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"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Flow control redistribution to mitigate high cycle fatigue

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/00   
미국특허분류(USC) 060/269; 137/015.1; 137/015.2; 415/914; 244/053.B
출원번호 UP-0418336 (2006-05-04)
등록번호 US-7617670 (2009-11-27)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Bracewell & Giuliani LLP
인용정보 피인용 횟수 : 23  인용 특허 : 6
초록

A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow, The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within th...

대표
청구항

What is claimed is: 1. An inlet flow control system for a gas turbine engine operable to improve pressure recovery and/or distortion within a flow inlet, the inlet flow control system comprising: a duct operable to receive a primary fluid flow; a first manifold; at least one primary jet vortex generator located proximate to an inner surface of the duct wherein the at least one primary jet vortex generator injects fluid received from the first pressure manifold at a first injection rate into a boundary layer of the primary fluid flow within the flow inle...

이 특허를 인용한 특허 피인용횟수: 23

  1. Little, David A.; Paprotna, Hubertus E.; Light, Kevin M.. Combustion turbine including a diffuser section with cooling fluid passageways and associated methods. USP2012098257025.
  2. Dawson, Stacie M.; Wiley, Richard. Core reflex nozzle for turbofan engine. USP2011088002520.
  3. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  4. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  7. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  8. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  9. Ramakrishnan, Kishore. Inlet assembly for an aircraft aft fan. USP20190410252790.
  10. Ramakrishnan, Kishore; Otta, Shourya Prakash. Inlet assembly for an aircraft aft fan. USP20190410259565.
  11. Yao, Jixian. Inlet guide vane assembly for reducing airflow swirl distortion of an aircraft aft fan. USP20190410253779.
  12. Richardson, Giles Anthony; MacManus, David; Sheaf, Christopher Thomas John. Intake liner for a gas turbine engine. USP2015018931252.
  13. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  14. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  15. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  16. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  17. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  18. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  19. Surply, Thierry; Bourdeau, Christophe. Turbojet nacelle and method for controlling separation in a turbojet nacelle. USP2014028640986.
  20. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  21. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  22. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  23. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.