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특허 상세정보

Gas turbine engine inlet with noise reduction features

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/02   
미국특허분류(USC) 060/226.1; 060/226.3; 060/262; 244/053.0B; 137/015.1
출원번호 UP-0588544 (2006-10-27)
등록번호 US-7739865 (2010-07-12)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds PC
인용정보 피인용 횟수 : 18  인용 특허 : 10
초록

A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the i...

대표
청구항

What is claimed is: 1. A gas turbine engine comprising: a fan nacelle that comprises an inner fan nacelle surface which defines an inlet duct; and a nacelle contoured surface disposed in said fan nacelle for selectively reducing an inlet area of said inlet duct to increase acoustic attenuation associated therewith, said nacelle contoured surface segmented around the circumference of said fan nacelle to selectively permit asymmetrical deployment thereof and selectively reduce the inlet area of the inlet duct asymmetrically. 2. The gas turbine engine o...

이 특허를 인용한 특허 피인용횟수: 18

  1. Lucas, Evan; Hastings, Sean. Compressor intake noise prevention by choking flow with duct geometry. USP2015119181961.
  2. Clark, Adam Wayne; Cedar, Richard David; Riddle, David Baker. Crosswind performance aircraft engine spinner. USP20190110167088.
  3. Turner, Matthew A.; Brown, Charles W.; Bugaj, Shari L.; Quinn, Christopher M.; Hyland, David J.; Alarcon, Andrew G.. Fairing assembly. USP2016029267386.
  4. Cloft, Thomas G.. Gas turbine engine assembly including accessory components within the nacelle. USP2014078769924.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  7. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  8. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  9. Suciu, Gabriel L.; Merry, Brian D.; Brilliant, Lisa I.. Integrated inlet vane and strut. USP2015069068460.
  10. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  11. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  12. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  13. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  14. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  15. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  16. Kling, Colin J.; McPhail, James J.; Rader, Matthew R.. Turbine engine nosecone with deformation region. USP2016059353685.
  17. Grip, Robert E.; Brown, John J.. Two-surface sandwich structure for accommodating in-plane expansion of one of the surfaces relative to the opposing surface. USP2017019555871.
  18. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.