|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-006/08 F01D-005/08 F02C-007/06 F02C-007/18|
|미국특허분류(USC)||060/782; 060/795; 060/785; 060/806; 060/039.08; 060/266; 060/267; 060/039.83; 184/006.11|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 14 인용 특허 : 20|
A gas turbine engine includes a heat exchanger, a bearing compartment, and a nozzle assembly in fluid communication with the bearing compartment. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The bearing compartment is in fluid communication with the heat exchanger. A first passageway communicates the conditioned airflow from the heat exchanger to the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment to the nozzle assembly.
1. A gas turbine engine, comprising: a compressor section, a combustor section and a turbine section circumferentially disposed about an engine centerline axis;a buffer cooling system that establishes a buffer cooled cooling air path that conditions a part of at least one of said compressor section and said turbine section, wherein said buffer cooling system includes a heat exchanger, a passageway and a nozzle assembly, and said buffer cooled cooling air path extends from said heat exchanger, through said passageway, and then through said nozzle assembly...