Thrust reverser interspatial blocker system
An interspatial blocker for a thrust reverser system of a turbofan engine, and a thrust reverser system and a turbofan engine incorporating the same. The interspatial blocker includes a first and second flap that rotate from a stored position to a blocking position, and a leading-edge structure rotatably coupling the first flap to the second flap. The leading-edge structure is set up to be installed in a fan nacelle of a turbofan engine 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 stored position to the 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 stored position to the blocking position, with the first direction being opposite to the second direction.
1. An interspatial blocker for a thrust reverser system of a turbofan engine, the interspatial blocker comprising:
a first flap configured to rotate from a first stored position to a first blocking position;
a second flap configured to rotate from a second stored position to a second blocking position; and
a leading-edge structure rotatably coupling the first flap to the second flap,
wherein the leading-edge structure is configured to be installed in a fan nacelle 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 first axis and the second axis are colinear.
2. The interspatial blocker of claim 1 , wherein, when the first flap is in the first blocking position and the second flap is in the second blocking position, the first flap and the second flap are configured to direct air out of cascades of the fan nacelle.
3. The interspatial blocker of claim 1 further comprising a fairing disposed between the first flap and the second flap, wherein, when the first flap is the first stored position and the second flap is in the second stored position, a portion of each of the first flap and the second flap abuts the fairing.
4. The interspatial blocker of claim 1 further comprising an actuation mechanism 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.
5. The interspatial blocker of claim 4 , wherein the actuation mechanism is a drag link configured to extend between a stationary portion of the fan nacelle and a translating portion of the fan nacelle.
6. 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.
7. The thrust reverser system of claim 6 , wherein, for each of the plurality of interspatial blockers, the first axis and the second axis are colinear.
8. The thrust reverser system of claim 6 , wherein, for each of the plurality of interspatial blockers, when the first flap is the first blocking position and the second flap is in the second blocking position, the first flap and the second flap are configured to direct air out of cascades of the fan nacelle.
9. The thrust reverser system of claim 6 , wherein each of the plurality of interspatial blockers further includes a fairing disposed between the first flap and the second flap, wherein, when the first flap is the first stored position and the second flap is in the second stored position, a portion of each of the first flap and the second flap abuts the fairing.
10. The thrust reverser system of claim 6 , wherein the plurality of interspatial blockers are configured to be installed in an annular passage defined by an outer flow surface on the sleeve and an inner flow surface on a core of the turbofan engine, and wherein, when the sleeve is in the activated position, neighboring pairs of the first and second flaps of neighboring interspatial blockers of the plurality of interspatial blockers are configured to abut one another thereby restricting airflow through a majority of the annular passage.
11. 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.
12. The turbofan engine of claim 11 , wherein, for each of the plurality of interspatial blockers, when the first flap is in the first blocking position and the second flap is in the second blocking position, the first flap and the second flap are configured to direct air out of the cascading portion.
13. The turbofan engine of claim 11 , wherein each of the plurality of interspatial blockers further includes a fairing disposed between the first flap and the second flap, wherein, when the first flap is in the first stored position and the second flap is in the second stored position, a portion of each of the first flap and the second flap abuts the fairing.
14. The turbofan engine of claim 11 , wherein each of the plurality of interspatial blockers further includes an actuation mechanism 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.
15. The turbofan engine of claim 14 , wherein, for each of the plurality of interspatial blockers, the actuation mechanism is a drag link configured to extend between the stationary portion and the translating portion.
16. The turbofan engine of claim 11 , wherein the plurality of interspatial blockers are disposed in an annular passage defined by an outer flow surface on the translating portion and an inner flow surface on the core nacelle, and wherein, when the translating portion is in the activated position, neighboring pairs of the first and second flaps of neighboring interspatial blockers of the plurality of interspatial blockers are configured to abut one another thereby restricting airflow through a majority of the annular passage.