发明名称 |
TURBINE SECTION OF HIGH BYPASS TURBOFAN |
摘要 |
A turbofan engine (20) comprises a fan (42) having fan blades (70). A compressor is in communication with the fan section. The fan (42) is configured to communicate a portion of air into a bypass path defining a bypass area outwardly of the compressor and a portion into the compressor. A bypass ratio is greater than 6.0. A combustor (48) is in fluid communication with the compressor. A turbine is in communication with the combustor (48). The turbine has a first turbine section (27) that includes two or more stages (200, 202, 204) and a second turbine section (26) that includes at least two stages. A ratio of airfoils in the first turbine section (27) to the bypass ratio is less than 170. The first turbine section (27) includes a maximum gas path radius. A ratio of the maximum gas path radius to a maximum radius of the fan blades (70) is less than 0.50. A speed reduction mechanism (46) is coupled to the fan (42) and rotatable by the turbine. |
申请公布号 |
EP3115590(A1) |
申请公布日期 |
2017.01.11 |
申请号 |
EP20160178679 |
申请日期 |
2016.07.08 |
申请人 |
United Technologies Corporation |
发明人 |
ADAMS, Paul R.;MAGGE, Shankar S.;STAUBACH, Joseph B.;LORD, Wesley K.;SCHWARZ, Frederick M.;SUCIU, Gabriel L. |
分类号 |
F02K3/06;F02C3/107;F02C7/36 |
主分类号 |
F02K3/06 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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