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    Resistive-inductive de-icing of aircraft flight control surfaces
    71.
    发明授权
    Resistive-inductive de-icing of aircraft flight control surfaces 有权
    飞机飞行控制表面的电阻感应除冰

    公开(公告)号：US09457909B2

    公开(公告)日：2016-10-04

    申请号：US13870403

    申请日：2013-04-25

    Applicant: Hamilton Sundstrand Corporation

    Inventor： Lubomir A. Ribarov ,  Jacek F. Gieras

    IPC: B64D15/12 ,  B64D15/14 ,  B64D15/00

    CPC classification number: B64D15/12 ,  B64D15/00 ,  B64D15/14

    Abstract: Embodiments of the disclosure include a de-icing system for an aircraft. The de-icing system includes a plurality of resistive-inductive heating elements inserted adjacent to a flight control surface and a controller configured to provide a supply current to each of the plurality of resistive-inductive heating elements. Each of the plurality of resistive-inductive heating elements produces an electromagnetic field normal to the flight control surfaces and resistive heat in response to the supply current. The electromagnetic field induces an eddy current in the flight control surface.

    Abstract translation: 本公开的实施例包括用于飞行器的除冰系统。 除冰系统包括与飞行控制表面相邻地插入的多个电阻感应加热元件和被配置为向多个电阻感应加热元件中的每一个提供电源电流的控制器。 多个电阻感应加热元件中的每一个响应于电源电流产生垂直于飞行控制表面的电磁场和电阻热。 电磁场在飞行控制表面中产生涡流。

    COMPACT HEAT EXCHANGER
    72.
    发明申请
    COMPACT HEAT EXCHANGER 审中-公开
    紧凑型热交换器

    公开(公告)号：US20160282061A1

    公开(公告)日：2016-09-29

    申请号：US14669202

    申请日：2015-03-26

    Applicant: HAMILTON SUNDSTRAND CORPORATION

    Inventor： Leo J. Veilleux, JR. ,  Lubomir A. Ribarov

    IPC: F28F9/02 ,  B23P15/26

    CPC classification number: B23P15/26 ,  B22F3/1055 ,  B22F5/106 ,  B29C64/153 ,  B33Y10/00 ,  B33Y80/00 ,  F28D7/0066 ,  F28D2021/0021 ,  F28F1/04 ,  F28F7/02 ,  F28F2260/02 ,  Y02P10/295

    Abstract: A compact heat exchanger is provided and includes a first manifold defining an inlet for receiving from a component a fluid to be cooled and an outlet for returning the cooled fluid to the component to cool the component. A second manifold is disposed spaced from the first manifold. A core extends between and fluidly communicates with the manifolds and includes hexagonal channels. Each channel is formed by mini-tubes defining respective triangular passages. A cross-section of the core defines an irregular-cross structure. The fluid enters the inlet of the first manifold, makes a first pass through the mini-tubes to the second manifold, makes a second pass through the mini-tubes to the first manifold such that the fluid is cooled across the mini-tubes, exits the first manifold through the outlet, and returns to the component to cool the component. A method of manufacturing the heat exchanger is provided also.

    Abstract translation: 提供了紧凑的热交换器，并且包括限定用于从部件接收待冷却的流体的入口的第一歧管和用于将冷却的流体返回到部件以冷却部件的出口。 第二歧管与第一歧管间隔设置。 芯部与歧管之间延伸并与流体连通并且包括六边形通道。 每个通道由限定相应的三角形通道的微型管形成。 芯的横截面限定了不规则交叉结构。 流体进入第一歧管的入口，首先通过微型管到第二歧管，使第二通过微型管到第一歧管，使得流体在微型管，出口 通过出口的第一个歧管，并返回到组件以冷却组件。 还提供制造热交换器的方法。

    RESISTIVE-INDUCTIVE PROPELLER BLADE DE-ICING SYSTEM INCLUDING CONTACTLESS POWER SUPPLY
    73.
    发明申请
    RESISTIVE-INDUCTIVE PROPELLER BLADE DE-ICING SYSTEM INCLUDING CONTACTLESS POWER SUPPLY 有权
    电阻式螺旋叶片除尘系统，包括无连接电源

    公开(公告)号：US20150260047A1

    公开(公告)日：2015-09-17

    申请号：US14203813

    申请日：2014-03-11

    Applicant: HAMILTON SUNDSTRAND CORPORATION

    Inventor： Jacek F. Gieras ,  Lubomir A. Ribarov

    IPC: F01D5/18 ,  H05B1/02

    CPC classification number: F01D5/18 ,  B64C11/00 ,  B64D15/12 ,  H05B1/0236 ,  H05B6/105 ,  H05B2214/02

    Abstract: An aircraft propeller de-icing system comprises at least one propeller blade coupled to a rotatable prop assembly. The prop assembly is configured to rotate in response to rotatably driving a propeller shaft. At least one resistive-inductive heating unit is coupled to the at least one propeller blade. The resistive-inductive heating unit is configured to generate eddy currents that induce inductive heat in response to an electric current. A contactless power transfer system generates the electrical current in response to transferring power across an air gap separating the propeller shaft from the contactless power transfer system.

    Abstract translation: 飞机螺旋桨除冰系统包括联接到可旋转支架组件的至少一个螺旋桨叶片。 支架组件构造成响应于可旋转地驱动螺旋桨轴而旋转。 至少一个电阻感应加热单元联接到所述至少一个螺旋桨叶片。 电阻感应加热单元被配置为产生响应于电流而感应感应热的涡流。 非接触式动力传递系统响应于将传动轴与非接触式动力传递系统分离的气隙传递动力而产生电流。

    FLUID COOLING ARRANGEMENT FOR A GAS TURBINE ENGINE AND METHOD
    74.
    发明申请
    FLUID COOLING ARRANGEMENT FOR A GAS TURBINE ENGINE AND METHOD 有权
    用于气体涡轮发动机的流体冷却装置和方法

    公开(公告)号：US20150023776A1

    公开(公告)日：2015-01-22

    申请号：US13945070

    申请日：2013-07-18

    Applicant: Hamilton Sundstrand Corporation

    Inventor： Lubomir A. Ribarov ,  James S. Elder ,  Leo J. Veilleux, JR.

    IPC: F01D25/14

    CPC classification number: F01D9/065 ,  F01D25/162 ,  F02C7/14 ,  F05D2250/185 ,  Y02T50/672 ,  Y02T50/675

    Abstract: A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path. Further included is at least one strut operatively coupling the inner structure to the outer structure. Yet further included is at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut.

    Abstract translation: 用于航空航天推进的燃气涡轮发动机中的流体冷却装置包括内部结构。 还包括设置在内部结构的径向外侧的外部结构，外部结构和内部结构限定旁路流动路径。 还包括至少一个支柱，其可操作地将内部结构联接到外部结构。 还包括至少一个形成在所述至少一个支柱内的冷却管，所述至少一个冷却管构造成当空气通过所述至少一个支柱时对所述至少一个支柱进行对流冷却时，冷却通过所述至少一个冷却管的流体 旁路流路和至少一个支柱上。

    ENERGY RECOVERY AND REGENERATION SYSTEM
    75.
    发明申请
    ENERGY RECOVERY AND REGENERATION SYSTEM 审中-公开
    能源回收和再生系统

    公开(公告)号：US20140360547A1

    公开(公告)日：2014-12-11

    申请号：US13911687

    申请日：2013-06-06

    Applicant: Hamilton Sundstrand Corporation

    Inventor： Lubomir A. Ribarov

    IPC: B60L11/18 ,  H01L35/30 ,  H01L37/02

    CPC classification number: H01L35/30 ,  B60L53/00 ,  B64D41/00 ,  H01L37/02 ,  H02N2/186 ,  Y02T50/53

    Abstract: In at least one embodiment, an energy recovery and regeneration system includes at least one pyroelectric energy recovery module (ERM), a coolant line, a valve and an energy storage module. The at least one pyroelectric ERM generates a voltage in response to realizing a temperature change. The coolant line includes a first end in fluid communication with a coolant source to receive a coolant and a second end disposed adjacent the at least one pyroelectric ERM to deliver the coolant thereto. The valve is interposed between the coolant source and the at least one pyroelectric ERM. The valve modulates the coolant delivered to the at least one pyroelectric ERM to generate the temperate change. The energy storage module is in electrical communication with the pyroelectric ERM to store the voltage generated by the at least one pyroelectric ERM.

    Abstract translation: 在至少一个实施例中，能量回收和再生系统包括至少一个热释电能量回收模块（ERM），冷却剂管线，阀门和能量储存模块。 响应于实现温度变化，至少一个热释电ERM产生电压。 冷却剂管线包括与冷却剂源流体连通以接收冷却剂的第一端和邻近所述至少一个热释电ERM设置以将冷却剂输送到其上的第二端。 阀被插入在冷却剂源和至少一个热释电ERM之间。 阀调节输送到至少一个热释电ERM的冷却剂以产生温和变化。 能量存储模块与热电ERM电连通以存储由至少一个热释电ERM产生的电压。

    Heat exchanger
    77.
    发明授权
    Heat exchanger 有权

    公开(公告)号：US11199365B2

    公开(公告)日：2021-12-14

    申请号：US14531376

    申请日：2014-11-03

    Applicant: HAMILTON SUNDSTRAND CORPORATION

    Inventor： James S. Elder ,  Leo J. Veilleux, Jr. ,  Lubomir A. Ribarov

    IPC: F28D9/00 ,  B64C13/00

    Abstract: An air to air heat exchanger is provided including a core having a plurality of alternately stacked first layers and second layers. Each first layer includes a plurality of first modules having corrugated fins that define a plurality of first fluid flow paths. The first modules are aligned to fluidly couple the first fluid flow paths. Each second layer includes at least one second module having corrugated fins that define a plurality of second fluid flow paths. At least one second layer includes a third module having a plurality of corrugated fins that define a plurality of third fluid flow paths. The third module is arranged such that the third fluid flow paths are parallel to the second fluid flow paths. A number of corrugated fins formed in the third module is less than a number of corrugated fins formed in the second module.

    Generators with open loop active cooling
    80.
    发明授权
    Generators with open loop active cooling 有权

    公开(公告)号：US10587170B2

    公开(公告)日：2020-03-10

    申请号：US15925985

    申请日：2018-03-20

    Applicant: Hamilton Sundstrand Corporation

    Inventor： Lubomir A. Ribarov ,  Robert Scott Downing ,  Richard A. Himmelmann

    IPC: H02K9/00 ,  H02K9/197 ,  H02K1/32 ,  H02K9/19

    Abstract: A rotor body for a high-speed generator includes a rotor body with interior and exterior surfaces, a coolant inlet and outlet, and a rotor cooling path for actively cooling the rotor body. The coolant inlet and outlet extend between the interior and exterior surfaces. An interior segment of the rotor cooling path fluidly couples the coolant inlet and coolant outlet and is bounded by the rotor body interior surface. An exterior segment of the cooling path is bounded by the rotor body exterior surface and fluidly couples the coolant outlet an environment external to the rotor body.

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