|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/053R; 060/226.3; 060/039.163|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 3 인용 특허 : 48|
A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
1. A gas turbine engine comprising: a fan section rotatable about an engine centerline axis and configured for operation at a fan pressure ratio of less than about 1.45;a fan drive turbine that includes six (6) or less stages;a second spool including a compressor section that includes between eight to fifteen (8-15) stages, and a second turbine section coupled to the second compressor section, wherein the fan drive turbine is axially aft of the second turbine section; anda gear train defined along an engine centerline axis, said fan drive turbine is oper...