公开(公告)号：WO2019118110A1

公开(公告)日：2019-06-20

申请号：PCT/US2018/060246

申请日：2018-11-12

Applicant: SOLAR TURBINES INCORPORATED

Inventor： MEIER, Andrew T. ,  OKPARA, Nnawuihe ,  POINTON, Stephen E. ,  HAMM, Hans D. ,  HIRAKO, Kevin ,  CARULLO, Jeffrey S.

IPC: F01D5/18 ,  F01D5/20

Abstract: A cooled turbine blade (440) is disclosed herein. The cooled turbine blade having a base (442) and an airfoil (441), the base including cooling air inlets (481) and channels (483), and the airfoil including an multi bend heat exchange path (470) beginning at the base and ending at a cooling air outlet (471) at the trailing edge (447) of the airfoil. The airfoil also includes a skin (460) that encompasses a tip wall (461) and an inner spar (462).

公开(公告)号：WO2019050679A1

公开(公告)日：2019-03-14

申请号：PCT/US2018/047425

申请日：2018-08-22

Applicant: SOLAR TURBINES INCORPORATED

Inventor： ZHANG, Donghui ,  MOFFATT, Christopher ,  SINGH, Avneet ,  GARCEAU, Sean

IPC: F01D11/06 ,  F16J15/40 ,  F04D29/12 ,  F04C27/00 ,  F04B39/04

CPC classification number: F04D29/102 ,  F01D11/00 ,  F04D25/08 ,  F04D27/009 ,  F04D29/124 ,  F16J15/004

Abstract: A compressor system (10) includes a gas compressor (18) with dry gas seals (66, 68) about a driveshaft (64). The compressor system (10) also includes a fugitive gas system (30) having a gas conduit (36) in fluid communication with a collection cavity (34, 35) in a collector (32) coupled to the gas compressor (18) to receive fugitive gas leaked through a pressurized gas leakage path (67, 69). The fugitive gas system (30) may be structured for flaring the gas, and includes a pressure control system (42) with an accumulator tank (44), and a vent line (46) for venting gas pressure and having a backpressure regulator (52) therein. Fugitive combustible gas is conveyed through a flow restriction orifice (96, 100) downstream of the compressor (18).

公开(公告)号：WO2019032295A2

公开(公告)日：2019-02-14

申请号：PCT/US2018/043684

申请日：2018-07-25

Applicant: SOLAR TURBINES INCORPORATED

Inventor： LEE, David

IPC: H02J3/38 ,  H02J3/46 ,  F02C9/42

Abstract: A control system (12) for preventing electrical power supply disruptions in an electrical power system (10) includes an electronic control unit (14) structured to receive a power signal indicative of reactive power in an electrical generator (34) that is produced in response to a change in an electrical load of an electrical power bus (40). The electronic control unit (14) is further structured to determine voltage commands based on the power signal and vary output voltage of the electrical generator (34) non-linearly such that occurrence of a reactive power shutdown condition is inhibited.

公开(公告)号：WO2018222508A1

公开(公告)日：2018-12-06

申请号：PCT/US2018/034534

申请日：2018-05-25

Applicant: SOLAR TURBINES INCORPORATED

Inventor： ANDERSON, Kevin D. ,  WARREN, Martin L. ,  JAFFURS, Jeffrey J. ,  VAN DER STOK, Marcel

IPC: E04H5/02 ,  E04B1/348

CPC classification number: E04B1/3483 ,  E04B1/8218 ,  E04B2001/34884 ,  E04B2001/34892 ,  E04H5/02 ,  F04D29/601

Abstract: A modular building structure (200) for a turbomachinery equipment (400) includes a first prefabricated structure (102), a second prefabricated structure (102'), and a plurality of guides (106) to align and couple the first prefabricated structure (102) to the second prefabricated structure (102'). The first prefabricated structure (102) includes a first rigid frame (104) formed from first linear members, and defines first pin receiving holes (120). The second prefabricated structure (102') includes a second rigid frame (104') formed from second linear members, and defines second pin receiving holes (120'). Each guide (106) includes a plate (130) having an opening (134) extending through the plate (130), and an elongated member (132) extending through the opening (134) of the plate (130). The elongated member (132) includes a first end portion (138) extending inside a corresponding first pin receiving hole (120) and a second end portion (140) extending inside a corresponding second pin receiving hole (120') for coupling the first prefabricated structure (102) with the second prefabricated structure (102').

公开(公告)号：WO2017023517A1

公开(公告)日：2017-02-09

申请号：PCT/US2016/042481

申请日：2016-07-15

Applicant: SOLAR TURBINES INCORPORATED

Inventor： SCHIFF, Garrett L. ,  PHAM, Thompson, H. ,  MURGIA, Fabrice M. ,  WATKINS, Neal ,  SADASIVAN, Vijaya S. ,  VASAMSETTY, Ramanath ,  KEMP, Frances J. ,  SANJEEVI, Anbarasu ,  MONTI, Andrea ,  DE STEFANO, Alessio ,  SCABAROZI, John G. ,  LEON, Marco E. ,  CANCHI, Venkatesh ,  CAMERON, Paul F. ,  MCELHINNEY IV, Joseph S. ,  ESTUPINAN, Miguel J. ,  COOK, Christian M.

IPC: G01M15/14 ,  G01M15/04

CPC classification number: F01D21/003 ,  F05D2260/80 ,  G05B19/0428 ,  G05B23/0235 ,  G07C3/00

Abstract: A method of monitoring a turbomachinery system (50) is disclosed herein. The method includes periodically receiving sensor data for the turbomachinery system (50) at a monitoring device (800) from a monitoring system server (740). The method also includes the monitoring device (800) determining whether the tags for each group of a plurality of groups are in the sensor data and correlating the tags with the groups. The method further includes displaying one of the groups on an output display of the monitoring device (800) including the tag name and the sensor value for each tag correlated with the group displayed.

Abstract translation: 本文公开了一种监测涡轮机械系统（50）的方法。 该方法包括在来自监视系统服务器（740）的监视设备（800）周期性地接收涡轮机械系统（50）的传感器数据。 该方法还包括监视设备（800），确定多个组中的每个组的标签是否在传感器数据中，并将标签与组相关联。 该方法还包括在监视设备（800）的输出显示器上显示其中一个组，其中包括与所显示的组相关联的每个标签的标签名称和传感器值。

公开(公告)号：WO2016111773A1

公开(公告)日：2016-07-14

申请号：PCT/US2015/063011

申请日：2015-11-30

Applicant: SOLAR TURBINES INCORPORATED

Inventor： KIM, Yong Weon ,  LIN, Tsuhon ,  CARULLO, Jeffrey Stephen

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12

CPC classification number: F01D9/047 ,  F01D5/189 ,  F01D9/02

Abstract: A metal insert tube (460) of a turbine vane (452) is disclosed. The insert tube (460) includes a pressure side wall (461), a suction side wall (464) opposite and spaced apart from the pressure side wall (461), a leading edge (462), and a trailing edge (463) opposite the leading edge (462). The insert tube (460) includes a plurality of cooling channels spaced along the pressure side wall (461). The insert tube (460) includes an indented portion (467) located between the trailing edge (463) and the pressure side wall (461).

Abstract translation: 公开了一种涡轮叶片（452）的金属插入管（460）。 插入管（460）包括压力侧壁（461），与压力侧壁（461）相对且间隔开的吸入侧壁（464），前缘（462）和与所述压力侧壁（461）相对的后缘（463） 前沿（462）。 插入管（460）包括沿着压力侧壁（461）间隔开的多个冷却通道。 插入管（460）包括位于后缘（463）和压力侧壁（461）之间的凹入部分（467）。

公开(公告)号：WO2016089970A1

公开(公告)日：2016-06-09

申请号：PCT/US2015/063385

申请日：2015-12-02

Applicant: SOLAR TURBINES INCORPORATED

Inventor： LAMICQ, Olivier Jacques Louis ,  CLARK, Tristan William

IPC: F01D9/02 ,  F01D5/14 ,  F04D29/54

CPC classification number: F01D17/162 ,  F04D27/0246 ,  F04D29/563 ,  F05D2250/51

Abstract: A vane (110) for an Inlet Guide Vane (IGV) (112) of a multistage compressor (100) includes a root portion (114), a tip portion (116), and an airfoil (118) extending therebetween. The vane (110) is configured such that a ratio of the maximum thickness of the airfoil (118) to a chord length (Tmax/C) at 50% of the span height (H) taken from the tip portion (116) of the vane (110) is configured to lie in the range of 0.11 to 0.12. In addition to the ratio (Tmax/C) at 50% of the span height (H) being in range of 0.11 to 0.12, a ratio of the maximum thickness to the chord length (Tmax/C) at various points along the airfoil (118) varies with span height (H) of the vane (110) i.e., distance taken from the tip portion (116) of the vane (110) and the local chord length C present at that span height H of the vane (110) taken from the tip portion (116).

Abstract translation: 用于多级压缩机（100）的入口引导叶片（IGV）（112）的叶片（110）包括根部（114），尖端部分（116）和在它们之间延伸的翼型件（118）。 叶片110被配置为使得翼型件118的最大厚度与跨度高度（H）的50％的翼弦长度（Tmax / C）的比率取自 叶片（110）被配置为位于0.11至0.12的范围内。 除了跨度高度（H）的50％的比率（Tmax / C）在0.11至0.12的范围内，沿着翼型的各个点处的最大厚度与弦长（Tmax / C）的比率 118）随着叶片（110）的跨度高度（H）而变化，即从叶片（110）的尖端部分（116）获取的距离和在叶片（110）的跨度高度H处存在的局部弦长C， 从尖端部分（116）取出。

公开(公告)号：WO2015187328A1

公开(公告)日：2015-12-10

申请号：PCT/US2015/030721

申请日：2015-05-14

Applicant: SOLAR TURBINES INCORPORATED

Inventor： BOGANE, William Corey

IPC: F23R3/28 ,  F02C7/22

CPC classification number: B23K1/0008 ,  B23K1/0018 ,  B23K1/19 ,  B23K2203/26 ,  F02C7/22 ,  F23R3/28 ,  F23R2900/00018 ,  Y10T403/479

Abstract: A fuel injector for a combustor assembly for a gas turbine engine is disclosed. The fuel injector includes a first component, a second component, and a braze layer. The first component has a sidewall. The second component also has a sidewall. The braze layer is formed between the sidewall of the first component and the sidewall of the second component. The braze layer is being formed from a Nickel (Ni) alloy brazing material containing non-metallic constituents. The braze layer also has a eutectic-free region with substantially all of the non-metallic constituents diffused away from a centerline area between the first component and the second component.

Abstract translation: 公开了一种用于燃气涡轮发动机的燃烧器组件的燃料喷射器。 燃料喷射器包括第一部件，第二部件和钎焊层。 第一部件具有侧壁。 第二部件还具有侧壁。 钎焊层形成在第一部件的侧壁和第二部件的侧壁之间。 钎焊层由含有非金属成分的镍（Ni）合金钎焊材料形成。 钎焊层还具有非共晶区域，其中基本上所有的非金属成分都远离第一部件和第二部件之间的中心线区域扩散。

公开(公告)号：WO2015053950A1

公开(公告)日：2015-04-16

申请号：PCT/US2014/057379

申请日：2014-09-25

Applicant: SOLAR TURBINES INCORPORATED

Inventor： GREEN, Richard J. ,  NOVARESI, Mark A. ,  BOLLAPRAGADA, Sudhakar

IPC: F01D25/00 ,  F02C7/00 ,  G06F19/00

CPC classification number: G01M15/14 ,  G05B23/0283 ,  G07C5/006

Abstract: A system and methods for the condition based lifing of a gas turbine engine component is disclosed. The system and methods determine the stress and caused by fatigue and creep for each load cycle of the gas turbine engine, and use a ductility exhaustion method to combine the fatigue and creep strain rates determined from the fatigue and creep stresses to determine the remaining useful of the gas turbine engine component.

Abstract translation: 公开了一种用于燃气涡轮发动机部件的基于条件的升降机的系统和方法。 该系统和方法确定了燃气轮机发动机每个负载循环的疲劳和蠕变引起的应力，并采用延性疲劳方法来组合从疲劳和蠕变应力确定的疲劳和蠕变应变速率，以确定剩余有用 燃气涡轮发动机部件。

公开(公告)号：WO2015053949A1

公开(公告)日：2015-04-16

申请号：PCT/US2014/057373

申请日：2014-09-25

Applicant: SOLAR TURBINES INCORPORATED

Inventor： GREEN, Richard, J. ,  DOUGLAS, Jonathan, P.

IPC: F01D5/12 ,  G06F19/00

CPC classification number: G01M15/14 ,  F01D5/28 ,  F05D2260/82 ,  F05D2300/607

Abstract: A system and methods for lifing a single crystal turbine blade of a gas turbine engine is disclosed. The system and methods determine the anisotropic strain of the single crystal turbine blade caused by fatigue and creep by resolving the shear stresses on each of the primary slip systems of the single crystal turbine blade. The system and methods use a ductility exhaustion method to combine the anisotropic fatigue and creep strains to determine the operating life of the single crystal turbine blade.

Abstract translation: 公开了一种用于升高燃气涡轮发动机的单晶涡轮叶片的系统和方法。 该系统和方法通过解决单晶涡轮叶片的每个主滑动系统上的剪切应力来确定由疲劳和蠕变引起的单晶涡轮叶片的各向异性应变。 该系统和方法采用延性耗尽方法组合各向异性疲劳和蠕变应变，以确定单晶轮机叶片的使用寿命。