Thrust reverser interspatial blocker system

A thrust reverser system for a turbofan engine, the thrust reverser system comprising:

• a sleeve configured to translate with respect to a stationary portion of a fan nacelle from a deactivated position to an activated position;
• an actuation mechanism configured to extend between the stationary portion of the fan nacelle and the sleeve;
• and
• a plurality of discrete interspatial blockers circumferentially arrayed within the sleeve, each of the plurality of interspatial blockers including:
• a first flap configured to rotate from a first stored position, when the sleeve is in the deactivated position, to a first blocking position, when the sleeve is in the activated position;
• a second flap configured to rotate from a second stored position, when the sleeve is in the deactivated position, to a second blocking position, when the sleeve is in the activated position;
• and
• a leading-edge structure rotatably coupling the first flap to the second flap,
• wherein the leading-edge structure is mounted within the sleeve in a substantially radial orientation such that the first flap rotates in a first direction about a first axis extending in a substantially radial direction from the first stored position to the first blocking position, and such that the second flap rotates in a second direction about a second axis extending in the substantially radial direction from the second stored position to the second blocking position, wherein the first direction is opposite to the second direction, wherein the actuation mechanism is configured to move the first flap and the second flap from the first and second stored positions, respectively, to the first and second blocking positions, respectively, in mechanical reaction to translation of the sleeve, wherein, for each of the plurality of interspatial blockers, the actuation mechanism is a drag link configured to extend between the stationary portion of the fan nacelle and the sleeve.

A turbofan engine comprising:

• a core nacelle housing a turbofan core;
• and
• a cascading fan nacelle housing a fan operatively coupled to the turbofan core and a thrust reverser system,
• wherein the fan nacelle includes:
• a stationary portion;
• a translating portion;
• and
• a cascading portion,
• wherein the translating portion is configured to move from a deactivated position to an activated position, and
• wherein, when the translating portion is in the activated position, the cascading portion extends from the translating portion to the stationary portion providing an exit for airflow within the fan nacelle, and
• wherein the thrust reverser system includes:
• a plurality of discrete interspatial blockers circumferentially arrayed within the translating portion, each of the plurality of interspatial blockers including:
• a first flap configured to rotate from a first stored position, when the translating portion is in the deactivated position, to a first blocking position, when the translating portion is in the activated position;
• a second flap configured to rotate from a second stored position, when the translating portion is in the deactivated position, to a second blocking position, when the translating portion is in the activated position;
• and
• a leading-edge structure rotatably coupling the first flap to the second flap,
• wherein the leading-edge structure is mounted within the translating portion in a substantially radial orientation such that the first flap rotates in a first direction about a first axis extending in a substantially radial direction from the first stored position to the first blocking position, and such that the second flap rotates in a second direction about a second axis extending in the substantially radial direction from the second stored position to the second blocking position, wherein the first direction is opposite to the second direction, wherein, for each of the plurality of interspatial blockers, the first axis and the second axis are colinear.