[특허]Thrust reversers including support members for inhibiting deflection

The Boeing Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Thrust reversers including support members for inhibiting deflection

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/02 F02K-003/00
미국특허분류(USC)	060/226.2; 239/265.31; 244/110.B
출원번호	UP-0252444 (2005-10-18)
등록번호	US-7600371 (2009-10-28)
발명자 / 주소	Sternberger, Joe E.
출원인 / 주소	The Boeing Company
대리인 / 주소	Perkins Coie LLP
인용정보	피인용 횟수 : 14 인용 특허 : 59

초록
▼

Aircraft systems having thrust reversers with support members are disclosed herein. In one embodiment, an aircraft system includes a thrust reverser having a nozzle inner wall, a nozzle outer wall radially outward of the inner wall, and a blocker door carried by the outer wall. The blocker door is movable between a deployed position and a stowed position. The thrust reverser further includes a support member extending between a forward section of a nozzle inner wall and a forward section of the nozzle outer wall. The support member is positioned such tha...

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I claim: 1. An aircraft system, comprising a thrust reverser including: a nozzle inner wall; a nozzle outer wall radially outward of the nozzle inner wall, the nozzle outer wall including a blocker door movable between a deployed position and a stowed position; a fixed structure positioned radially outward of the nozzle outer wall; a link having a first end portion pivotally coupled to the fixed structure and a second end portion spaced apart from the first end portion; and a support member extending between the nozzle inner wall and the nozzle outer wall, wherein at least a portion of the support member is positioned forward of the blocker door when the blocker door is in the stowed position, wherein a first end portion of the support member is pivotally attached to the second end portion of the link, and wherein the first end portion of the support member is spaced radially inward from the fixed structure by a gap. 2. The aircraft system of claim 1, wherein the fixed structure is a first torque box, and wherein the aircraft system further comprises a second torque box positioned radially outward of at least a portion of the nozzle outer wall; wherein the nozzle inner wall further includes a first inner wall panel and a second inner wall panel opposite the first inner wall panel, the first and second inner wall panels each including an upper portion, a lower portion, and an arcuate portion extending between the upper and lower portions; wherein the support member is a first support member having a second end portion attached to the arcuate portion of the first inner wall panel; and wherein the aircraft system further comprises a second support member having a first end portion coupled to the second torque box and a second end portion attached to the arcuate portion of the second inner wall. 3. The aircraft system of claim 1 wherein: the nozzle inner wall further includes a first inner wall panel and a second inner wall panel opposite the first inner wall panel, the first and second inner wall panels each including an upper portion, a lower portion, and an arcuate portion extending between the upper and lower portions; and the support member includes a second end portion attached to the arcuate portion of the first or second inner wall panel. 4. The aircraft system of claim 1, wherein: the nozzle inner wall further includes a first inner wall panel and a second inner wall panel opposite the first inner wall panel, the first and second inner wall panels each including an upper portion, a lower portion, and an arcuate portion extending between the upper and lower portions; and the support member includes a second end portion attached to the arcuate portion of the first or second inner wall panel. 5. The aircraft system of claim 1 wherein: the nozzle inner wall further includes a first inner wall panel and a second inner wall panel opposite the first inner wall panel, the first and second inner wall panels each including an upper portion, a lower portion, and an arcuate portion extending between the upper and lower portions; the support member is a first support member; the aircraft system further comprises a second support member; and the first and second support members each include an end portion attached to the arcuate portion of the first inner wall panel. 6. The aircraft system of claim 1 wherein the fixed structure is a torque box. 7. The aircraft system of claim 1, further comprising a fan casing including an inner V-groove, wherein the thrust reverser further includes an inner V-blade proximate to the nozzle inner wall for engaging the inner V-groove, and wherein the support member is positioned to at least inhibit disengagement of the inner V-groove and the inner V-blade. 8. The aircraft system of claim 1 wherein the thrust reverser has a central axis, and wherein the support member is elongated along an axis that intersects the central axis. 9. The aircraft system of claim 1, further comprising an urging member operably coupled to the support member and positioned to urge the support member toward the nozzle inner wall. 10. The aircraft system of claim 1, further comprising: a wing coupled to the thrust reverser; a fuselage attached to the wing; and a tail coupled to the fuselage. 11. An aircraft system, comprising a cascade thrust reverser including: a first inner wall panel; a second inner wall panel opposite the first inner wall panel with a nozzle gas flow path located between the first and second inner wall panels; a nozzle outer wall radially outward of the first and second inner wall panels; a fixed structure radially outward of at least a portion of the nozzle outer wall; a link having a first end portion pivotally coupled to the fixed structure and a second end portion spaced apart from the first end portion; and a support member having a first end portion attached to the first or second inner wall panel and a second end portion pivotally attached to the second end portion of the link, wherein the first end portion of the support member is spaced radially inward from the fixed structure by a gap. 12. The aircraft system of claim 11 wherein: the first inner wall panel includes an upper portion, a lower portion, and an arcuate portion extending between the upper and lower portions; and the first end portion of the support member is attached to the arcuate portion of the first inner wall panel. 13. The aircraft system of claim 11 wherein: the fixed structure includes a torque box; the first inner wall panel includes an upper portion, a lower portion, and an arcuate portion extending between the upper and lower portions; and the first end portion of the support member is attached to the arcuate portion of the first inner wall panels. 14. The aircraft system of claim 11 wherein the fixed structure includes a torque box. 15. The aircraft system of claim 11 wherein the support member is a first support member attached to the first inner wall panel, and wherein the aircraft system further comprises a second support member extending between the first inner wall panel and the nozzle outer wall. 16. The aircraft system of claim 11 wherein: the first inner wall panel includes an upper portion, a lower portion, and an arcuate portion extending between the upper and lower portions; the support member is a first support member and the first end portion of the first support member is attached to the arcuate portion of the first inner wall panel; the fixed structure is a first fixed structure; and the aircraft system further comprises (a) a second fixed structure radially outward of at least a portion of the nozzle outer wall, and (b) a second support member having a first end portion attached to the second inner wall panel and a second end portion coupled to the second fixed structure. 17. The aircraft system of claim 11, further comprising a fan casing having an inner V-groove, wherein the thrust reverser further comprises an inner V-blade proximate to the first and second inner wall panels for engaging the inner V-groove, and wherein the support member inhibits disengagement of the inner V-groove and the inner V-blade. 18. An aircraft system, comprising: a fan casing including a first member; and a thrust reverser including a nozzle inner wall, a second member proximate to the nozzle inner wall for engaging the first member, a nozzle outer wall radially outward of the nozzle inner wall, a fixed structure positioned radially outward of the nozzle outer wall, and means for inhibiting disengagement of the first and second members, wherein the means for inhibiting comprise: a link having a first end portion pivotally coupled to the fixed structure and a second end portion spaced apart from the first end portion; and a support member extending between the nozzle inner wall and the nozzle outer wall, wherein the support member includes an end portion pivotally attached to the second end portion of the link, and wherein the first end portion of the support member is spaced radially inward from the fixed structure by a gap. 19. The aircraft system of claim 18 wherein the nozzle inner wall includes a forward section and the nozzle outer wall includes a forward section, and wherein the support member extends between the forward section of the nozzle inner wall and the forward section of the nozzle outer wall. 20. The aircraft system of claim 18 wherein the first member is an inner V groove and the second member is an inner V-blade. 21. The aircraft system of claim 18 wherein the means for inhibiting comprise a plurality of support members extending between the nozzle inner and outer walls. 22. The aircraft system of claim 18 wherein: the nozzle inner wall includes a first inner wall panel and a second inner wall panel opposite the first inner wall panel, the first and second inner wall panels each including an upper portion, a lower portion, and an arcuate portion extending between the upper and lower portions; and the support member extends between the nozzle outer wall and the arcuate portion of the first or second inner wall panel. 23. The aircraft system of claim 18 wherein: the fixed structure is a torque box; the nozzle inner wall includes a first inner wall panel and a second inner wall panel opposite the first inner wall panel, the first and second inner wall panels each including an upper portion, a lower portion, and an arcuate portion extending between the upper and lower portions; and the support member extends between the arcuate portion of the first inner wall panel and the torque box.

이 특허에 인용된 특허 (59)

이 특허를 인용한 특허 피인용횟수: 14

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Thrust reversers including support members for inhibiting deflection

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이 특허에 인용된 특허 (59)

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Thrust reversers including support members for inhibiting deflection

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이 특허에 인용된 특허 (59)

이 특허를 인용한 특허 피인용횟수: 14

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