|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||415/001; 415/116; 415/173.1|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 1 인용 특허 : 18|
A method of cooling a shroud ring in a turbine section of gas turbine engine includes identifying a series of alternating high temperature regions and lower temperature regions of a circumferential temperature distribution about the inner surface of the shroud ring, and impinging cooling air on to an outer surface of the shroud ring. More cooling air is impinged onto regions which correspond to the high temperature regions on the shroud ring than to regions corresponding to the lower temperature regions of the shroud ring.
1. A method of cooling a turbine shroud ring within a surrounding turbine support case in a turbine section of a gas turbine engine, the turbine shroud ring including a plurality of individual turbine shroud segments circumferentially arranged to form the turbine shroud ring, at least an inner surface of the shroud ring being exposed to an annular hot gas flow produced from a combustor of the gas turbine engine having a plurality of circumferentially spaced apart fuel nozzles, the method comprising: identifying a series of alternating high temperature re...