate outward flare configured to provide an aerodynamic path to the airflow during thrust reverser deployment;
a torque beam positioned within the aircraft nacelle including a radial ring extending inward from a fan cowl and a circumferential outer band axially extending from the radial ring to form a cavity between the circumferential outer band and the fan cowl and the torque beam configured to limit airflow into the aircraft nacelle during thrust reverser deployment;
a plurality of cascades positioned radially outward of the circumferential outer band around the circumference of the torque beam during thrust reverser stowage and configured to translate from the cavity to direct air flow forward during thrust reverser deployment; and
a plurality of blocker doors positioned in alignment with the plurality of cascades and configured to direct airflow through the plurality of cascades during thrust reverser deployment.
2. The thrust reverser of claim 1 , wherein the plurality of cascades are coupled to the sleeve and translate rearward during thrust reverser deployment.
3. The thrust reverser of claim 1 , wherein the plurality of cascades cover a gap formed between the sleeve and a fixed portion of the aircraft nacelle during thrust reverser deployment.
4. The thrust reverser of claim 1 , wherein the plurality of blocker doors lie flat against an inner surface of the sleeve during thrust reverser stowage and are pulled inward to contact an aircraft engine during thrust reverser deployment.
5. The thrust reverser of claim 1 , further including a plurality of actuators that couple to the forward edge of the sleeve and are configured to translate the sleeve rearward during thrust reverser deployment.
6. The thrust reverser of claim 5 , wherein each actuator includes a drive element coupled to the forward edge of the torque beam, an arm that extends the length of the torque beam, and a rod that is coupled to the forward edge of the sleeve.
7. The thrust reverser of claim 1 , further including a plurality of blocker door drag links that couple the plurality of blocker doors to the exterior surface of an aircraft engine and pull the blocker doors inward during thrust reverser deployment.
8. The thrust reverser of claim 1 , wherein the circumferential outer band includes a multicell internal structure.
9. A thrust reverser for use with an aircraft nacelle, the thrust reverser comprising:
a sleeve positioned at a rear of the aircraft nacelle and configured to translate rearward during thrust reverser deployment;
a plurality of actuators coupled to the forward edge of the sleeve and configured to translate the sleeve rearward during thrust reverser deployment;
a fan ramp positioned within the aircraft nacelle including an arcuate outward flare configured to provide an aerodynamic path to the airflow during thrust reverser deployment;
a torque beam positioned within the aircraft nacelle and including a radial ring extending inward from a fan cowl and a circumferential outer band axially extending from the radial ring to form a cavity between the circumferential outer band and the fan cowl, the torque beam configured to limit airflow into the aircraft nacelle during thrust reverser deployment;
a plurality of cascades positioned radially outward of the circumferential outer band and configured to translate from the cavity to direct air flow forward during thrust reverser deployment; and
a plurality of blocker doors positioned in alignment with the plurality of cascades and configured to direct airflow through the plurality of cascades during thrust reverser deployment.
10. The thrust reverser of claim 9 , wherein each actuator includes a drive element coupled to the forward edge of the torque beam, an arm that extends the length of the torque beam, and a rod that is coupled to the forward edge of the sleeve.
11. The thrust reverser of claim 9 , further including a plurality of blocker door drag links that couple the plurality of blocker doors to the exterior surface of an aircraft engine and pull the blocker doors inward during thrust reverser deployment.
12. The thrust reverser of claim 9 , wherein the plurality of cascades are coupled to the sleeve and translate rearward during thrust reverser deployment.
13. The thrust reverser of claim 9 , wherein the plurality of cascades cover a gap formed between the sleeve and a fixed portion of the aircraft nacelle during thrust reverser deployment.
14. The thrust reverser of claim 9 , wherein the plurality of blocker doors lie flat against an inner surface of the sleeve during thrust reverser stowage and are pulled inward to contact an aircraft engine during thrust reverser deployment.
15. The thrust reverser of claim 9 , wherein the circumferential outer band includes a multicell internal structure.
16. An aircraft nacelle comprising:
a fan case arcuate in shape and positioned to surround an aircraft engine intake fan;
a fan cowl arcuate in shape and positioned to surround the fan case, the fan cowl presenting an outer surface;
a support structure positioned within a portion of the circumference of the fan cowl and coupled to the fan cowl; and
a thrust reverser, including
a sleeve positioned to a rear of the fan cowl and including an outer surface that aligns with the outer surface of the fan cowl, the sleeve configured to translate rearward during thrust reverser deployment,
a torque beam positioned between the fan cowl and the fan case, including a radial ring extending inward from the fan cowl and a circumferential outer band axially extending from the radial ring to form a cavity between the circumferential outer band and the fan cowl and the torque beam configured to limit airflow into the aircraft nacelle during thrust reverser deployment,
a plurality of cascades positioned radially outward of the circumferential outer band during thrust reverser stowage and configured to translate from the cavity to direct air flow forward during thrust reverser deployment,
an outwardly flaring fan ramp positioned radially inward and rearward from the torque beam and configured to provide an aerodynamic path to the airflow through the plurality of cascades during thrust reverser deployment, and
a plurality of blocker doors positioned in alignment with the plurality of cascades and configured to direct airflow through the plurality of cascades during thrust reverser deployment.
17. The aircraft nacelle of claim 16 , wherein the plurality of cascades are coupled to the sleeve and translate rearward during thrust reverser deployment.
18. The aircraft nacelle of claim 16 , wherein the plurality of cascades cover a gap formed between the sleeve and a fixed portion of the aircraft nacelle during thrust reverser deployment.
19. The aircraft nacelle of claim 16 , wherein the plurality of blocker doors lie flat against an inner surface of the sleeve during thrust reverser stowage and are pulled inward to contact an aircraft engine during thrust reverser deployment.
20. The aircraft nacelle of claim 16 , further including a plurality of actuators that couple to the forward edge of the sleeve and are configured to translate the sleeve rearward during thrust reverser deployment.
21. The aircraft nacelle of claim 20 , wherein each actuator includes a drive element coupled to the forward edge of the torque beam, an arm that extends the length of the torque beam, and a rod that is coupled to the forward edge of the sleeve.
22. The aircraft nacelle of claim 16 , further including a plurality of blocker door drag links that couple the plurality of blocker doors to the exterior surface of an aircraft engine and pull the blocker doors inward during thrust reverser deployment.
23. An assembly for a thrust reverser for use with an aircraft nacelle, the assembly comprising:
a sleeve positioned at a rear of the aircraft nacelle and configured to translate rearward during thrust reverser deployment; and
a fan ramp positioned within the aircraft nacelle including an arcuate outward flare configured to provide an aerodynamic path to the airflow during thrust reverser deployment;
a torque beam positioned forward of the fan ramp within the aircraft nacelle including a radial ring extending inward from the fan cowl and a circumferential outer band axially extending from the radial ring to form a cavity between the circumferential outer band and a fan cowl and the torque beam configured to limit airflow into the aircraft nacelle during thrust reverser deployment; and
a plurality of cascades positioned radially outward of the circumferential outer band during thrust reverser stowage and configured to translate from the cavity to direct air flow forward during thrust reverser deployment.
24. The assembly of claim 23 , further including
a plurality of blocker doors positioned in alignment with the plurality of cascades and configured to direct airflow through the plurality of cascades during thrust reverser deployment.