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특허 상세정보

Gas turbine engine operating process

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-003/14    F02C-007/12   
미국특허분류(USC) 60/3906 ; 60/3936 ; 60/735 ; 60/744
출원번호 US-0127916 (1987-12-02)
발명자 / 주소
인용정보 피인용 횟수 : 21  인용 특허 : 1

The process of increasing the efficiency and output of a gas-turbine having blades in a combustion chamber which includes cooling the gas-turbine blades with a liquid-fuel and mixing the fuel used for cooling with air in the combustion chamber and burning the mixture and driving the turbine by the exhaust from the combustion chamber. Preferably the fuel is a liquid-gas such as hydrogen. The turbine may be cooled by injecting liquid-fuel onto its disk to provide a film coating which is centrifuged around the blades whereby the liquid will cool both the in...


The process of increasing the efficiency and output of gas turbine blades and a combustion chamber comprising: arranging the combustion chamber, annularly around the turbine blades, cooling the gas turbine blades with a mixture of air and liquid fuel introduced internally in the blades, wherein the liquid fuel vaporizes to form an air-fuel vapor mixture, expelling the air-fuel vapor mixture directly from the blades into the annular combustion chamber for turbulent mixing and combustion. combusting the air-fuel vapor mixture, recuperatively recovering the...

이 특허를 인용한 특허 피인용횟수: 21

  1. Melconian Jerry O. (Reading MA). Annular vortex slinger combustor. USP1991034996838.
  2. Stimson Martin L. ; Musil Joseph E.. Asphalt plant having centralized media burner and low fugitive emissions. USP2000116146007.
  3. Stimson, Martin L.; Musil, Joseph E.. Asphalt plant having centralized media burner and low fugitive emissions. USP2003106634780.
  4. Kendrick, Donald W.. Combustion cavity layouts for fuel staging in trapped vortex combustors. USP2014048689562.
  5. Boehnlein John J. ; Bendot Joseph G.. Ejector ramjet engine. USP1999095946904.
  6. Stickler David B. ; Kerrebrock Jack L.. Evaporatively cooled rotor for a gas turbine engine. USP1999015857836.
  7. Wang, Ivan; Ethier, Jason; Shen, Hardy. Fluid flow devices with vertically simple geometry and methods of making the same. USP2015129217370.
  8. Thompson, Jr., Robert S.; Williams, Gregg G.; Jarrell, David W.; Lynch, Curtis E.; Suchezky, Mark E.. Fuel-cooled bladed rotor of a gas turbine engine. USP2016109464527.
  9. Anatoly Rakhmailov RU. Gas turbine engine. USP2002106460343.
  10. Thompson Jr.,Robert S.; Williams,Gregg. Gas turbine engine cooling system and method. USP2006016988367.
  11. Thompson, Jr., Robert S.; Williams, Gregg; Jarrell, David W.; Lynch, Curtis E.; Suchezky, Mark E.. Gas turbine engine cooling system and method. USP2014098820092.
  12. Thompson, Jr., Robert S; Williams, Gregg. Gas turbine engine cooling system and method. USP2011118057163.
  13. Sordyl, John; Condevaux, Jamey J.. Gas turbine engine rotary injection system and method. USP2014078763405.
  14. Paul, Marius A.. Integrated bypass turbojet engines for air craft and other vehicles. USP2005116966174.
  15. Kendrick, Donald W.. Method of fuel staging in combustion apparatus. USP2013108549862.
  16. Ethier, Jason How-Ring; Wang, Ivan; Herold, Erik; Hatch, Alyssa M.. Micro gas turbine systems and uses thereof. USP20180710030580.
  17. Rodriguez, Jose L.. Radial midframe baffle for can-annular combustor arrangement having tangentially oriented combustor cans. USP2015099134029.
  18. Montgomery, Matthew D.; Charron, Richard C.; Rodriguez, Jose L.; Küsters, Bernhard W.; Morrison, Jay A.; Beeck, Alexander R.. Swirling midframe flow for gas turbine engine having advanced transitions. USP2016129528706.
  19. Commaret, Patrice Andre; Hernandez, Didier Hippolyte; Locatelli, David. System for ventilating a combustion chamber wall in a turbomachine. USP2010117827798.
  20. Kendrick, Donald W.. Vortex premixer for combustion apparatus. USP2014048689561.
  21. Haase, Richard Alan. Water combustion technology—methods, processes, systems and apparatus for the combustion of hydrogen and oxygen. USP2012048161748.