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110 条记录 (耗时 0.016 秒)

    ADDITIVE MANUFACTURE OF TURBINE COMPONENT WITH MULTIPLE MATERIALS
    11.
    发明申请
    ADDITIVE MANUFACTURE OF TURBINE COMPONENT WITH MULTIPLE MATERIALS 审中-公开
    涡轮组件与多种材料的补充制造

    公开(公告)号：US20140099476A1

    公开(公告)日：2014-04-10

    申请号：US14043037

    申请日：2013-10-01

    申请人： Ramesh Subramanian ,  Michael Ott ,  Dimitrios Thomaidis ,  Alexandr Sadovoy ,  Jan Münzer

    发明人： Ramesh Subramanian ,  Michael Ott ,  Dimitrios Thomaidis ,  Alexandr Sadovoy ,  Jan Münzer

    IPC分类号： B22F7/02

    CPC分类号： B22F7/02 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F7/06 ,  B22F2003/1057 ,  B22F2999/00 ,  B23K26/342 ,  B28B1/001 ,  B28B1/008 ,  B29C64/153 ,  B33Y10/00 ,  F01D5/00 ,  F01D5/288 ,  F05D2230/31 ,  Y02P10/295 ,  Y10T428/24545 ,  B22F2203/00 ,  B22F2207/01

    摘要： A method for additive manufacturing with multiple materials. First (48), second (50), and third (52) adjacent powder layers are delivered onto a working surface (54A) in respective first (73), second (74), and third (75) area shapes of adjacent final materials (30, 44, 45) in a given section plane of a component (20). The first powder may be a structural metal delivered in the sectional shape of an airfoil substrate (30). The second powder may be a bond coat material delivered in a sectional shape of a bond coat (45) on the substrate. The third powder may be a thermal barrier ceramic delivered in a section shape of the thermal barrier coating (44). A particular laser intensity (69A, 69B) is applied to each layer to melt or to sinter the layer. Integrated interfaces (57, 77, 80) may be formed between adjacent layers by gradient material overlap and/or interleaving projections.

    摘要翻译： 一种多种材料添加剂制造方法。 第一（48），第二（50）和第三（52）相邻粉末层在相邻最终材料的相应的第一（73），第二（74）和第三（75）区域形状中被输送到工作表面（54A） （30,44,45）在组件（20）的给定截面中。 第一粉末可以是以翼型基材（30）的截面形状输送的结构金属。 第二粉末可以是在衬底上以接合涂层（45）的截面形状递送的粘合涂层材料。 第三粉末可以是以隔热涂层（44）的截面形式输送的热障陶瓷。 将特定的激光强度（69A，69B）施加到每层以熔化或烧结该层。 集成接口（57,77,80）可以通过梯度材料重叠和/或交错突起在相邻层之间形成。

    ROTATING STALL DETECTION USING OPTICAL MEASUREMENT OF BLADE UNTWIST
    12.
    发明申请
    ROTATING STALL DETECTION USING OPTICAL MEASUREMENT OF BLADE UNTWIST 有权
    使用光学测量刀片的旋转台架检测

    公开(公告)号：US20140023498A1

    公开(公告)日：2014-01-23

    申请号：US13936561

    申请日：2013-07-08

    申请人： Prime Photonics, LC

    发明人： Daniel Kominsky

    IPC分类号： F01D5/00

    CPC分类号： F01D5/00 ,  F01D17/02 ,  F01D21/003 ,  F05D2260/80 ,  F05D2270/101 ,  F05D2270/804 ,  G01N21/553 ,  G01N21/554 ,  Y02T50/671

    摘要： Systems and methods are provided for real-time detection of the onset of stall in turbomachinery, such as compressor stall. The methods are capable of detecting and analyzing time of arrival of the chord of the blade at a sensor array to provide an indication of the onset of compressor stall. Systems for detecting the onset of compressor stall include: light sources; a plurality of linearly arranged optical fibers for transmitting light from the light sources and for receiving transmitted light reflected from a blade; a detector for measuring intensity of the reflected light; and a processor for analyzing the intensity of the reflected light to determine blade twist angle and from the blade twist angle identify onset of compressor stall. The invention can prevent the needless loss of life and assets caused by compressor stall that may lead to unexpected catastrophic failure of an engine.

    摘要翻译： 提供了系统和方法，用于实时检测涡轮机械中失速的发生，如压缩机失速。 这些方法能够检测和分析在传感器阵列处的叶片的到达时间，以提供压缩机失速开始的指示。 用于检测压缩机失速发生的系统包括：光源; 多个线性布置的光纤，用于从光源透射光并接收从叶片反射的透射光; 用于测量反射光强度的检测器; 以及用于分析反射光强度以确定叶片扭转角度和从叶片扭转角度识别压缩机失速开始的处理器。 本发明可以防止由压缩机失速引起的不必要的人身伤害和资产损失，这可能导致发动机意外的灾难性故障。

    VENTILATION DEVICE FOR GENERATING UNIFORM FLUID FLOWS, AND A DRIVE UNIT FOR A DEVICE OF SAID TYPE
    13.
    发明申请
    VENTILATION DEVICE FOR GENERATING UNIFORM FLUID FLOWS, AND A DRIVE UNIT FOR A DEVICE OF SAID TYPE 审中-公开
    用于产生均匀流体流动的通风装置和用于装置类型的装置的驱动装置

    公开(公告)号：US20130280069A1

    公开(公告)日：2013-10-24

    申请号：US13996332

    申请日：2011-12-16

    申请人： Reto Böhlen ,  Marcel Frikart

    发明人： Reto Böhlen ,  Marcel Frikart

    IPC分类号： F01D5/00

    CPC分类号： F01D5/00 ,  F04D33/00

    摘要： A device according to the present disclosure (60) for generating a directed fluid flow comprises a support structure (1); a rotary structure (5) disposed in relation to the support structure so as to be rotatable around a first axis of rotation (10); and at least one active element (61, 61′) disposed on the rotary structure (5) so as to be rotatable around a second axis of rotation (9,9′), and which has an active surface (67). The at least one active element is rotatably connected to the rotary structure and the support structure such that, when the rotary structure rotates in relation to the support structure by one revolution around the first axis of rotation in a first direction of rotation, the at least one active element rotates in relation to the rotary structure by half of one revolution around the second axis of rotation in the opposite direction of rotation.

    摘要翻译： 根据本公开（60）的用于产生定向流体流的装置包括支撑结构（1）; 相对于所述支撑结构设置成能够围绕第一旋转轴线（10）旋转的旋转结构（5）; 以及设置在所述旋转结构（5）上的至少一个有源元件（61,61'），以便能够围绕第二旋转轴线（9,9'）旋转，并且具有活动表面（67）。 所述至少一个有源元件可旋转地连接到所述旋转结构和所述支撑结构，使得当所述旋转结构相对于所述支撑结构在第一旋转方向围绕所述第一旋转轴旋转一周时，所述至少一个 一个有源元件相对于旋转结构在相反的旋转方向围绕第二旋转轴旋转一圈。

    Methods and apparatus for gas turbine engines
    14.
    发明授权
    Methods and apparatus for gas turbine engines 有权
    燃气轮机发动机的方法和装置

    公开(公告)号：US07429166B2

    公开(公告)日：2008-09-30

    申请号：US11312060

    申请日：2005-12-20

    申请人： Stephen Craig Mitchell

    发明人： Stephen Craig Mitchell

    IPC分类号： F01D5/18

    CPC分类号： F01D25/02 ,  F01D5/00 ,  F02C7/047 ,  Y02T50/672 ,  Y02T50/673

    摘要： A method for manufacturing a turbine engine component includes forming a component to include a first side and an opposite second side, positioning at least one capillary adjacent to an external surface of at least one of the first and second sides, and securing the at least one capillary to the component with at least one composite layer.

    摘要翻译： 一种用于制造涡轮发动机部件的方法包括形成包括第一侧和相对的第二侧的部件，将邻近第一和第二侧中的至少一个的外表面定位至少一个毛细管，并且将至少一个 毛细管与具有至少一个复合层的部件。

    HIGH PRESSURE TURBINE DISK HUB WITH CURVED HUB SURFACE AND METHOD
    16.
    发明申请
    HIGH PRESSURE TURBINE DISK HUB WITH CURVED HUB SURFACE AND METHOD 有权
    高压涡轮盘带弯曲的HUB表面和方法

    公开(公告)号：US20070140856A1

    公开(公告)日：2007-06-21

    申请号：US11306227

    申请日：2005-12-20

    申请人： Richard Albrecht ,  Craig Higgins

    发明人： Richard Albrecht ,  Craig Higgins

    IPC分类号： B64C11/04

    CPC分类号： F01D5/00 ,  F01D5/02 ,  F01D5/06 ,  F01D5/08 ,  F01D5/30 ,  Y02T50/671 ,  Y02T50/676

    摘要： A first stage turbine disk section for a gas turbine engine, including a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a convex, curved hub surface exposed to high pressure, high temperature compressor bleed and discharge gases during engine operation, and the convex, curved hub surface acts to reduce the axial constraint at the location of peak axial stress, thereby mitigating the formation of undesirable axial stress in the disk hub and allows separation of the peak axial and hoop stresses, thereby reducing the magnitude of the peak hub surface effective stress.

    摘要翻译： 用于燃气涡轮发动机的第一级涡轮盘部分，包括中心设置的盘毂，其具有终止于外端的一体形成的径向向外延伸的纤维网。 盘毂具有在发动机运行期间暴露于高压，高温压缩机排气和放电气体的凸形弯曲毂表面，并且凸形弯曲毂表面用于减小在轴向应力峰值位置处的轴向约束，从而减轻 在盘毂中形成不期望的轴向应力并允许峰值轴向和环向应力的分离，从而减小峰值毂表面有效应力的大小。

    Combustor turbine successive dual cooling
    17.
    发明申请
    Combustor turbine successive dual cooling 有权
    燃油轮机连续双重冷却

    公开(公告)号：US20020069644A1

    公开(公告)日：2002-06-13

    申请号：US09733051

    申请日：2000-12-11

    发明人： Peter Stuttaford ,  Bernhard Fischer ,  David Edwin Cowburn ,  Saeid Oskooei ,  Michael Andrew Fryer ,  Aleksandar Kojovic ,  Jeffrey Scott Acton

    IPC分类号： F23R003/02

    CPC分类号： F23R3/005 ,  F01D5/00 ,  F01D25/26 ,  F02C7/18 ,  F05D2260/201 ,  F23R2900/03044

    摘要： The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and cooling air is forced under pressure through perforations in the cold combustor walls and impinges on the annular front and rear sections of the hot combustor wall for the backside cooling of the hot combustor wall. The exhaust combustor backside cooling air is directed to gain access to the hot end of the engine, that is, the turbine section, to cool the turbine components. The combustor/turbine successive dual cooling arrangement according to the present invention enables all the air typically used to cool the hot end of the engine downstream of the combustor, to be used as combustor backside cooling as well, to significantly reduce the amount of air needed for combustor and turbine cooling. Moreover, all the exhaust combustor backside cooling air must be used for turbine cooling and is never ingested into the combustion chamber, thereby avoiding negatively affecting the engine combustion emissions.

    摘要翻译： 本发明涉及一种燃烧器/涡轮机连续的双重冷却装置，其中燃烧器具有一体式的热燃烧器壁和前后冷的燃烧室壁，并且冷却空气被迫在压力下穿过冷的燃烧室壁和撞击物 在热燃烧器壁的环形前后部分上，用于热燃烧器壁的后侧冷却。 排气燃烧器背面冷却空气被引导以进入发动机的热端，即涡轮部分，以冷却涡轮机部件。 根据本发明的燃烧器/涡轮机连续双重冷却装置使得通常用于将燃烧器下游的发动机的热端冷却的所有空气也用作燃烧器后侧冷却，以显着减少所需的空气量 用于燃烧器和涡轮机冷却。 此外，所有排气燃烧器背面冷却空气必须用于涡轮冷却，并且不会吸入燃烧室，从而避免对发动机燃烧排放产生负面影响。

    OPTICAL CONDITION MONITORING SYSTEM FOR A WIND TURBINE GENERATOR AND METHODS OF USE THEREOF
    18.
    发明申请
    OPTICAL CONDITION MONITORING SYSTEM FOR A WIND TURBINE GENERATOR AND METHODS OF USE THEREOF 审中-公开

    公开(公告)号：US20190048854A1

    公开(公告)日：2019-02-14

    申请号：US15760044

    申请日：2016-09-15

    申请人： MICATU INC.

    发明人： Michael OSHETSKI ,  Atul PRADHAN

    IPC分类号： F03D7/04 ,  F03D7/02 ,  G01H1/00 ,  F01D5/02 ,  F03D17/00

    CPC分类号： F03D7/043 ,  F01D5/00 ,  F01D5/02 ,  F03D7/0224 ,  F03D17/00 ,  F05B2270/334 ,  F05B2270/804 ,  G01H1/003

    摘要： A wind turbine condition monitoring system includes a light source configured to produce an emitted light beam and a plurality of optical sensors configured to be positioned on a wind turbine to receive the emitted light beam from the light source. The optical sensors are configured to generate one or more product light beams from the emitted light beam. A detector is positioned to receive the product light beams generated from the optical sensors and is configured to measure intensity values of the product light beams for the optical sensors. A computing device is coupled to the detector and includes a processor and a memory coupled to the processor. The processor executes programmed instructions stored in the memory to determine, based on the intensity values for the product light beams for the optical sensors, at least a displacement value, a current value, and a voltage value for the wind turbine.