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    MULTI-CIRCUIT LUBRICATION SYSTEM FOR A TURBINE ENGINE
    61.
    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：US20150369082A1

    公开(公告)日：2015-12-24

    申请号：US14765211

    申请日：2014-02-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Simon Pickford

    IPC: F01D25/20 ,  F01D25/08 ,  F01D15/10 ,  F01D15/12 ,  F01D1/02 ,  F01D25/16

    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。

    Modifying Direct Drive Gas Turbine Engine Core to Provide a Geared Turbofan
    62.
    发明申请
    Modifying Direct Drive Gas Turbine Engine Core to Provide a Geared Turbofan 审中-公开
    改装直接驱动燃气轮机发动机内核，提供齿轮式涡轮风扇

    公开(公告)号：US20150361921A1

    公开(公告)日：2015-12-17

    申请号：US14711861

    申请日：2015-05-14

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Joseph Brent Staubach

    IPC: F02K3/02 ,  F02K3/075 ,  F02K3/065

    CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2230/80 ,  F05D2260/4031 ,  Y10T29/49323 ,  Y10T29/49718

    Abstract: A method comprises the steps of modifying a direct drive engine, which includes a first fan rotor, a high pressure compressor driven by a high pressure turbine on a first high spool and a first low pressure turbine designed to drive a first low pressure compressor on a first low spool, and the fan rotor all at the same speed. The modifying step includes providing a second fan rotor, second low spool, including a second low pressure compressor rotor and second low pressure turbine rotor and incorporating a gear reduction between a shaft driven by the second low pressure turbine rotor and the second fan rotor to provide a geared turbofan, such that at least a portion of the design of the high pressure compressor rotor, the combustor and the high pressure turbine rotor from the designed direct drive engine are utilized in the geared turbofan. A gas turbine engine is also disclosed.

    Abstract translation: 一种方法包括以下步骤：修改直接驱动发动机，其包括第一风扇转子，由第一高阀芯上的高压涡轮机驱动的高压压缩机和设计成驱动第一低压压缩机的第一低压涡轮机 第一个低阀芯，风扇转子全部以相同的速度。 修改步骤包括提供第二风扇转子，第二低阀芯，包括第二低压压缩机转子和第二低压涡轮转子，并且在由第二低压涡轮转子驱动的轴和第二风扇转子之间并入减速齿轮，以提供 齿轮式涡扇，使得来自设计的直接驱动发动机的高压压缩机转子，燃烧器和高压涡轮机转子的设计的至少一部分被用于齿轮传动风扇。 还公开了一种燃气涡轮发动机。

    MULTI-CIRCUIT LUBRICATION SYSTEM FOR A TURBINE ENGINE
    64.
    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：US20150361811A1

    公开(公告)日：2015-12-17

    申请号：US14765217

    申请日：2014-02-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Simon Pickford

    IPC: F01D9/06 ,  F01D25/18

    CPC classification number: F01D9/065 ,  F01D25/18 ,  F02C7/06 ,  F02C7/14 ,  F05D2260/213 ,  F05D2260/40311 ,  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 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 lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger. The second lubricant circuit is fluidly coupled with the first lubricant circuit, and 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。 第二润滑剂回路与第一润滑剂回路流体联接，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 GAS TURBINE ENGINE ARCHITECTURE
    66.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开
    齿轮涡轮发动机涡轮发动机结构

    公开(公告)号：US20150330302A1

    公开(公告)日：2015-11-19

    申请号：US14789300

    申请日：2015-07-01

    Applicant: United Technologies Corporation

    Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

    IPC: F02C3/107 ,  F02C7/06

    CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D9/02 ,  F01D9/065 ,  F02C3/04 ,  F02C3/107 ,  F02C3/36 ,  F02C7/06 ,  F02C9/18 ,  F02K1/78 ,  F02K3/04 ,  F02K3/06 ,  F02K3/072 ,  F04D27/009 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

    Abstract translation: 燃气涡轮发动机通常包括风扇部分，压缩机部分，燃烧器部分和涡轮部分。 可以使用诸如行星齿轮组件的减速装置来驱动风扇部分，使得风扇部分可以以不同于涡轮机部分的速度旋转，从而增加发动机的整体推进效率。 在这样的发动机结构中，由一个涡轮机部分驱动的轴为行星齿轮组件提供输入，该输入齿轮组件以不同于涡轮机部分的速度驱动风扇部分，使得涡轮部分和风扇部分可以更接近 最佳速度通过所述和所公开的燃气涡轮发动机的各种部件的公开特征的期望组合来提供增加的性能属性和性能。

    GEARED TURBINE ENGINE WITH RELATIVELY LIGHTWEIGHT PROPULSOR MODULE
    67.
    发明申请
    GEARED TURBINE ENGINE WITH RELATIVELY LIGHTWEIGHT PROPULSOR MODULE 审中-公开
    具有相对轻型推进器模块的齿轮式涡轮发动机

    公开(公告)号：US20150252730A1

    公开(公告)日：2015-09-10

    申请号：US14432377

    申请日：2013-02-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C7/36 ,  F02C3/10

    CPC classification number: F02C7/36 ,  F02C3/10 ,  F02C3/107 ,  F02C7/20 ,  F02C7/32 ,  F05D2220/36 ,  F05D2260/40311 ,  Y02T50/672 ,  Y10T29/49321

    Abstract: An example gas turbine engine includes a propulsor assembly including at least a fan module and a fan drive turbine module; a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a turbine in fluid communication with the combustor; and a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module. A weight of the fan module and the fan drive turbine module is less than about 40% of a total weight of a gas turbine engine.

    Abstract translation: 示例性燃气涡轮发动机包括至少包括风扇模块和风扇驱动涡轮机模块的推进器组件; 气体发生器组件，其至少包括压缩机部分，与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮机; 以及由风扇驱动涡轮机模块驱动的用于旋转风扇模块的风扇的齿轮架构。 风扇模块和风扇驱动涡轮模块的重量小于燃气涡轮发动机总重量的约40％。

    Compressor Areas For High Overall Pressure Ratio Gas Turbine Engine
    68.
    发明申请
    Compressor Areas For High Overall Pressure Ratio Gas Turbine Engine 审中-公开
    用于高总压比燃气轮机发动机的压缩机区域

    公开(公告)号：US20150252723A1

    公开(公告)日：2015-09-10

    申请号：US14620395

    申请日：2015-02-12

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Stephen G. Pixton

    IPC: F02C3/107 ,  F02C7/36

    CPC classification number: F02C3/107 ,  F02C3/067 ,  F02C7/36 ,  F05D2250/44 ,  F05D2260/4031

    Abstract: A gas turbine engine comprises a high pressure turbine rotor, an intermediate pressure turbine rotor and a fan drive turbine rotor. The fan drive turbine rotor drives a fan rotor through a gear reduction. The intermediate pressure rotor drives a low pressure compressor rotor and the high pressure turbine rotor drives a high pressure compressor rotor. A first flow cross-sectional area is between an outer periphery of a hub in the low pressure compressor rotor, and an outer tip of an upstream most blade row of the low pressure compressor rotor. A second flow cross-sectional area is between an outer periphery of a hub in the high pressure compressor rotor, and an outer tip of an upstream most blade row of the high pressure compressor rotor. A ratio of the first and second flow cross-sectional areas is greater than or equal to about 0.12 and less than or equal to about 0.33.

    Abstract translation: 燃气涡轮发动机包括高压涡轮转子，中压涡轮转子和风扇驱动涡轮转子。 风扇驱动涡轮转子通过齿轮减速驱动风扇转子。 中压转子驱动低压压缩机转子，高压涡轮转子驱动高压压缩机转子。 第一流动横截面积在低压压缩机转子中的轮毂的外周与低压压缩机转子的最上游叶片排的外端之间。 第二流动横截面积在高压压缩机转子中的轮毂的外周与高压压缩机转子的最上游叶片排的外端之间。 第一和第二流动横截面积的比率大于或等于约0.12且小于或等于约0.33。

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    70.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开

    公开(公告)号：US20150192070A1

    公开(公告)日：2015-07-09

    申请号：US14662459

    申请日：2015-03-19

    Applicant: United Technologies Corporation

    Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

    IPC: F02C7/32 ,  F02K3/02

    CPC classification number: F02C7/32 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F05D2240/12 ,  F05D2240/129 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

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