|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-007/18 F02C-003/045 F01D-009/06 F02C-007/20 F01D-005/18 F01D-005/08|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 14|
A gas turbine engine includes a core engine that has a compressor section, a combustor section and a turbine section. A thermal management system is configured to receive a cooling stream. The thermal management system includes a metering device that is located near an outer diameter of the core engine. The metering device is configured to divide the cooling stream into multiple segregated passages. The metering device can be configured to divide the cooling stream between a first passage and a second passage that is concentric with the first passage.
1. A gas turbine engine comprising: a core engine including, a compressor section,a combustor in fluid communication with the compressor section, anda turbine section in fluid communication with the combustor; anda thermal management system configured to receive a cooling stream, the thermal management system including a metering device located near an outer diameter of the core engine, the metering device being configured to divide the cooling stream into multiple segregated passages, the metering device including an inner tube and an outer tube that is...