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1.发明公开
公开(公告)号：EP3115589A1
公开(公告)日：2017-01-11
申请号：EP16178668.6
申请日：2016-07-08
发明人： ADAMS, Paul R. , MAGGE, Shankar S. , STAUBACH, Joseph B. , LORD, Wesley K. , SCHWARZ, Frederick M. , SUCIU, Gabriel L.
摘要： A turbofan engine (20) includes an engine case (22), a gaspath through the engine case (22), a fan (42) having a circumferential array of fan blades, a compressor in fluid communication with the fan (42), a combustor (48) in fluid communication with the compressor, and a turbine in fluid communication with the combustor (48). The turbine has a fan drive turbine section (27) having 3 to 6 blade stages (200, 202, 204). A speed reduction mechanism (46) couples the fan drive turbine section (27) to the fan (42). A bypass area ratio is between 8.0 and 20.0. A ratio of maximum gaspath radius along the fan drive turbine section (27) to maximum radius of the fan (42) is less than 0.50. A ratio of a turbine section airfoil count to the bypass area ratio is between 10 and 170.
摘要翻译： 涡轮风扇发动机（20）包括发动机壳体（22），通过发动机壳体（22）的气路，具有圆周阵列的风扇叶片的风扇（42），与风扇（42）流体连通的压缩机， 与压缩机流体连通的燃烧器（48）和与燃烧器（48）流体连通的涡轮机。 涡轮机具有风扇驱动涡轮部分（27），其具有3至6个叶片级（200,202,204）。 减速机构（46）将风扇驱动涡轮部分（27）连接到风扇（42）。 旁路面积比在8.0和20.0之间。 沿着风扇驱动涡轮部分（27）的最大气路径半径与风扇（42）的最大半径的比值小于0.50。 涡轮机翼型计数与旁路面积比的比值在10和170之间。
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公开(公告)号：EP3115590A1
公开(公告)日：2017-01-11
申请号：EP16178679.3
申请日：2016-07-08
发明人： ADAMS, Paul R. , MAGGE, Shankar S. , STAUBACH, Joseph B. , LORD, Wesley K. , SCHWARZ, Frederick M. , SUCIU, Gabriel L.
CPC分类号： F02K3/06 , F02C3/107 , F05D2250/30 , F05D2260/40311
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.
摘要翻译： 涡扇发动机（20）包括具有风扇叶片（70）的风扇（42）。 压缩机与风扇部分连通。 风扇（42）被构造成将空气的一部分连通到限定压缩机外侧的旁路区域的旁通路径和压缩机的一部分。 旁路比大于6.0。 燃烧器（48）与压缩机流体连通。 涡轮机与燃烧器（48）连通。 涡轮机具有包括两个或多个级（200,202,204）的第一涡轮部分（27）和包括至少两个级的第二涡轮机部分（26）。 第一涡轮部分（27）中的翼型件与旁路比的比率小于170.第一涡轮部分（27）包括最大气体路径半径。 风扇叶片（70）的最大气路半径与最大半径的比小于0.50。 减速机构（46）联接到风扇（42）并由涡轮机旋转。
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3.发明公开TURBINE SECTION OF HIGH BYPASS TURBOFAN 审中-公开TURBINENABSCHNITT EINES TURBOFAN MIT HOHEMNEBENSTROMVERHÄLTNIS
公开(公告)号：EP3115576A1
公开(公告)日：2017-01-11
申请号：EP16178691.8
申请日：2016-07-08
发明人： ADAMS, Paul R. , MAGGE, Shankar S. , STAUBACH, Joseph B. , LORD, Wesley K. , SCHWARZ, Frederick M. , SUCIU, Gabriel L.
CPC分类号： F02C7/36 , F02K3/068 , F05D2220/36 , F05D2260/40311
摘要： A turbofan engine (20) includes an engine case (22), a gaspath through the engine case (22), a fan (42) having an array of fan blades, a compressor in fluid communication with the fan (42), a combustor (48) in fluid communication with the compressor, and a turbine in fluid communication with the combustor (48). The turbine has a fan drive turbine section (27) having 3 to 6 blade stages (200, 202, 204) and a second turbine section (26). A speed reduction mechanism (46) couples the fan drive turbine (27) section to the fan (42). A ratio of maximum gaspath radius along the fan drive turbine section (27) to maximum radius of the fan blades is less than 0.55. A bypass area ratio is greater than 6.0. A ratio of a fan drive turbine section airfoil count to the bypass area ratio is less than 170.
摘要翻译： 涡轮风扇发动机（20）包括发动机壳体（22），通过发动机机壳（22）的气路，具有风扇叶片阵列的风扇（42），与风扇（42）流体连通的压缩机，燃烧器 （48）与所述压缩机流体连通，以及与所述燃烧器（48）流体连通的涡轮机。 涡轮机具有风扇驱动涡轮机部分（27），其具有3至6个叶片级（200,202,204）和第二涡轮部分（26）。 减速机构（46）将风扇驱动涡轮机（27）部分连接到风扇（42）。 风扇驱动涡轮部分（27）的最大气路径半径与风扇叶片的最大半径之比小于0.55。 旁路面积比大于6.0。 风扇驱动涡轮机翼型计数与旁路面积比的比值小于170。
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公开(公告)号：EP3591192A1
公开(公告)日：2020-01-08
申请号：EP19184028.9
申请日：2019-07-02
发明人： ADAMS, Paul R. , MAGGE, Shankar S. , STAUBACH, Joseph B. , LORD, Wesley K. , SCHWARZ, Frederick M , SUCIU, Gabriel L.
摘要： A turbofan engine (20) according to an example of the present disclosure includes, among other things, a fan (42) including a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a first compressor section (28) and a second compressor section (27), the second compressor section including a second compressor section inlet with a second compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, a shaft assembly (23) having a first portion (24) and a second portion (25), a turbine in fluid communication with the combustor, the turbine having a first turbine section (26) coupled to the first portion of the shaft assembly to drive the first compressor section, and a second turbine section (27) coupled to the second portion of the shaft assembly to drive the fan, an epicyclic transmission (46) coupled to the fan and rotatable by the second turbine section through the second portion of the shaft assembly to allow the second turbine to turn faster than the fan, wherein the second turbine section includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.
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公开(公告)号：EP3591191A1
公开(公告)日：2020-01-08
申请号：EP19184027.1
申请日：2019-07-02
发明人： ADAMS, Paul R. , MAGGE, Shankar S. , STAUBACH, Joseph B. , LORD, Wesley K. , SCHWARZ, Frederick M. , SUCIU, Gabriel L.
摘要： Turbofan engine (20) comprising a fan (42) including an array of fan blades rotatable about an engine axis, a compressor including a first compressor section (30) and a second compressor section (28), the second compressor section including a second compressor section inlet with a compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, wherein a ratio of the fan duct annulus area to the compressor inlet annulus area defines a bypass area ratio between 8.0 and 20.0, a turbine having a first turbine section (26) driving the first compressor section, and a second turbine section (27) driving the fan through an epicyclic gearbox (46), the second turbine section including blades and vanes, and a second turbine airfoil count defined as the numerical count of all of the blades and vanes in the second turbine section, wherein a ratio of the second turbine airfoil count to the bypass area ratio is between 100 and 150, wherein the second turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6, and wherein a hub-to-tip ratio (R I :R O ) of the second turbine section is greater than 0.5, measured at the maximum R O axial location in the second turbine section.
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公开(公告)号：EP3409935A1
公开(公告)日：2018-12-05
申请号：EP18184558.7
申请日：2012-06-15
发明人： ADAMS, Paul R. , MAGGE, Shankar S. , STAUBACH, Joseph B. , LORD, Wesley K. , SCHWARZ, Frederick M. , SUCIU, Gabriel L.
CPC分类号： F02C9/18 , F01D1/02 , F01D5/02 , F01D9/041 , F01D25/24 , F02C3/04 , F02C3/107 , F02C3/113 , F02C7/20 , F02C7/36 , F02K3/025 , F02K3/06 , F02K3/075 , F02K7/06 , F05D2220/32 , F05D2260/40311 , F05D2260/606 , Y02T50/671
摘要： A turbofan engine (20) has an engine case (22) and a gaspath through the engine case (22). A fan (42) has a circumferential array of fan blades (70). The engine further has a compressor, a combustor, a gas generating turbine (26), and a low pressure turbine section (27). A speed reduction mechanism (46) couples the low pressure turbine section (27) to the fan (42). A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.
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