[특허]Fan case thrust reverser

United Technologies Corporation

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Fan case thrust reverser

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-001/72 F02K-001/70 F02K-001/12
미국특허분류(USC)	060/226.2;
출원번호	US-0234213 (2011-09-16)
등록번호	US-9038367 (2015-05-26)
발명자 / 주소	Suciu, Gabriel L. Merry, Brian D. Penda, Allan R. Dye, Christopher M. Bhatt, Jay
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 1 인용 특허 : 39

초록

A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis, a thrust reverser cascade section downstream of the blade containment section and a Fan Exit Guide Vane section downstream of the thrust reverser cascade section.

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1. A fan case of a gas turbine engine comprising: a fan blade containment section defined about anengine axis;a thrust reverser cascade section downstream of said blade containment section, said thrust reverser cascade section including an array of cascade airfoils and a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a helix; anda Fan Exit Guide Vane section downstream of said thrust reverser cascade section. 2. The fan case as recited in claim 1, wherein said fan blade containment section includes an abradable layer. 3. The fan case as recited in claim 1, wherein said thrust reverser cascade section includes a multiple of ribs which support a multiple of cascade airfoils. 4. A fan section of a gas turbine engine comprising: a fan case defined about an engine axis;a multiple of Fan Exit Guide Vanes attached to said fan case; anda thrust reverser cascade section upstream of said multiple of Fan Exit Guide Vanes, said thrust reverser cascade section including an array of cascade airfoils arranged among a plurality of ribs that are in a helix arrangement and a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a helix. 5. The fan section as recited in claim 4, wherein at least one of said multiple of Fan Exit Guide Vanes supports a fan blocker door. 6. The fan section as recited in claim 4, wherein each of said multiple of Fan Exit Guide Vanes supports a fan blocker door. 7. The fan section as recited in claim 4, further comprising a plurality of outer thrust reverser doors radially outwards of said array of cascade airfoils, wherein said plurality of outer thrust reverser doors axially slide generally parallel to said engine axis. 8. A gas turbine engine comprising: a fan case defined about an engine axis;a core case defined about said engine axis;a multiple of Fan Exit Guide Vanes attached to said fan case and said core case;a thrust reverser cascade section upstream of said multiple of Fan Exit Guide Vanes, said thrust reverser cascade section including an array of cascade airfoils, a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a helix, and said array of cascade airfoils being arranged among a plurality of ribs that are in a helix arrangement. 9. The gas turbine engine as recited in claim 8, further comprising a fan nacelle mounted to said fan case, said fan nacelle at least partially defined by a multiple of outer thrust reverser doors. 10. The gas turbine engine as recited in claim 8, further comprising a multiple of outer thrust reverser doors that axially slide generally parallel to said engine axis. 11. The gas turbine engine as recited in claim 8, further comprising a multiple of outer thrust reverser doors that hinge about an outer door axis generally parallel to said engine axis. 12. The fan case as recited in claim 1, wherein said inner thrust reverser doors are pivotable about respective inner door axes that are inclined to said engine axis. 13. The fan case as recited in claim 12, wherein said array of cascade airfoils is arranged with respect to a plurality of cascade ribs that are also arranged in a helix. 14. The fan case as recited in claim 13, further comprising a plurality of outer thrust reverser doors radially outwards of said array of cascade airfoils. 15. The fan case as recited in claim 14, wherein said plurality of outer thrust reverser doors are pivotable about respective outer door axes that are substantially parallel to the engine axis. 16. The fan case as recited in claim 14, wherein said plurality of outer thrust reverser doors are passively deployable in response to a thrust reverse airflow. 17. The fan case as recited in claim 16, wherein said plurality of outer thrust reverser doors are biased toward a closed position in absence of the thrust reverse airflow. 18. The fan section as recited in claim 4, wherein the plurality of inner thrust reverser doors are pivotable about respective inner door axes that are inclined to said engine axis. 19. The fan section as recited in claim 18, further comprising a plurality of outer thrust reverser doors radially outwards of said array of cascade airfoils, wherein said plurality of outer thrust reverser doors are pivotable about respective outer door axes that are substantially parallel to the engine axis. 20. The fan section as recited in claim 19, wherein said plurality of outer thrust reverser doors are passively deployable in response to a thrust reverse airflow.

이 특허에 인용된 특허 (39)

이 특허를 인용한 특허 피인용횟수: 1

Nestico, Brian Francis; Cox, Melanie Zoe; Gabel, Martin Kenneth; Blodgett, Keith Edward James. System and method of operating a ducted fan propulsion system inflight. USP20181110119495.

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Fan case thrust reverser

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Fan case thrust reverser

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이 특허에 인용된 특허 (39)

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