|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-007/20 F02C-007/28 F01D-011/14 F01D-011/18 F01D-015/02|
|미국특허분류(USC)||060/796; 060/806; 060/039.091; 415/200; 415/173.1; 415/173.5; 415/174.5|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 326|
A method and apparatus are disclosed for a gas turbine spool design combining metallic and ceramic components in a way that controls clearances between critical components over a range of engine operating temperatures and pressures. In a first embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud and separated by a small clearance gap. The ceramic rotor is connected to a metallic volute. In order to accommodate the differential rates of thermal expansion between the ceramic rotor and metallic volute, an active clearance control system ...
1. A gas turbine engine, comprising: at least one turbo-compressor spool assembly, wherein the at least one turbo-compressor spool assembly comprises a compressor in mechanical communication with a turbine, a volute directing an inlet gas towards an inlet of a rotor of the turbine and a shroud adjacent to the rotor of the turbine, the shroud directing an outlet gas towards an outlet of the at least one turbo-compressor spool assembly; anda clearance control device to substantially maintain, during the at least one turbo-compressor spool assembly operatio...