• 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

Apparatus, method and system for gas turbine engine noise reduction

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/02    F02K-003/00   
미국특허분류(USC) 060/226.1; 060/204; 239/265.19
출원번호 US-0343566 (2001-10-02)
국제출원번호 PCT/US01/030862 (2001-10-02)
§371/§102 date 20030911 (20030911)
국제공개번호 WO02/029232 (2002-04-11)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Goodwin Procter LLP
인용정보 피인용 횟수 : 13  인용 특허 : 18

An apparatus for reducing gas turbine engine noise, such as noise generated by an aircraft gas turbine engine, comprises at least one and preferably a plurality of gas injectors for injecting gas such as high pressure engine bleed air, diverted core air, air obtained from a pressurized storage container or air obtained from a synthetic jet actuator into the area proximate to one or more engine nozzle portions, thereby disrupting the noise-generating gas streams generated by the engine exhaust and the travel of the airplane through the air. The apparatus ...


The invention claimed is: 1. An apparatus for reducing noise generated by an aircraft gas turbine engine having an engine core with a longitudinal centerline, a core nozzle having an exit plane and fan nozzle having an exit plane, wherein a fan air stream flows between the fan nozzle and the core nozzle and a core air stream flows between the core nozzle and the engine core when the aircraft is in flight, the apparatus comprises at least one gas injector for injecting gas into the fan air stream proximate to the fan nozzle exit plane toward the engine c...

이 특허에 인용된 특허 (18)

  1. Terrier Douglas A. (Fort Worth TX). After-burning turbo-fan engine with a fixed geometry exhaust nozzle having a variable flow coefficient. USP1997095664415.
  2. Lee, Douglas; Anderson, J. Thomas; Hershberger, Brian K.. Apparatus and method for controlling primary fluid flow using secondary fluid flow injection. USP2004016679048.
  3. Spring Samuel D. ; Carita Robert J. ; Stocking Herbert A.. Bay cooled turbine casing. USP2001056227800.
  4. Newton Arnold C,GBX. Ducted fan gas turbine engine with variable area fan duct nozzle. USP2000066070407.
  5. Lair, Jean-Pierre. Duplex mixer exhaust nozzle. USP2004096786038.
  6. Lidstone Gary L. ; Clark Larry T. ; Szupkay Imre A. ; Sandquist David L.. Engine noise suppression ejector nozzle. USP1999035884843.
  7. John Michael Koshoffer. Fluidic nozzle control system. USP2002016336319.
  8. Rudolph Peter K. C. (Seattle WA). Gas turbine mixer apparatus. USP1980084215536.
  9. Herbert Stephens Jones ; Joseph Paul Arves ; Darren Andrew Kearney ; Ryan Earl Roberts ; Rory Nell McLeod. Hybrid injection thrust vector control. USP2002106470669.
  10. Klees Garry W. (Mercer Island WA) Wright Charles P. (Seattle WA). Internally ventilated noise suppressor with large plug nozzle. USP1985024501393.
  11. Berman Charles H.. Jet engine noise suppressor assembly. USP1999095947412.
  12. Luffy Ronald J. (Maineville OH) Taylor ; Jr. John B. (Cincinnati OH) Sutherland William V. (Milford OH) Stine Frederick J. (Mainville OH) Crowley James A. (Midlothian VA) Mann David E. (West Chester . Method and apparatus for boosting ram airflow to an ejection nozzle. USP1995075435127.
  13. Zysman Steven H. ; Lord Wesley K. ; Barber Thomas J.. Method of noise suppression for a turbine engine. USP1998075775095.
  14. Glezer Ari ; Smith Barton L. ; Trautman Mark A.. Modifications of fluid flow about bodies and surfaces with synthetic jet actuators. USP1999095957413.
  15. Liang George P. ; Soileau John F.. Multi-expansion ejector nozzle with diverging walls. USP2000126164059.
  16. Glezer Ari ; Allen Mark G. ; Coe David J. ; Smith Barton L. ; Trautman Mark A. ; Wiltse John W.. Synthetic jet actuator and applications thereof. USP1998065758823.
  17. Glezer Ari ; Wiltse John W.. Synthetic jet actuators for mixing applications. USP2000056056204.
  18. Thayer Edward B.. Vectoring nozzle using injected high pressure air. USP1998015706650.

이 특허를 인용한 특허 피인용횟수: 13

  1. Huber, Jerome; Bonnet, Jean Paul; Gomes, Luis; Maury, Remy. Aircraft jet engine comprising a system for reducing the noise generated by the ejection of the gases. USP2015109151244.
  2. Beutin, Bruno Albert; Derenes, Jacky Raphael Michel; Eichstadt, Frederic Paul; Vuillemin, Alexandre Alfred Gaston. Bypass turbomachine with reduction of jet noise. USP2011108037687.
  3. Siden, Gunnar Leif; Ingram, Clint L.. Combustor mixing joint with flow disruption surface. USP20180710030872.
  4. Huber, Jerome; Bonnet, Jean-Paul; Delville, Joel; Jordan, Peter; Strekowski, Francois. Device for reducing noise generated by an aircraft jet engine with curve ducts. USP2012048157050.
  5. Huber, Jerome; Bonnet, Jean-Paul; Delville, Joel; Jordan, Peter; Strekowski, Francois. Device with plane jets for reducing the noise generated by an aircraft engine. USP2012038132756.
  6. Kupratis, Daniel B.. Gas turbine engine having core auxiliary duct passage. USP2013028371806.
  7. Ullman, Alan Z.. Method and apparatus for controlling flow about a turret. USP2014108870122.
  8. Gutmark,Ephraim Jeff; Callender,Bryan W.; Martens,Steven. Method and apparatus for operating gas turbine engines. USP2008087412832.
  9. Oishi, Tsutomu; Oba, Yoshinori. Noise reducing device and jet propulsion system. USP2014128904795.
  10. Tanaka, Nozomi; Kusuda, Shinya; Oishi, Tsutomu; Oba, Yoshinori. Noise reduction system with chamber. USP2014088813907.
  11. Schwark, Fred W.. Nozzle extension assembly for ground and flight testing. USP2010077762086.
  12. McMahan, Kevin Weston; Schott, Carl Gerard; Ingram, Clint Luigie; Siden, Gunnar Leif; Pierre, Sylvain. Transition duct assembly with modified trailing edge in turbine system. USP2016109458732.
  13. Thomas, Russell H.; Kinzie, Kevin W.. Wet active chevron nozzle for controllable jet noise reduction. USP2011098015819.