$\require{mediawiki-texvc}$
  • 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Aerodynamic feature for aft edge portions of thrust reverser lower bifurcation wall

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/72    F02K-001/56    F02K-001/78   
출원번호 US-0262220 (2014-04-25)
등록번호 US-9822733 (2017-11-21)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    O'Shea Getz P.C.
인용정보 피인용 횟수 : 0  인용 특허 : 14
초록

A thrust reverser of a propulsion system nacelle is provided. The thrust reverser includes a fixed structure, a translating structure, and an aerodynamic feature. The fixed structure includes an annular wall that partially defines an annular bypass airstream duct. The fixed structure is bifurcated into left and right side sections. The annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section. The translating structure is moveable relative to th...

대표
청구항

1. A thrust reverser of a propulsion system nacelle, the thrust reverser comprising: a fixed structure that includes an annular wall that partially defines an annular bypass airstream duct, wherein the fixed structure is bifurcated into left and right side sections, wherein the annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section;a translating structure that is moveable relative to the fixed structure, between a stowed position and a deploy...

이 특허에 인용된 특허 (14)

  1. Sternberger, Joe E.. Acoustic treated thrust reverser bullnose fairing assembly. USP2003056557799.
  2. Buchacher Daniel A. (Kirkland WA). Composite structure for thrust reverser torque box. USP1993085239822.
  3. Welch John M. ; Popp Thomas D. ; Wikstrom Robert F. ; Stratton Terry W. ; Kitt Brian R.. Engine nacelle acoustic panel with integral wedge fairings and an integral forward ring. USP2001016173807.
  4. Moorehead James R. (Bellevue WA). Nacelle assembly and mounting structures for a turbofan jet propulsion engine. USP1977084044973.
  5. Greiert, Alfred H.. Removable slider shoe for a translating sleeve used on a jet engine cowl and duct. USP1985094541673.
  6. Pauley Gerald A. (Hamilton OH). Reverser inner cowl with integral bifurcation walls and core cowl. USP1993105251435.
  7. Vauchel, Guy Bernard; Cazuc, Xavier. Side-opening jet engine nacelle. USP2015049004855.
  8. Naud Henry (Verrieres Le Buisson FRX). Structural cowlings of twin flow turbo jet engines. USP1987084683717.
  9. Lair, Jean-Pierre. Thrust reverser. USP2011118051639.
  10. Lair, Jean-Pierre; Weaver, Paul. Thrust reverser for a turbofan gas turbine engine. USP2012038127530.
  11. Standish Robert R.,FRX. Thrust reverser for high bypass fan engine. USP1999015863014.
  12. Geidel Helmjut-Arnd (Karlsfeld DEX) Enderle Heinrich (Grbenzell DEX) Rohra Alois (Munich DEX). Thrust reverser for turbofan engine. USP1991105054285.
  13. Standish Robert R.,FRX ; Laboure Bernard,FRX. Thrust reverser with adjustable section nozzle for aircraft jet engine. USP1998125853148.
  14. Cariola Roy E. ; Aten Michael R.. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser. USP1998095806302.