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    TURBINE SECTION OF HIGH BYPASS TURBOFAN
    5.
    发明申请
    TURBINE SECTION OF HIGH BYPASS TURBOFAN 审中-公开
    高旁路涡轮机涡轮部分

    公开(公告)号：US20150345404A1

    公开(公告)日：2015-12-03

    申请号：US14692090

    申请日：2015-04-21

    Applicant: United Technologies Corporation

    Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz

    IPC: F02C9/18 ,  F02C7/36 ,  F01D25/24 ,  F01D1/02 ,  F01D5/02 ,  F01D9/04 ,  F02C3/04 ,  F02C7/20

    Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

    Abstract translation: 涡轮风扇发动机具有发动机壳体和通过发动机壳体的气路。 风扇具有圆周阵列的风扇叶片。 发动机还具有压缩机，燃烧器，气体发生涡轮机和低压涡轮部分。 减速机构将低压涡轮部分连接到风扇。 旁路面积比大于约6.0。 低压涡轮机翼型计数到旁路面积比低于约170。

    TURBINE SECTION OF HIGH BYPASS TURBOFAN
    7.
    发明申请
    TURBINE SECTION OF HIGH BYPASS TURBOFAN 审中-公开
    高旁路涡轮机涡轮部分

    公开(公告)号：US20150377123A1

    公开(公告)日：2015-12-31

    申请号：US14793785

    申请日：2015-07-08

    Applicant: United Technologies Corporation

    Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C3/107 ,  F02K3/02 ,  F02C9/18

    CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D11/122 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/20 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F04D19/02 ,  F05B2250/283 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

    Abstract: A turbofan engine comprises a fan having fan blades. A compressor is in communication with the fan section. The fan 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 defined as air communicated through the bypass path relative to air communicated to the compressor being greater than about 6.0. A combustor is in fluid communication with the compressor. A turbine is in communication with the combustor. The turbine has a first turbine section that includes two or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to the bypass ratio is less than about 170. The first turbine section includes a maximum gas path radius. A ratio of the maximum gas path radius to a maximum radius of the fan blades is less than about 0.50. A speed reduction mechanism is coupled to the fan and rotatable by the turbine.

    Abstract translation: 涡轮风扇发动机包括具有风扇叶片的风扇。 压缩机与风扇部分连通。 风扇被构造成将一部分空气传送到限定压缩机外部的旁路区域的旁路，以及一部分进入压缩机。 旁路比定义为相对于连通到压缩机的空气通过旁路通路的空气大于约6.0。 燃烧器与压缩机流体连通。 涡轮机与燃烧器连通。 涡轮机具有包括两级或更多级的第一涡轮部分和包括至少两级的第二涡轮部分。 第一涡轮机部分中的翼型件与旁路比率的比率小于约170.第一涡轮机部分包括最大气体路径半径。 风扇叶片的最大气路半径与最大半径的比值小于约0.50。 减速机构联接到风扇并由涡轮旋转。

    TURBINE SECTION OF HIGH BYPASS TURBOFAN
    8.
    发明申请
    TURBINE SECTION OF HIGH BYPASS TURBOFAN 审中-公开
    高旁路涡轮机涡轮部分

    公开(公告)号：US20150377122A1

    公开(公告)日：2015-12-31

    申请号：US14793770

    申请日：2015-07-08

    Applicant: United Technologies Corporation

    Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C3/10 ,  F02K3/06 ,  F02C7/36

    CPC classification number: F02K3/06 ,  F02C3/107 ,  F02C7/36 ,  F02K3/075 ,  F05D2260/40311

    Abstract: A turbofan engine includes an engine case, a gaspath through the engine case, a fan having an array of fan blades, a compressor in fluid communication with the fan, a combustor in fluid communication with the compressor, and a turbine in fluid communication with the combustor. The turbine has a fan drive turbine section having 3 to 6 blade stages. A speed reduction mechanism couples the fan drive turbine section to the fan. A ratio of maximum gaspath radius along the low pressure turbine section to maximum radius of the fan blades is less than about 0.55. A bypass area ratio is greater than about 6.0. A ratio of a fan drive turbine section airfoil count to the bypass area ratio is less than about 170 and a second turbine section.

    Abstract translation: 涡轮风扇发动机包括发动机壳体，通过发动机壳体的气路，具有风扇叶片阵列的风扇，与风扇流体连通的压缩机，与压缩机流体连通的燃烧器，以及与压缩机流体连通的涡轮机 燃烧器。 涡轮机具有风扇驱动涡轮机部分，具有3到6个叶片级。 减速机构将风扇驱动涡轮部分连接到风扇。 沿着低压涡轮机段的最大气路径与风扇叶片的最大半径之比小于约0.55。 旁路面积比大于约6.0。 风扇驱动涡轮机翼型计数与旁路面积比的比率小于约170，而第二涡轮部分。

    Gas turbine engine mid turbine frame with flow turning features
    9.
    发明授权
    Gas turbine engine mid turbine frame with flow turning features 有权
    燃气涡轮发动机中涡轮机架具有流动转向特征

    公开(公告)号：US08915090B2

    公开(公告)日：2014-12-23

    申请号：US14221450

    申请日：2014-03-21

    Applicant: United Technologies Corporation

    Inventor： Thomas J. Praisner ,  Shankar S. Magge ,  Matthew B. Estes

    IPC: F02D1/00 ,  F01D9/04 ,  F01D25/28 ,  F02K3/06

    CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D9/04 ,  F01D9/065 ,  F01D25/28 ,  F02K3/06 ,  F05D2240/12 ,  Y02T50/673

    Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.

    Abstract translation: 燃气涡轮发动机包括具有旋转轴线的第一和第二级。 在第一阶段和第二阶段之间轴向布置有圆周阵列的翼型件。 至少一个翼型件具有在压力侧和吸力侧之间等距离设置的曲率。 翼型件从翼缘沿着翼型在中跨平面处从前缘延伸到后缘。 第一和第二线之间的角度分别与翼型前缘和后缘的中跨平面和曲率的交点相切。 该角度等于或大于约10°。

    GAS TURBINE ENGINE MID TURBINE FRAME WITH FLOW TURNING FEATURES
    10.
    发明申请
    GAS TURBINE ENGINE MID TURBINE FRAME WITH FLOW TURNING FEATURES 有权
    气体涡轮发动机中间涡轮机框架与流动特性

    公开(公告)号：US20140202133A1

    公开(公告)日：2014-07-24

    申请号：US14221450

    申请日：2014-03-21

    Applicant: United Technologies Corporation

    Inventor： Thomas J. Praisner ,  Shankar S. Magge ,  Matthew B. Estes

    IPC: F01D9/04 ,  F02K3/06

    CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D9/04 ,  F01D9/065 ,  F01D25/28 ,  F02K3/06 ,  F05D2240/12 ,  Y02T50/673

    Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.

    Abstract translation: 燃气涡轮发动机包括具有旋转轴线的第一和第二级。 在第一阶段和第二阶段之间轴向布置有圆周阵列的翼型件。 至少一个翼型件具有在压力侧和吸力侧之间等距离设置的曲率。 翼型件从翼缘沿着翼型在中跨平面处从前缘延伸到后缘。 第一和第二线之间的角度分别与翼型前缘和后缘的中跨平面和曲率的交点相切。 该角度等于或大于约10°。

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