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    LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM WITH SAFE PYLON TRANSIT
    382.
    发明申请
    LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM WITH SAFE PYLON TRANSIT 审中-公开
    低压环境控制系统安全透平

    公开(公告)号：US20160177820A1

    公开(公告)日：2016-06-23

    申请号：US14751320

    申请日：2015-06-26

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C3/06 ,  F02C7/20

    CPC classification number: F02C7/20 ,  B64D13/06 ,  B64D2013/0618 ,  B64D2013/0648 ,  F02C6/08 ,  Y02T50/56

    Abstract: A gas turbine engine includes a fan section delivering air into a compressor section. The compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. A pylon supports the engine. The pylon defines a lowermost surface and the higher pressure tap extends above a plane including the lowermost surface. The higher pressure tap includes a double wall tube above the plane for preventing leakage from impinging on a portion of the pylon. An environmental control system is also disclosed.

    Abstract translation: 燃气涡轮发动机包括将空气输送到压缩机部分中的风扇部分。 压缩机部分压缩空气并将空气输送到燃烧部分中。 燃烧产物从燃烧部分通过涡轮部分，以驱动风扇部分和主要压缩机部分。 变速箱由涡轮部分驱动以驱动风扇部分。 环境控制系统包括在压缩机部分中较高压力位置处的较高压力分接头和在较低压力位置处的较低压力分接头。 较低压力位置处于比较高压力位置更低的压力。 较低压力分接头连通到通向下游出口的第一通道，并具有通向涡轮压缩机的压缩机部分的第二通道。 较高压力分接头进入涡轮压缩机的涡轮部分，使得较高压力分接头中的空气驱动涡轮部分，从而驱动涡轮压缩机的压缩机部分。 涡轮压缩机的压缩机部分和涡轮部分的组合出口混合并通过下游以被输送到飞行器使用。 吊架支撑发动机。 塔架限定最下表面，较高压力水龙头在包括最下表面的平面之上延伸。 较高压力水龙头包括在该平面上方的双壁管，用于防止泄漏撞击在塔架的一部分上。 还公开了一种环境控制系统。

    GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES
    385.
    发明申请
    GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES 审中-公开
    具有高速低压涡轮部分和轴承支持特性的气体涡轮发动机

    公开(公告)号：US20160053679A1

    公开(公告)日：2016-02-25

    申请号：US14932251

    申请日：2015-11-04

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  Daniel Bernard Kupratis ,  William K. Ackermann

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

    CPC classification number: F02C7/06 ,  F01D25/162 ,  F02C7/20 ,  F02K3/06

    Abstract: A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a fan drive turbine section and a second turbine section. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. The second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机的涡轮部分包括风扇驱动涡轮部分和第二涡轮机部分。 风扇驱动涡轮部分在第一出口处具有第一出口区域，并且构造成以第一速度旋转。 第二涡轮部分在第二出口处具有第二出口区域，并且构造成以比第一速度快的第二速度旋转。

    TURBINE SECTION OF HIGH BYPASS TURBOFAN
    389.
    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
    390.
    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。

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