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특허 상세정보

Advanced integrated propulsion system with total optimized cycle for gas turbines

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-001/06   
미국특허분류(USC) 60/3917 ; 60/3929 ; 60/39511
출원번호 US-0855847 (1986-04-24)
발명자 / 주소
인용정보 피인용 횟수 : 89  인용 특허 : 4
초록

A gas turbine system with integrated high and low pressure circuits having a power transmission for extracting work from one of the circuits, the volume of air and fuel to the respective circuits being varied according to the power demand monitored by a microprocessor, wherein the turbine system has a low pressure compressor and a staged high pressure compressor with a combustion chamber and high pressure turbine associated with the high pressure compressor, and, a combustion chamber and a low pressure turbine associated with the low pressure compressor,...

대표
청구항

A gas turbine assembly with integrated high and low pressure circuits comprising: a low pressure air compressor and a high pressure air compressor staged with the low pressure air compressor; a first high pressure combustion chamber and associated two-stage, high pressure turbine communicating with the high pressure combustion chamber, the two-stage high pressure turbine having a first stage coupled to the high pressure air compressor and a second stage coupled to the low pressure air compressor; a second low pressure combustion chamber and associated lo...

이 특허를 인용한 특허 피인용횟수: 89

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