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특허 상세정보

Gas turbine engine compressor arrangement

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-029/00   
미국특허분류(USC) 244/053R; 060/226.3; 060/039.163
출원번호 US-0340969 (2011-12-30)
등록번호 US-8807477 (2014-08-19)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds, P.C.
인용정보 피인용 횟수 : 3  인용 특허 : 48
초록

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.

대표
청구항

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...

이 특허에 인용된 특허 (48)

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