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    GAS TURBINE ENGINE WITH GEARED TURBOFAN AND OIL THERMAL MANAGEMENT SYSTEM WITH UNIQUE HEAT EXCHANGER STRUCTURE
    2.
    发明申请
    GAS TURBINE ENGINE WITH GEARED TURBOFAN AND OIL THERMAL MANAGEMENT SYSTEM WITH UNIQUE HEAT EXCHANGER STRUCTURE 审中-公开
    具有特殊热交换器结构的带齿轮涡轮机和油热管理系统的气体涡轮发动机

    公开(公告)号：US20150361887A1

    公开(公告)日：2015-12-17

    申请号：US14761427

    申请日：2014-03-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Ethan K. Stearns ,  Jorn A. Glahn ,  Daniel J. McKaveney

    IPC: F02C7/06

    CPC classification number: F02C7/06 ,  F02C3/32 ,  F02C7/14 ,  F02C7/224 ,  F02C7/36 ,  F02C9/18 ,  F05D2260/213 ,  F05D2260/601 ,  Y02T50/676

    Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.

    Abstract translation: 用于燃气涡轮发动机的供油系统具有向出口管线输送润滑剂的润滑剂泵。 出口管线被分成至少一个热管线并进入冷却管线，热管线主要指向与不用于接收较冷润滑剂的发动机相关联的位置，并且冷管线通过一个或多个热交换器引导 哪种润滑剂被冷却。 然后，冷线路路由到相关联的燃气涡轮发动机的风扇驱动齿轮系统。 公开了一种方法和装置。 热交换器至少包括空气/油冷却器，其中空气被拉过空气/油冷却器以冷却油。 空气/油冷却器设置有从压缩机部分抽出压缩空气的喷射器，以增加空气/油冷却器的气流。

    GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM
    3.
    发明申请
    GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM 审中-公开
    气体涡轮发动机热管理系统

    公开(公告)号：US20140360153A1

    公开(公告)日：2014-12-11

    申请号：US14247575

    申请日：2014-04-08

    Applicant: United Technologies Corporation

    Inventor： Federico Papa ,  Thomas G. Phillips ,  Kathleen R. Phillips ,  Ethan K. Stearns ,  Justin W. Heiss

    IPC: F02C7/12 ,  F02C7/224 ,  G05D7/06 ,  F02C9/48 ,  F02C7/06 ,  G05B15/02 ,  F02C3/08 ,  F02C7/232

    CPC classification number: F02C7/12 ,  F01D25/12 ,  F02C3/08 ,  F02C7/06 ,  F02C7/08 ,  F02C7/14 ,  F02C7/224 ,  F02C7/232 ,  F02C9/00 ,  F02C9/48 ,  F05D2220/32 ,  F05D2260/213 ,  G05B15/02 ,  G05D7/06 ,  Y02T50/675

    Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan. A turbine section is configured for driving the geared architecture. A thermal management system that includes a first fluid circuit and a second fluid circuit that manage heat generated in at least a portion of the gas turbine engine. A first heat exchanger is incorporated into each of the first fluid circuit and the second fluid circuit. A second heat exchanger is incorporated into the first fluid circuit. A valve controls an amount of a first fluid that is communicated to the first heat exchanger and the second heat exchanger. A controller is configured to control a positioning of the valve. The amount of the first fluid communicated to the first heat exchanger is based on a first characteristic of a second fluid and the amount of the first fluid communicated to the second heat exchanger is based on a second characteristic of the second fluid. A method and a system are also disclosed.

    Abstract translation: 根据本公开的示例性实施例的燃气涡轮发动机以及其它可能的事情包括风扇。 齿轮架构配置为驱动风扇。 涡轮机部分被配置用于驱动齿轮架构。 一种热管理系统，其包括第一流体回路和第二流体回路，其管理在燃气涡轮发动机的至少一部分中产生的热量。 第一热交换器被并入到第一流体回路和第二流体回路的每一个中。 第二热交换器被并入到第一流体回路中。 阀门控制与第一热交换器和第二热交换器连通的第一流体的量。 控制器被配置为控制阀的定位。 与第一热交换器连通的第一流体的量基于第二流体的第一特性，并且与第二热交换器连通的第一流体的量基于第二流体的第二特性。 还公开了一种方法和系统。

    GAS TURBINE ENGINE WITH GEARED TURBOFAN AND OIL THERMAL MANAGEMENT SYSTEM
    4.
    发明申请
    GAS TURBINE ENGINE WITH GEARED TURBOFAN AND OIL THERMAL MANAGEMENT SYSTEM 审中-公开
    燃气涡轮发动机与齿轮涡轮和油热管理系统

    公开(公告)号：US20140216003A1

    公开(公告)日：2014-08-07

    申请号：US14245317

    申请日：2014-04-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Kathleen R. Phillips ,  Thomas G. Phillips ,  Ethan K. Stearns ,  Federico Papa

    IPC: F01D25/20 ,  F02C7/06

    CPC classification number: F01D25/20 ,  F01D25/18 ,  F01M5/002 ,  F02C7/06 ,  F02C7/14 ,  F02K9/64 ,  F05D2260/213 ,  F05D2260/40311 ,  Y02T50/676

    Abstract: A gas turbine engine includes a fan, a compressor section, a combustion section, and a turbine section. A fan drive gear system is configured for driving the fan at a speed different than the turbine section. A lubricant system includes a lubricant pump delivering lubricant to an outlet line. The outlet line splits into at least a hot line and into a cool line. The hot line is directed primarily to locations in the gas turbine engine that are not intended to receive cooler lubricant. The cool line is directed through one or more heat exchangers at which the lubricant is cooled, and the cool line then is routed to the fan drive gear system. At least one of the one or more heat exchangers is a fuel/oil cooler at which lubricant will be cooled by fuel leading to the combustion section. The fuel/oil cooler is downstream of a point where the outlet line splits into the at least the hot line and the cool line, such that the hot line is not directed through the fuel/oil cooler. A method is also disclosed.

    Abstract translation: 燃气涡轮发动机包括风扇，压缩机部，燃烧部和涡轮部。 风扇驱动齿轮系统构造成以不同于涡轮部分的速度驱动风扇。 润滑剂系统包括将润滑剂输送到出口管线的润滑剂泵。 出口线分成至少一条热线，并进入冷线。 热线主要针对燃气涡轮发动机中不用于接收较冷润滑剂的位置。 冷却管线被引导通过一个或多个热交换器，在该热交换器处润滑剂被冷却，然后将冷却管线路由到风扇驱动齿轮系统。 一个或多个热交换器中的至少一个是燃料/油冷却器，在该燃料/油冷却器处，通过燃料通向燃烧部分的润滑剂将被冷却。 燃料/油冷却器在出口管线分成至少热管线和冷却管线的点的下游，使得热管线不被引导通过燃料/油冷却器。 还公开了一种方法。

    AIR OIL COOLER AIRFLOW AUGMENTATION SYSTEM
    5.
    发明申请
    AIR OIL COOLER AIRFLOW AUGMENTATION SYSTEM 审中-公开

    公开(公告)号：US20190170016A1

    公开(公告)日：2019-06-06

    申请号：US16266948

    申请日：2019-02-04

    Applicant: United Technologies Corporation

    Inventor： Ethan K. Stearns ,  John Axel Glahn ,  Daniel J. McKaveney

    IPC: F01D25/20 ,  F01D25/12 ,  F02C7/224 ,  F02C7/18 ,  F01M1/12 ,  F02C7/06 ,  F02C7/14 ,  F02C9/18 ,  F01D25/18

    Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.

    TECHNIQUE FOR OPTIMIZING ENGINE PERFORMANCE USING FUEL TEMPERATURE
    6.
    发明申请
    TECHNIQUE FOR OPTIMIZING ENGINE PERFORMANCE USING FUEL TEMPERATURE 有权
    使用燃料温度优化发动机性能的技术

    公开(公告)号：US20160332743A1

    公开(公告)日：2016-11-17

    申请号：US15112648

    申请日：2014-10-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Matthew D. Teicholz ,  Ethan K. Stearns

    IPC: B64D37/34 ,  B64D27/10 ,  F02C9/28 ,  F02C7/22 ,  F02C7/14

    CPC classification number: B64D37/34 ,  B64D27/10 ,  F02C7/06 ,  F02C7/14 ,  F02C7/22 ,  F02C7/224 ,  F02C9/28 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2270/20 ,  F05D2270/313 ,  Y02T50/675

    Abstract: A method of protecting fuel hardware for a gas turbine engine in an aircraft is disclosed. The method may include determining a current altitude of the aircraft, and controlling a temperature of fuel for the gas turbine engine based at least in part on the current altitude. A thermal management system for a gas turbine engine in an aircraft is also disclosed. The thermal management system may include a sensor configured to detect a current altitude of the aircraft, and a controller in operative communication with the sensor. The controller may be configured to manage a fuel temperature for the gas turbine engine based at least in part on the current altitude detected by the sensor.

    Abstract translation: 公开了一种保护飞机中的燃气涡轮发动机的燃料硬件的方法。 该方法可以包括确定飞行器的当前高度，以及至少部分地基于当前高度来控制燃气涡轮发动机的燃料的温度。 还公开了一种用于飞机中的燃气涡轮发动机的热管理系统。 热管理系统可以包括被配置为检测飞行器的当前高度的传感器，以及与传感器可操作地通信的控制器。 控制器可以被配置为至少部分地基于由传感器检测到的当前高度来管理燃气涡轮发动机的燃料温度。

    Air oil cooler airflow augmentation system
    9.
    发明授权
    Air oil cooler airflow augmentation system 有权

    公开(公告)号：US10196936B2

    公开(公告)日：2019-02-05

    申请号：US14774412

    申请日：2014-03-14

    Applicant: United Technologies Corporation

    Inventor： Ethan K. Stearns ,  Jorn A. Glahn ,  Daniel J. McKaveney

    IPC: F01D25/18 ,  F01D25/20 ,  F02C7/224 ,  F02C7/18 ,  F01M1/12 ,  F02C7/06 ,  F02C7/14 ,  F02C9/18 ,  F01D25/12

    Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.

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