中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

446 records (took 0.026 seconds)

    TURBOFAN ENGINE FRONT SECTION
    152.
    发明申请
    TURBOFAN ENGINE FRONT SECTION 审中-公开
    涡轮发动机前部分

    公开(公告)号：US20160108807A1

    公开(公告)日：2016-04-21

    申请号：US14785872

    申请日：2014-04-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  William G. Sheridan

    IPC: F02C3/107 ,  F16H1/28 ,  F02K3/06

    CPC classification number: F01D25/24 ,  F01D5/02 ,  F01D5/12 ,  F01D17/105 ,  F02C3/107 ,  F02K3/06 ,  F04D29/321 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/24 ,  F05D2250/51 ,  F05D2260/40311 ,  F16H1/28

    Abstract: A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between about 430 and 645.

    Abstract translation: 涡扇发动机包括用于围绕轴驱动风扇的齿轮架构。 齿轮架构包括围绕轴线旋转的太阳齿轮，由太阳齿轮驱动的多个行星齿轮和围绕多个行星齿轮的环形齿轮。 载体支撑多个行星齿轮。 齿轮架构包括功率传递参数（PTP），定义为通过齿轮传动结构传递的功率，除以齿轮量乘以齿轮减速比，在约430和645之间。

    NACELLE AND COMPRESSOR INLET ARRANGEMENTS
    153.
    发明申请
    NACELLE AND COMPRESSOR INLET ARRANGEMENTS 审中-公开
    NACELLE和压缩机入口安排

    公开(公告)号：US20160076460A1

    公开(公告)日：2016-03-17

    申请号：US14824292

    申请日：2015-08-12

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Robert E. Malecki

    IPC: F02C9/18 ,  F02C3/04 ,  F02C7/36 ,  F01D25/24

    CPC classification number: F02C9/18 ,  B64D2033/022 ,  F01D25/24 ,  F02C3/04 ,  F02C7/05 ,  F02C7/36 ,  F02K3/06 ,  F05D2250/14 ,  F05D2250/232 ,  F05D2250/24

    Abstract: A gas turbine engine includes a nacelle defining a centerline axis and an annular splitter radially inward from the nacelle. A spinner is radially inward of the nacelle forward of a compressor section. A fan blade extends from a fan blade platform. A distance X is the axial distance from a first point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defined on a leading edge of the fan blade where the fan blade meets the fan blade platform. A distance H is the radial distance from the first point to the second point. The relative position of the first point and the second point is governed by the ratio of X/H≧1.5 for reducing foreign object debris (FOD) intake into the compressor section.

    Abstract translation: 燃气涡轮发动机包括限定中心线轴线的机舱和从机舱径向向内的环形分配器。 旋转器在压缩机部分的前方的机舱的径向内侧。 风扇叶片从风扇叶片平台延伸。 距离X是从第一点到第二点的轴向距离，其中第一点被限定在环形分配器的前缘上，第二点限定在风扇叶片的前缘上，其中风扇叶片与 风扇叶片平台。 距离H是从第一点到第二点的径向距离。 第一点和第二点的相对位置由减少异物（FOD）进入压缩机段的X /H≥1.5的比率决定。

    GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE
    154.
    发明申请
    GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE 审中-公开
    具有高压缩机出口温度的齿轮涡轮发动机

    公开(公告)号：US20160076445A1

    公开(公告)日：2016-03-17

    申请号：US14950393

    申请日：2015-11-24

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Karl L. Hasel

    IPC: F02C3/13 ,  F02C3/06 ,  F02C7/36 ,  F02C3/10

    CPC classification number: F02C3/13 ,  F02C3/06 ,  F02C3/10 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2250/283 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F. A combustor is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

    Abstract translation: 一种燃气涡轮发动机，包括风扇，其包括可围绕轴线旋转的多个风扇叶片。 压缩机部分包括至少第一压缩机部分和第二压缩机部分，其中第二压缩机部分的部件被构造成在平均出口温度下工作，平均出口温度在大约1000°F至大约1500°F之间。燃烧器处于 与压缩机部分流体连通。 涡轮机部分与燃烧器流体连通。 齿轮架构由涡轮部分驱动，用于围绕轴线旋转风扇。

    ALUMINUM FAN BLADE CONSTRUCTION WITH WELDED COVER
    157.
    发明申请
    ALUMINUM FAN BLADE CONSTRUCTION WITH WELDED COVER 审中-公开
    铝合金风扇叶片结构与焊接盖

    公开(公告)号：US20160024934A1

    公开(公告)日：2016-01-28

    申请号：US14877254

    申请日：2015-10-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Michael A. Weisse

    IPC: F01D5/14 ,  F01D5/02 ,  F01D5/18 ,  F02C3/04

    CPC classification number: F01D5/147 ,  B23K20/1265 ,  B23K2101/001 ,  F01D5/16 ,  F05D2220/36 ,  F05D2230/232 ,  F05D2300/121 ,  F05D2300/612

    Abstract: An airfoil includes, among other possible things, a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. A cover skin is attached to the main body. The cover skin is welded to the main body with a weld at outer edges. An adhesive is placed between inner surfaces of the cover skin and the main body. The adhesive is deposited inwardly of the outer edges of the cover skin. A method of constructing an airfoil is also disclosed as is a gas turbine engine.

    Abstract translation: 除了其它可能的事情之外，翼型件还包括在前缘和后缘之间延伸的主体。 通道形成在主体中，多个肋在通道之间延伸。 覆盖皮肤附着在主体上。 覆盖皮肤在外边缘焊接焊接到主体。 将粘合剂放置在覆盖皮肤和主体的内表面之间。 粘合剂沉积在覆盖皮肤的外边缘的内侧。 还公开了构造翼型的方法，也就是燃气轮机引擎。

    GEARED TURBOFAN WITH IMPROVED SPINNER
    158.
    发明申请
    GEARED TURBOFAN WITH IMPROVED SPINNER 审中-公开
    具有改进的旋转器的齿轮涡轮机

    公开(公告)号：US20160001873A1

    公开(公告)日：2016-01-07

    申请号：US14709744

    申请日：2015-05-12

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz

    IPC: B64C11/14 ,  F02C7/04

    CPC classification number: B64C11/14 ,  F02C3/107 ,  F02C7/04 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2250/232 ,  F05D2250/24 ,  F05D2260/40311

    Abstract: A fan section comprises a fan rotor having a plurality of blades and a spinner positioned forwardly of the fan rotor. The fan rotor is driven through a gear reduction. The spinner includes a spinner body having an outer surface with a forward end and a rearward end. A conical line extends between the forward end to the rear end. A first radius is measured from a centerline of the spinner at substantially 0.25 of a length of the spinner to the conical line. A second radius is also measured at substantially 0.25 of the length and extends outwardly to the outer surface of the spinner. A ratio of the second radius to the first radius is less than or equal to about 2.0. A gas turbine engine is also disclosed.

    Abstract translation: 风扇部分包括具有多个叶片的风扇转子和位于风扇转子前方的旋转器。 风扇转子通过齿轮减速驱动。 旋转器包括具有前表面和后端的外表面的旋转体。 锥形线在前端到后端之间延伸。 第一半径从旋转器的中心线在旋转器的长度的大致0.25处到锥形线测量。 第二个半径也在长度的大致0.25处测量，并向外延伸到旋转器的外表面。 第二半径与第一半径的比率小于或等于约2.0。 还公开了一种燃气涡轮发动机。

    Air-Oil Heat Exchangers with Minimum Bypass Flow Pressure Loss
    159.
    发明申请
    Air-Oil Heat Exchangers with Minimum Bypass Flow Pressure Loss 审中-公开
    具有最小旁路流量压力损失的空气 - 油热交换器

    公开(公告)号：US20150361891A1

    公开(公告)日：2015-12-17

    申请号：US14765509

    申请日：2013-12-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Simon Pickford

    IPC: F02C7/18 ,  F02C7/04 ,  F01D25/24 ,  F02C3/04

    Abstract: A geared turbofan engine having a bypass ratio of at least six (6) includes a nacelle that encloses a fan assembly and at least part of an engine case that houses an engine core. The fan assembly is disposed fore of the engine case. The nacelle and engine case defining an annular fan duct for air flow that passes through the fan but that bypasses the engine core. The nacelle includes a fore end and an aft end that defines a fan nozzle with the engine case. The engine case includes an inlet and an outlet. The inlet is connected to a duct that extends within the engine case to the outlet. The duct accommodates an air-oil heat exchanger between the inlet and outlet of the duct, which may be used for the gearbox dedicated to reducing the speed of the fan as compared to the low pressure turbine.

    Abstract translation: 具有至少六（6）的旁路比的齿轮涡扇发动机包括包围风扇组件和容纳发动机芯的发动机壳体的至少一部分的机舱。 风扇组件设置在发动机壳体的前方。 机舱和发动机壳体限定了通过风扇但绕过发动机芯的空气流的环形风扇通道。 机舱包括前端和后端，其与发动机壳体形成风扇喷嘴。 发动机壳体包括入口和出口。 入口连接到在发动机壳体内延伸到出口的管道。 管道容纳在管道的入口和出口之间的空气 - 油热交换器，其可用于与低压涡轮机相比专用于降低风扇速度的变速箱。

    EPICYCLIC GEAR TRAIN
    160.
    发明申请
    EPICYCLIC GEAR TRAIN 有权
    环形齿轮火车

    公开(公告)号：US20150345321A1

    公开(公告)日：2015-12-03

    申请号：US14824351

    申请日：2015-08-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

    IPC: F01D15/12 ,  F01D5/02 ,  F01D25/16 ,  F01D1/02 ,  F16H57/04 ,  F01D25/18

    CPC classification number: F01D15/12 ,  F01D1/02 ,  F01D5/02 ,  F01D5/027 ,  F01D25/16 ,  F01D25/18 ,  F02C7/32 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/40311 ,  F16H57/0423 ,  F16H57/0479 ,  F16H57/0486 ,  F16H2057/085

    Abstract: A turbine engine has a fan shaft. At least one tapered bearing is mounted on the fan shaft. The fan shaft includes at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear. A ring gear surrounds and meshes with the intermediate gears. Each of the intermediate gears are supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train. The turbine section has a fan drive turbine that includes a pressure ratio that is greater than about 5. The fan includes a pressure ratio that is less than about 1.45, and the fan has a bypass ratio of greater than about ten (10).

    Abstract translation: 涡轮发动机具有风扇轴。 至少有一个锥形轴承安装在风扇轴上。 风扇轴包括沿至少一个径向分量的方向延伸的至少一个通道，并且与至少一个锥形轴承相邻。 风扇安装在锥形轴承上旋转。 一个行星齿轮系被联接以驱动风扇。 行星齿轮系包括支撑与太阳齿轮啮合的中间齿轮的载体。 环形齿轮围绕并与中间齿轮啮合。 每个中间齿轮支撑在相应的轴颈轴承上。 行星齿轮系确定齿轮减速比大于或等于约2.3。 涡轮部分联接以通过行星齿轮系驱动风扇。 涡轮部分具有包括大于约5的压力比的风扇驱动涡轮机。风扇包括小于约1.45的压力比，并且风扇具有大于约十（10）的旁路比。

Patent Agency Ranking