$\require{mediawiki-texvc}$
  • 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

Crosswind performance aircraft engine spinner

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-005/02    B64D-033/02    F01D-025/24    F02C-007/04    B64C-011/14   
출원번호 US-0886262 (2015-10-19)
등록번호 US-10167088 (2019-01-01)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    General Electric Company
인용정보 피인용 횟수 : 0  인용 특허 : 12
초록

Aircraft gas turbine engine spinner includes conical forward spinner section extending aftwardly from spinner tip to a curved aft spinner section circumscribed about centerline axis, a spinner aspect ratio greater than about 1.8, and wherein spinner aspect ratio is an axial distance between spinner tip and spinner end divided by radial distance from axis to spinner end. Aspect ratio may be in a range of about 2.0-2.2 or about 2.2-2.8. Aft spinner section may be substantially tangential to platform leading edges of platforms of fan blades. Aft spinner sec...

대표
청구항

1. A spinner for mounting to a rotor of an aircraft gas turbine engine, the spinner comprising: a conical upstream or forward spinner section extending aftwardly from a spinner tip, the conical upstream or forward spinner section having a decreasing slope which transitions directly into a convex downstream or aft spinner section, the convex downstream or aft spinner section initially having a decreasing slope and subsequently having an increasing slope extending aftwardly to a spinner end which transitions directly into a leading edge of a fan blade plat...

이 특허에 인용된 특허 (12)

  1. Chanez, Philippe Gerard; Loheac, Pierre Philippe Marie. Air inlet for a turbofan engine. USP2010067735776.
  2. Chen-Yu J. Chou ; Gerald A. Pauley ; Yiping Xu. Composite spinner and method of making the same. USP2002036358014.
  3. Nicholas David J. (Derby GB2) Mortimer Tony F. (Derby GB2). Fan for a gas turbine engine air intake. USP1993075224833.
  4. Pool Francis C. (Duffield GB2). Gas turbine engine having an automatic ice shedding spinner. USP1983074393650.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  6. Prasad, Dilip; Feng, Jinzhang; Sabnis, Jayant S.. Gas turbine engine inlet with noise reduction features. USP2010067739865.
  7. Prasad, Dilip; Feng, Jinzhang; Sabnis, Jayant S.. Gas turbine engine inlet with noise reduction features. USP2012108286654.
  8. Nelson ; Michael E.. Gas turbine engine with anti-icing facility. USP1978124129984.
  9. Gilchrist Alan R. (Fairfield OH) Sullivan Thomas J. (Fairfield OH) Walker Roger C. (Middletown OH). Hybrid spinner nose configuration in a gas turbine engine having a bypass duct. USP1993025182906.
  10. Liston Laurence D. N. (Mason OH) Sepela Michael J. (Middletown OH). Inlet fan blade fragment containment shield. USP1993115259724.
  11. Stockman Norbert O. (Batavia OH) Yates David E. (Cincinnati OH) Crum Timothy S. (Fairfield OH). Nacelle inlet for an aircraft gas turbine engine. USP1991105058617.
  12. James Michael Forrester ; Joseph Timothy Stevenson ; Jeffrey Clayton Potter ; Sean Joel Corrigan. One piece spinner. USP2002076416280.