Thrust reverser translating sleeve assembly
View Patent ↗A translating sleeve assembly for use with an aircraft engine thrust reverser broadly comprises a slider track, a lifting bolt, and a hinge. The slider track may include a tubular sidewall and a guide channel formed therein that follows a curved path along a length thereof. The lifting bolt may be slidably positioned within the slider track. The hinge may include a first hinge element with a base coupled to an outer cowl shroud, a second hinge element with a hinge rod slidably positioned within the guide channel, and a pin about which the first hinge element and the second hinge element pivot. During deployment of the thrust reverser, the lifting bolt slides aftward and the hinge rod slides within the guide channel, urging the lifting bolt to pivot and the hinge to open, thereby lifting the outer cowl shroud away from the center of the aircraft engine.
1. A translating sleeve assembly for use with an aircraft engine thrust reverser, the translating sleeve assembly comprising:
a slider track having a guide channel formed therein that follows a curved path along a length thereof;
a lifting bolt slidably positioned within the slider track; and
a hinge coupled to an outer cowl shroud, the hinge including a hinge rod slidably positioned within the guide channel and coupled to the lifting bolt,
wherein during deployment of the thrust reverser, the outer cowl shroud is pushed aftward such that the lifting bolt slides within the slider track and the hinge rod slides within the guide channel, urging the lifting bolt to pivot and the hinge to open, thereby lifting the outer cowl shroud away from the center of the aircraft engine.
2. The translating sleeve assembly of claim 1 , wherein the hinge includes
a first hinge element with a base coupled to the outer cowl shroud,
a second hinge element coupled to the hinge rod, and
a pin about which the first hinge element and the second hinge element pivot.
3. The translating sleeve assembly of claim 2 , wherein the first hinge element further includes a plurality of first fingers with first spaces in between and the second hinge element further includes a plurality of second fingers with second spaces in between, wherein the first fingers fit within the second spaces and the second fingers fit within the first spaces.
4. The translating sleeve assembly of claim 2 , wherein the hinge opens as the first hinge element and the second hinge element pivot about the hinge pin such that the first hinge element moves away from the lifting bolt.
5. The translating sleeve assembly of claim 1 , wherein the lifting bolt is generally cylindrical in shape with an outer diameter that is less than the inner diameter of the tubular sidewall.
6. A translating sleeve assembly for use with an aircraft engine thrust reverser, the translating sleeve assembly comprising:
a slider track having a guide channel formed therein that follows a curved path along a length thereof;
a lifting bolt slidably positioned within the slider track; and
a hinge including a first hinge element with a base coupled to an outer cowl shroud, a second hinge element with a hinge rod slidably positioned within the guide channel and coupled to the lifting bolt, and a pin about which the first hinge element and the second hinge element pivot,
wherein during deployment of the thrust reverser, the outer cowl shroud is pushed aftward such that the lifting bolt slides within the slider track and the hinge rod slides within the guide channel, urging the lifting bolt to pivot and the hinge to open, thereby lifting the outer cowl shroud away from the center of the aircraft engine.
7. The translating sleeve assembly of claim 6 , wherein the first hinge element further includes a plurality of first fingers with first spaces in between and the second hinge element further includes a plurality of second fingers with second spaces in between, wherein the first fingers fit within the second spaces and the second fingers fit within the first spaces.
8. The translating sleeve assembly of claim 6 , wherein the hinge opens as the first hinge element and the second hinge element pivot about the hinge pin such that the first hinge element moves away from the lifting bolt.
9. The translating sleeve assembly of claim 6 , wherein the lifting bolt is generally cylindrical in shape with an outer diameter that is less than the inner diameter of the tubular sidewall.
10. An aircraft engine thrust reverser comprising:
a left outer cowl shroud including a first inner surface, a first lower portion, and a first upper portion;
a right outer cowl shroud including a second inner surface, a second lower portion, and a second upper portion;
a first translating sleeve assembly including a first hinge coupled to the first upper portion of the first inner surface, the first hinge operable to open while translating aftward;
a second translating sleeve assembly including a second hinge coupled to the second upper portion of the second inner surface, the second hinge operable to open while translating aftward;
a third translating sleeve assembly including a third hinge coupled to the first lower portion of the first inner surface, the third hinge operable to open while translating aftward; and
a fourth translating sleeve assembly including a fourth hinge coupled to the second lower portion of the second inner surface, the fourth hinge operable to open while translating aftward,
wherein during deployment of the thrust reverser, the left outer cowl shroud is pushed aftward along with the first hinge and the third hinge, thereby opening the first hinge and the third hinge such that the left outer cowl shroud is lifted away from the center of the aircraft engine, and the right outer cowl shroud is pushed aftward along with the second hinge and the fourth hinge, thereby opening the second hinge and the fourth hinge such that the right outer cowl shroud is lifted away from the center of the aircraft engine.
11. The aircraft engine thrust reverser of claim 10 , further including—
an upper left support beam to which the first translating sleeve assembly is coupled;
an upper right support beam to which the second translating sleeve assembly is coupled;
a lower left support beam to which the third translating sleeve assembly is coupled; and
a lower right support beam to which the fourth translating sleeve assembly is coupled.
12. The aircraft engine thrust reverser of claim 10 , wherein each of the translating sleeve assemblies further includes—
a slider track having a guide channel formed therein that follows a curved path along a length thereof,
a lifting bolt slidably positioned within the slider track,
a first hinge element with a base coupled to the left outer cowl shroud or the right outer cowl shroud,
a second hinge element with a hinge rod slidably positioned within the guide channel and coupled to the lifting bolt, and
a pin about which the first hinge element and the second hinge element pivot,
wherein during deployment of the thrust reverser, the lifting bolt slides within the slider track and the hinge rod slides within the guide channel, urging the lifting bolt to pivot and the hinge to open.
13. The translating sleeve assembly of claim 12 , wherein the first hinge element further includes a plurality of first fingers with first spaces in between and the second hinge element further includes a plurality of second fingers with second spaces in between, wherein the first fingers fit within the second spaces and the second fingers fit within the first spaces.
14. The translating sleeve assembly of claim 12 , wherein the hinge opens as the first hinge element and the second hinge element pivot about the hinge pin such that the first hinge element moves away from the lifting bolt.
15. The translating sleeve assembly of claim 12 , wherein the lifting bolt is generally cylindrical in shape with an outer diameter that is less than the inner diameter of the tubular sidewall.