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    TURBOFAN ENGINE FRONT SECTION
    21.
    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：WO2015012923A2

    公开(公告)日：2015-01-29

    申请号：PCT/US2014035821

    申请日：2014-04-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  SHERIDAN WILLIAM G

    IPC: F02C7/32 ,  F02C3/04 ,  F02K3/06 ,  F16H1/28

    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。

    MULTI-CIRCUIT LUBRICATION SYSTEM FOR A TURBINE ENGINE
    23.
    发明申请
    MULTI-CIRCUIT LUBRICATION SYSTEM FOR A TURBINE ENGINE 审中-公开
    用于涡轮发动机的多回路润滑系统

    公开(公告)号：WO2014123863A2

    公开(公告)日：2014-08-14

    申请号：PCT/US2014014601

    申请日：2014-02-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  PICKFORD SIMON

    CPC classification number: F01D25/20 ,  F01D1/02 ,  F01D15/10 ,  F01D15/12 ,  F01D25/08 ,  F01D25/125 ,  F01D25/16 ,  F01D25/18 ,  F02C3/107 ,  F02C7/14 ,  F05D2220/30 ,  F05D2260/20 ,  F05D2260/213 ,  F05D2260/40311 ,  F05D2260/98 ,  Y02T50/676

    Abstract: A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger, wherein the second lubricant circuit is fluidly separate from the first lubricant circuit. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second turbine engine component includes a bearing. The shaft is supported by the bearing and connected to one of the engine stages.

    Abstract translation: 涡轮发动机系统包括第一润滑剂回路，第二润滑剂回路，多个发动机级和轴。 第一润滑剂回路包括与第一润滑剂热交换器流体连接的第一涡轮发动机部件。 第二润滑剂回路包括与第二润滑剂热交换器流体连接的第二涡轮发动机部件，其中第二润滑剂回路与第一润滑剂回路流体分离。 第一涡轮发动机部件包括将第一发动机级与第二发动机级连接的齿轮系。 第二涡轮发动机部件包括轴承。 轴由轴承支撑并连接到其中一个发动机级。

    GEARED TURBOFAN WITH THREE TURBINE SECTIONS
    26.
    发明申请
    GEARED TURBOFAN WITH THREE TURBINE SECTIONS 审中-公开
    具有三个涡轮机部分的齿轮涡轮机

    公开(公告)号：WO2015112231A3

    公开(公告)日：2015-11-12

    申请号：PCT/US2014064490

    申请日：2014-11-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  STAUBACH JOSEPH BRENT

    IPC: F02C3/073 ,  F02K3/06

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

    Abstract: A gas turbine engine comprises a fan rotor configured to be driven by a fan drive turbine through a first shaft and a gear reduction. The fan rotor is configured to deliver air into a bypass duct as bypass air and to deliver core air flow into a core engine where it reaches an upstream compressor rotor. The upstream compressor rotor is configured to be driven through a second shaft by an intermediate turbine rotor. A downstream compressor rotor is configured to be driven by an upstream turbine rotor through a third shaft. An overall pressure ratio across the upstream and downstream compressor rotors is greater than or equal to about 35.0 and less than or equal to about 75.0.

    Abstract translation: 燃气涡轮发动机包括风扇转子，该风扇转子构造成由风扇驱动涡轮机通过第一轴和齿轮减速器驱动。 风扇转子被配置为将空气作为旁路空气输送到旁通管道中，并且将核心气流输送到核心发动机中，在那里它到达上游压缩机转子。 上游压缩机转子构造成通过中间涡轮机转子驱动通过第二轴。 下游压缩机转子构造成由上游涡轮转子通过第三轴驱动。 上游和下游压缩机转子之间的总压力比大于或等于约35.0且小于或等于约75.0。

    GAS TURBINE ENGINE FOR LONG RANGE AIRCRAFT
    27.
    发明申请
    GAS TURBINE ENGINE FOR LONG RANGE AIRCRAFT 审中-公开
    用于长距离飞机的燃气涡轮发动机

    公开(公告)号：WO2015116283A3

    公开(公告)日：2015-10-15

    申请号：PCT/US2014064477

    申请日：2014-11-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  SUCIU GABRIEL L

    IPC: F02K3/06 ,  F02C9/16 ,  F02K3/075

    CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2250/30 ,  F05D2260/40311

    Abstract: A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pressure ratio is defined across the upstream and downstream compressor rotors. A bypass ratio is defined as a volume of air delivered as bypass flow compared to a volume of air delivered into the core housing. The overall pressure ratio is greater than or equal to about 45.0, and the bypass ratio is greater than or equal to about 11.0.

    Abstract translation: 燃气涡轮发动机包括用于将空气作为旁路流输送到旁通管道的风扇，作为核心流动进入到芯壳体中，其中壳体包含上游压缩机转子和下游压缩机转子。 整个压力比定义在上游和下游的压缩机转子之间。 旁路比定义为与输送到芯壳体中的空气体积相比作为旁通流量输送的空气体积。 总压力比大于或等于约45.0，旁路比大于或等于约11.0。

    ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE
    28.
    发明申请
    ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE 审中-公开
    超高压比汽油涡轮发动机

    公开(公告)号：WO2015105594A3

    公开(公告)日：2015-10-15

    申请号：PCT/US2014067529

    申请日：2014-11-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  STAUBACH JOSEPH BRENT

    IPC: F02C3/04 ,  F02C3/06

    CPC classification number: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a first turbine positioned upstream of a second intermediate turbine and a third turbine positioned downstream of the first and second turbines. A fan and three compressors, with an upstream one of the compressors connected to rotate with the fan rotor, and the third turbine driving the upstream compressor and the fan both through a gear reduction. A second intermediate compressor is driven by the second intermediate turbine rotor, and a third compressor downstream of the first and second compressors is driven by the first turbine rotor.

    Abstract translation: 燃气涡轮发动机包括位于第二中间涡轮机上游的第一涡轮机和位于第一涡轮机和第二涡轮机下游的第三涡轮机。 一台风机和三台压缩机，上游的一台压缩机与风机转子连接在一起，第三台涡轮机通过减速机驱动上游压缩机和风机。 第二中间压缩机由第二中间涡轮转子驱动，并且第一和第二压缩机下游的第三压缩机由第一涡轮转子驱动。

    GEARED TURBOFAN ARRANGEMENT WITH CORE SPLIT POWER RATIO
    29.
    发明申请
    GEARED TURBOFAN ARRANGEMENT WITH CORE SPLIT POWER RATIO 审中-公开
    带有核心分体功率比的齿轮式齿盘装配

    公开(公告)号：WO2015112212A2

    公开(公告)日：2015-07-30

    申请号：PCT/US2014062764

    申请日：2014-10-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

    IPC: F02C3/107 ,  F02C7/36

    CPC classification number: F02C3/107 ,  F01D5/187 ,  F05D2300/606 ,  Y02T50/672 ,  Y02T50/676

    Abstract: A gas turbine engine includes a fan section and a compressor section. The compressor section includes both a first compressor section and a second compressor section. A turbine section includes at least one turbine and driving the second compressor section and a fan drive turbine driving at least a gear arrangement to drive the fan section. A power ratio is provided by the combination of the first compressor section and the second compressor section, with the power ratio being provided by a first power input to the first compressor section and a second power input to the second compressor section, the power ratio being equal to, or greater than, about 1.0 and less than, or equal to, about 1.4.

    Abstract translation: 燃气涡轮发动机包括风扇部分和压缩机部分。 压缩机部分包括第一压缩机部分和第二压缩机部分两者。 涡轮机部分包括至少一个涡轮机并且驱动第二压缩机部分，并且风扇驱动涡轮机驱动至少一个齿轮装置以驱动风扇部分。 功率比由第一压缩机部分和第二压缩机部分的组合提供，功率比由输入到第一压缩机部分的第一功率和输入到第二压缩机部分的第二功率提供，功率比是 等于或大于约1.0且小于或等于约1.4。

    HIGH THRUST GEARED GAS TURBINE ENGINE
    30.
    发明申请
    HIGH THRUST GEARED GAS TURBINE ENGINE 审中-公开
    高扭矩气动涡轮发动机

    公开(公告)号：WO2015050619A2

    公开(公告)日：2015-04-09

    申请号：PCT/US2014046781

    申请日：2014-07-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  HASEL KARL L ,  MERRY BRIAN D

    IPC: F02C7/00 ,  F02C7/32

    CPC classification number: F02C3/06 ,  F01D5/14 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2240/303 ,  F05D2240/307 ,  F05D2260/40311 ,  F16H1/28

    Abstract: A ratio of an outer diameter of a fan hub at a leading edge of the blades to an outer tip diameter of the blades at the leading edge is greater than or equal to about 0.24 and less than or equal to about 0.38. The fan tip diameter is greater than or equal to about 84 inches (213.36 centimeters) and a fan tip speed is less than or equal to about 1050 ft / second (320.04 meters / second). A bypass ratio, a gear ratio and an AN2 value are also claimed. The fan drive turbine has between three and six stages.

    Abstract translation: 在叶片的前缘处的风扇轮毂的外径与前缘处的叶片的外端直径的比率大于或等于约0.24且小于或等于约0.38。 风扇叶尖直径大于或等于约84英寸（213.36厘米），风扇叶尖速度小于或等于约1050英尺/秒（320.04米/秒）。 还要求旁路比，齿轮比和AN2值。 风扇驱动涡轮机有三到六级。

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