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특허 상세정보

Method and apparatus for turbine system combustor temperature

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-009/04    F02C-009/14   
미국특허분류(USC) 60/3903 ; 60/3923 ; 60/3927 ; 60/3982 ; C
출원번호 US-0519288 (1974-10-30)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 72  인용 특허 : 0
초록

A method and apparatus for operating a gas turbine system are disclosed utilizing an adiabatic combustion process, employing combustion of a pre-mixed carbonaceous fuel-air admixture in a combustion zone. The combustion and the combustion zone are maintained at an approximately constant temperature by selective control of the fuel-to-air ratio over a period of turbine operation during which the fuel demand or the combustion air temperature varies. Such combustion is conducted in the presence of an oxidation catalyst and the combustion zone including the ...

대표
청구항

A method for operating a gas turbine by combusting a carbonaceous fuel over a period of operation of said turbine during which the fuel demand or the combustion air temperature varies, comprising: a. forming an intimate admixture of said fuel and combustion air; b. substantially simultaneously controlling the ratio of said fuel to said combustion air in said admixture to maintain the adiabatic flame temperature of said admixture at about a preselected value; c. combusting at least a portion of the fuel in said admixture under essentially adiabatic condit...

이 특허를 인용한 특허 피인용횟수: 72

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