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특허 상세정보

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Integrated steam and air cooling for combined cycle gas turbines

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-005/18   
미국특허분류(USC) 415/114 ; 415/115 ; 415/48 ; 416/96R
출원번호 US-0794032 (1991-11-19)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 56  인용 특허 : 0
초록
▼

A steam or air-cooled combined cycle gas turbine includes first and second turbine stages and a second nozzle stage disposed about a spacer between the turbine stages. Cooling steam is passed through the nozzle vanes radially inwardly and through the seal between the spacer and the nozzle stage into a pair of chambers. Inlet ports are carried by the first and second-stage turbines for conducting the steam through both single and multi-pass circuits in the turbine blades to cool the blades. Steam is inlet along the axis of the turbine for mixing with the ...

대표
청구항
▼

A cooling system for a gas turbine comprising: a pair of axially spaced, rotatable turbine stages, each having a plurality of turbine blades for disposition in a gas flow through said turbine; said turbine blades each having at least one interior passage extending from an inlet port adjacent a root portion of the blade to an outlet port adjacent a tip portion of the blade; a nozzle stage between said turbine stages and including a plurality of nozzle vanes for disposition in the gas flow; each said vane having at least one interior passage having an inle...

이 특허를 인용한 특허 피인용횟수: 56

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  23. Hildebrand, Gregory C.; Hansen, James O.; Parkos, Jr., Joseph; Weisse, Michael A.; Hertel, Christopher J.; Meyer, Jesse. Gas turbine rotary blade with tip insert. USP2017099752441.
  24. Fukuno Hiroki,JPX ; Tomita Yasuoki,JPX ; Suenaga Kiyoshi,JPX. Gas turbine stationary blade. USP2001076264426.
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  28. Cunha Francisco J. (Schenectady NY). Impingement cooling for turbine stator vane trailing edge. USP1997035611662.
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  47. Parry, William T.; Tomaso, Christopher M.. System and method for providing supercritical cooling steam into a wheelspace of a turbine. USP2012058167535.
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  49. Liang, George. Turbine airfoil cooling system with perimeter cooling and rim cavity purge channels. USP2009067547191.
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  53. Liang, George. Turbine blade with triple pass serpentine flow cooling circuit. USP2009117611330.
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