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특허 상세정보

System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-023/06    B64C-007/02   
미국특허분류(USC) 244/053.B; 244/001.N
출원번호 US-0064884 (2002-08-27)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Clark, Penny A.Patnode, Patrick K.
인용정보 피인용 횟수 : 29  인용 특허 : 16
초록

An active effective flow-through area control system includes an upstream wall-flow perturber and a downstream wall-flow perturber situated in an inlet region of an aircraft engine. The downstream wall-flow perturber is positioned downstream from the upstream wall-flow perturber. The upstream and downstream wall-flow perturbers are configured to generate and trap at least one region of separated, vortical flow in the airflow through the inlet region. A method, for actively changing an effective flow-through area of an inlet region of an aircraft engine, ...

대표
청구항

An active effective flow-through area control system includes an upstream wall-flow perturber and a downstream wall-flow perturber situated in an inlet region of an aircraft engine. The downstream wall-flow perturber is positioned downstream from the upstream wall-flow perturber. The upstream and downstream wall-flow perturbers are configured to generate and trap at least one region of separated, vortical flow in the airflow through the inlet region. A method, for actively changing an effective flow-through area of an inlet region of an aircraft engine, ...

이 특허에 인용된 특허 (16)

  1. Gliebe Philip R. (Waynesville OH). Active low noise fan assembly. USP1995125478199.
  2. Smith David M. ; Dorris ; III John. Aircraft engine apparatus with reduced inlet vortex. USP2000106129309.
  3. Davison Samuel H. (Milford OH). Aircraft engine starter integrated boundary bleed system. USP1992085136837.
  4. Sanders Bobby W. ; Weir Lois J.. Axi-symmetric mixed compression inlet with variable geometry centerbody. USP2001086276632.
  5. Haas Jan T. (Hamburg DEX) Hadwin Robin-Leslie (Buxtehude DEX). Controllable diffuser for an air intake of an aircraft. USP1987024641678.
  6. John Michael Koshoffer. Fluidic nozzle control system. USP2002016336319.
  7. Bouchez Marc,FRX ; Saunier Emmanuel,FRX. Fuel injection device for a ramjet operating at a high mach number. USP1999055899061.
  8. Burrus David L. (Cincinnati OH). High inlet mach combustor for gas turbine engine. USP1997045619855.
  9. Scavo Steven. Integrated fluidic CD nozzle for gas turbine engine. USP2000026021637.
  10. Smith Brian R. ; Miller Daniel N. ; Yagle Patrick J. ; Bender Erich E. ; Ginn Kerry B.. Method and system of pulsed or unsteady ejector. USP2001106308740.
  11. Papamoschou Dimitri. Method of eliminating Mach waves from supersonic jets. USP1999065916127.
  12. Duane C. McCormick ; Daniel L. Gysling. Tangentially directed acoustic jet controlling boundary layer. USP2002056390418.
  13. Tindell Runyon H. ; Davis Warren ; Karanik James J.. Thin inlet lip design for low drag and reduced nacelle size. USP2001016179251.
  14. Harm Dorson J. (Seattle WA) Zabinsky Joseph M. (Bellevue WA). Translating lip aircraft cowling structure adapted for noise reduction. USP1991055014933.
  15. Rudolph Peter K. C. (Seattle WA). Vortex leading edge flap assembly for supersonic airplanes. USP1997105681013.
  16. Wisler David C. (Fairfield OH) Shin Hyoun-Woo (Cincinnati OH). Vortex suppression for an eductor. USP1996055517865.

이 특허를 인용한 특허 피인용횟수: 29

  1. Owens, Lewis R.; Allan, Brian G.. Boundary-layer-ingesting inlet flow control system. USP2010087784732.
  2. Gupta,Anurag. Device for reducing jet engine exhaust noise using oscillating jets. USP2007127308966.
  3. Winter, Michael. Fan nacelle flow control. USP2013098529188.
  4. Truax, Philip P.; Miller, Daniel N.; Ma, Edward C.. Flow control redistribution to mitigate high cycle fatigue. USP2009117617670.
  5. Truax, Philip P.; Miller, Daniel N.; Ma, Edward C.. Flow control redistribution to mitigate high cycle fatigue. USP2013038402738.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  7. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  8. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  9. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  10. Abrari, Farid; Townsend, Peter. Gas turbine engine inlet. USP20181210145301.
  11. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  12. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  13. Yu, Hong; Townsend, Peter. Gas turbine engine with partial inlet vane. USP20181110119552.
  14. Leblanc, Andr?. Gas turbine inlet flow straightener. USP2005116959552.
  15. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  16. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  17. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  18. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  19. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  20. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  21. Rybalko, Michael; Conners, Timothy R.; Wayman, Thomas R.. Propulsion system using large scale vortex generators for flow redistribution and supersonic aircraft equipped with the propulsion system. USP2018029884688.
  22. Richards, Clifford John. Relating to air-breathing flight vehicles. USP2014038662453.
  23. Macchia, Enzo. Rotor assembly with scoop. USP2018059957807.
  24. Macchia, Enzo. Rotor assembly with wear member. USP2018049938848.
  25. Whitmore, Ian. Structural element of an air vehicle air intake composed of an array of passages with a hexagonal cross section. USP2016119493244.
  26. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  27. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  28. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  29. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.