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특허 상세정보

Turbojet architecture with two fans at the front

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/065    F02K-003/00    F02K-003/072   
미국특허분류(USC) 060/226.1; 060/268; 415/068; 415/144; 415/213.1
출원번호 US-0041998 (2005-01-26)
등록번호 US-7412819 (2008-08-19)
우선권정보 FR-04 01336(2004-02-11)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Oblon, Spivak, McClelland, Maier & Neustadt, P.C.
인용정보 피인용 횟수 : 15  인용 특허 : 1
초록

A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interp...

대표
청구항

What is claimed is: 1. A three-spool by-pass turbojet with a high by-pass ratio, the turbojet having a front fan and a rear fan at the front of a first intermediate casing that presents a first outer structural grid in a by-pass air flow and a first inner structural grid in a main air flow, the fans having blades that extend radially outwards to a fan casing, which fan casing outwardly defines the by-pass air flow, the turbojet also having a low-pressure compressor for compressing air coming into a channel for the main air flow, said front fan and said ...

이 특허를 인용한 특허 피인용횟수: 15

  1. Gallet, Francois. Bypass engine with contrarotating turbine wheels including a reversing module. USP2014038667777.
  2. Bil, Eric Stephan; Charier, Gilles Alain Marie. Compressor comprising a plurality of cells reconstituting an annular volume of separation of flows in a turbine engine. USP2009117618232.
  3. Sheridan, William G.. Fan drive planetary gear system integrated carrier and torque frame. USP2015069068629.
  4. Davis, Todd A.; Reinhardt, Gregory E.; DiBenedetto, Enzo. Gas turbine engine architecture with low pressure compressor hub between high and low rotor thrust bearings. USP2017109784181.
  5. Merry, Brian D.; Suciu, Gabriel L.. Gas turbine engine shaft bearing arrangement. USP20181210145266.
  6. Merry, Brian D.; Suciu, Gabriel L.; Hasel, Karl L.. Gas turbine engine shaft bearing configuration. USP2015119194329.
  7. Merry, Brian D.; Suciu, Gabriel L.; Hasel, Karl L.. Gas turbine engine shaft bearing configuration. USP2014108863491.
  8. Merry, Brian D.; Suciu, Gabriel L.; Hasel, Karl L.. Gas turbine engine shaft bearing configuration. USP20190210215094.
  9. Kupratis, Daniel B.. Gas turbine engine with two-spool fan and variable vane turbine. USP2016039279388.
  10. Magowan, John W.. Geared fan with inner counter rotating compressor. USP20181110125694.
  11. Merry, Brian D.; Suciu, Gabriel L.; Brilliant, Lisa I.; Rose, Becky E.; Dong, Yuan; Balamucki, Stanley J.. LPC flowpath shape with gas turbine engine shaft bearing configuration. USP2015059038366.
  12. Sheridan, William G.; McCune, Michael E.. Turbofan engine bearing and gearbox arrangement. USP2018029885282.
  13. Sheridan, William G.; McCune, Michael E.. Turbofan engine bearing and gearbox arrangement. USP20181010113481.
  14. Sheridan, William G.; Schwarz, Frederick M.. Turbofan engine main bearing arrangement. USP2017089732629.
  15. Sheridan, William G.; Schwarz, Frederick M.. Turbofan engine main bearing arrangement. USP20180910066504.