|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||600/390.3 ; 600/392.3 ; 600/392.5 ; 600/392.9|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 23 인용 특허 : 5|
A gas turbine engine comprises a centrifugal compressor (4), an air diffuser (8), a heat exchanger (10), combustion apparatus (12), and first and second turbines (14,18). The combustion chamber assembly (22) comprises a primary, a secondary and a tertiary fuel and air mixing ducts (54,78,98). The compressor (4), diffuser (8), primary and secondary fuel and air mixing ducts (54,78) and turbines (14,18) all comprise means (6,8,16,20) for varying the mass flow area at their inlets such that in operation the amount of air mass through each component may be i...
[ We claim:] [30.]30. A method of controlling a gas turbine engine wherein the engine includes a centrifugal compressor, a diffuser, a heat exchanger, combustion apparatus and at least one turbine, said compressor, said diffuser, said combustion apparatus and said at least one turbine all comprise means for varying the flow capacity at their inlets, comprising the steps of independently varying the flow capacity of each component so that over a predetermined power range the gas turbine engine mass flow is variable whilst maintaining the temperature, pres...