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특허 상세정보

Low pressure ratio fan engine having a dimensional relationship between inlet and fan size

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-025/24    F01D-005/02    F01D-017/10    F01D-015/12    F02K-003/06    F01D-005/14    F02C-007/04   
출원번호 US-0721095 (2012-12-20)
등록번호 US-9920653 (2018-03-20)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds P.C.
인용정보 피인용 횟수 : 0  인용 특허 : 21
초록

According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and 0.45.

대표
청구항

1. A gas turbine engine assembly, comprising: a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, the fan being configured to deliver a portion of air into a compressor section and a portion of air into a bypass duct, wherein a bypass ratio is greater than 6, the bypass ratio being a ratio of a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section; andan inlet portion forward of the fan...

이 특허에 인용된 특허 (21)

  1. Manzi ; Jr. Robert J. ; Mathews Douglas C. ; Slomski Soter P. ; van Achterberg Johan. Acoustically improved gas turbine blade array. USP1999105966525.
  2. Surply, Thierry; Prat, Damien; Gagnaire, Benoit. Air inlet for commercial aircraft jet engine nacelle. USP2004036708711.
  3. McConachie James M. ; Curtin Margaret M. ; Dougherty Robert P. ; Sangwin Michael L.. Biplanar scarfed nacelle inlet. USP1999065915403.
  4. Eveker Kevin M. ; Gysling Daniel L. ; Nett Carl N. ; Wang Hua O.. Compressor stall and surge control using airflow asymmetry measurement. USP1999065915917.
  5. Morris John P. (Seattle WA) Podenski Patrick A. (Everett WA). Contracted inlet for jet engine being transported as cargo. USP1980064209149.
  6. Tse, Man-Chun; LeBlanc, Andr?. Fan and compressor noise attenuation. USP2005126973193.
  7. Hasel, Karl L.; Staubach, Joseph B.; Merry, Brian D.; Suciu, Gabriel L.; Dye, Christopher M.. Gas turbine engine compressor arrangement. USP2013058449247.
  8. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  9. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  10. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle. USP2013048418953.
  11. Kutney John T. (Cincinnati OH) Mishler Rodger B. (West Chester OH). Inlet noise deflector. USP1976033946830.
  12. Decker,John Jared; Szucs,Peter Nicholas; Solomon,William Joseph; Wilson,Virginia Louise. Low solidity turbofan. USP2008057374403.
  13. Stockman Norbert O. (Batavia OH) Yates David E. (Cincinnati OH) Crum Timothy S. (Fairfield OH). Nacelle inlet for an aircraft gas turbine engine. USP1991105058617.
  14. Harris Alfred W. (Bellevue WA). Noise reducing air inlet for gas turbine engines. USP1980124240250.
  15. Scoates William D. (Rte. 1 ; Box 930 Bryan TX 77803) Scoates Samuel W. (Rte. 1 ; Box 930 Bryan TX 77803). Shroud assembly for axial flow fans. USP1990054927328.
  16. Rowlands Paul A.,GBX. Swept fan blade. USP2000066071077.
  17. Spear David A. (Manchester CT) Biederman Bruce P. (Meriden CT) Orosa John A. (Palm Beach Gardens FL). Swept turbomachinery blade. USP1997075642985.
  18. Coplin John F. (Derby GB2). Turbofan gas turbine engine. USP1989054827712.
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  20. Suciu, Gabriel L.; Merry, Brian; Norris, James W.; Sirica, Steven J.. Variable fan inlet guide vane assembly for gas turbine engine. USP2011027882694.
  21. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.