|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3902 ; 60/3915 ; 60/3975 ; 415/116|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 15 인용 특허 : 7|
A method for periodically restoring the blade tip to annular seal clearance in a gas turbine engine (10) includes incrementing (42a, 42b) the flow of external cooling air responsive only to an accumulated engine use parameter (58).
A method for maintaining long term performance efficiency between consecutive periodic seal replacement in a particular one of a plurality of substantially similar gas turbine engines each having an active clearance control system for selectably reducing the clearance between a plurality of rotating blade tips and a surrounding annular seal, including means, disposed adjacent a portion of the engine structure, for delivering a modulated flow of gas, said gas flow having a temperature substantially different from the engine portion, means, responsive to c...