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특허 상세정보

Method of cooling a gas turbine blade and apparatus therefor

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/18   
미국특허분류(USC) 60/3905 ; 60/3953 ; 60/728 ; 415/114
출원번호 US-0964632 (1978-11-29)
우선권정보 JP-0143870 (1977-12-02)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 35  인용 특허 : 2

Part of high-pressure air is extracted from the vicinity of the final stage of a compressor and is introduced into a water spraying chamber, and water at the normal temperature is injected into the high-pressure air from a nozzle installed in the water spraying chamber, to prepare a cooled coolant. The coolant sometimes contains water drops. The cooled coolant is fed into coolant passageways which are provided inside a moving blade in a manner to extend from the root part to the tip of the moving blade. When the coolant passes through the passageways, th...


A method of cooling a moving blade of a gas turbine in which high-pressure air from a compressor is passed through a combustor to make it a combustion gas, the combustion gas is introduced into a main gas passageway with a cascade including the moving blade disposed therein, and power is taken out by expansion of the combustion gas, comprising the steps of: extracting part of the high-pressure air from the compressor in order to use it for cooling; spraying water into the extracted air, and mixing water drops with the air and cooling said air, to prepare...

이 특허를 인용한 특허 피인용횟수: 35

  1. Kendrick, Donald W.. Combustion cavity layouts for fuel staging in trapped vortex combustors. USP2014048689562.
  2. Tiemann,Peter. Cooling air and injected liquid system for gas turbine blades. USP2008027334412.
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  4. 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.
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  13. Rakhmailov Anatoly,RUX ; Yaishnikov Valentin,UAX ; Kolotilenko Mikhail,UAX ; Rakhmailov Oleg,RUX ; Drozd Igor,RUX ; Kalin Martin. Gas turbine engine. USP2001026189311.
  14. Rakhmailov, Anatoly. Gas turbine engine. USP2003056557337.
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  17. Thompson, Jr., Robert S; Williams, Gregg. Gas turbine engine cooling system and method. USP2011118057163.
  18. Rakhmailov Anatoly,RUX ; Yaishnikov Valentin,UAX ; Kolotilenko Mikhail,UAX ; Rakhmailov Oleg,RUX ; Drozd Igor,RUX. Gas turbine engine having a bladed disk. USP2001086272844.
  19. Rakhmailov Anatoly,RUX. Gas turbine engine having counter rotating turbines and a controller for controlling the load driven by one of the turbines. USP2000116145296.
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  23. Ceric, Hajrudin; Gaio, Giuseppe; Günther, Frank; Hülfenhaus, Armin; Hülsemann, Gerhard; Jungnickel-Marques, Gabriel; Wanz, Stefan. Liquid injection in a gas turbine during a cooling down phase. USP2010077752847.
  24. Andersen, Leonard M.. Method and apparatus for increasing thrust or other useful energy output of a device with a rotating element. USP2014038671696.
  25. Myers Geoffrey D.. Method and apparatus for water injection via primary jets. USP2000096112511.
  26. Kendrick, Donald W.. Method of fuel staging in combustion apparatus. USP2013108549862.
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  28. Bergholz, Robert Frederick. Methods and apparatus for controlling cooling air temperature in gas turbine engines. USP2009107607307.
  29. Reback,Scott Mitchell; Sebeika,Stephen Thomas. Methods and apparatus for injecting cleaning fluids into combustors. USP2006067065955.
  30. Cunha, Francisco J.; Chiu, R. Paul. Steam and air cooling for stator stage of a turbine. USP1994065320483.
  31. Tomlinson, Leroy O.; Garry, Robert S.. System and method for determining gas turbine firing and combustion reference temperatures having correction for water content in fuel. USP2004046715916.
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  33. Hines William R. (Cincinnati OH). Turbine engine with air and steam cooling. USP1991014982564.
  34. Brostmeyer, Joseph; Wilson, Jr., Jack W.. Turbine last stage blade with forced vortex driven cooling air. USP2010037677048.
  35. Kendrick, Donald W.. Vortex premixer for combustion apparatus. USP2014048689561.