公开(公告)号：US20150078892A1

公开(公告)日：2015-03-19

申请号：US14488661

申请日：2014-09-17

Applicant: General Electric Company

Inventor： Ariel Harter Lomas ,  Bradley Steven Carey ,  Fabio Bozzoni ,  Marco Bonini

IPC: F01D25/24 ,  F01D25/28

CPC classification number: F01D25/243 ,  B25B27/16 ,  F01D25/28 ,  Y10T29/49899

Abstract: Turbomachines, coupling devices and methods for coupling a first casing and an second casing together are provided. The first casing and second casing include mating bore holes defined in mating flanges thereof, which may be misaligned. The coupling device may include a bushing insertable and positionable within one of the mating bore holes, and a pin insertable and positionable within the bushing and the other of the mating bore holes. The bushing and pin may each include eccentric features which may facilitate insertion into the mating bore holes when the bore holes are misaligned, thus coupling the first casing and second casing together.

Abstract translation: 提供了用于将第一壳体和第二壳体联接在一起的涡轮机械，联接装置和方法。 第一壳体和第二壳体包括在其配合凸缘中限定的配合孔，其可能不对准。 联接装置可以包括可插入并可定位在一个配合孔内的衬套，以及可插入并可定位在衬套内的销和另一个配合孔。 衬套和销可以各自包括偏心特征，当钻孔不对准时，这些特征可以有助于插入到配合孔中，从而将第一壳体和第二壳体联接在一起。

公开(公告)号：US20150118014A1

公开(公告)日：2015-04-30

申请号：US14066225

申请日：2013-10-29

Applicant: General Electric Company

Inventor： Kevin Michael Elward ,  Scott Alan Kopcho ,  Robert Thomas Thatcher ,  Ariel Harter Lomas ,  Bradley Steven Carey ,  Clive Andrew Morgan

IPC: F02C9/28 ,  G05B15/02

CPC classification number: F02C9/28 ,  F01D21/10 ,  F01D21/12 ,  F01D25/002 ,  F05D2260/607 ,  F05D2260/81 ,  F05D2270/083 ,  F05D2270/112 ,  F05D2270/20 ,  F05D2270/303 ,  F23N5/022 ,  F23N2025/08 ,  F23N2041/20 ,  F23R2900/00004 ,  G05B15/02

Abstract: The systems, methods, and computer-readable media set a gas turbine firing temperature to maintain gas turbine metal surface temperatures. In certain embodiments, a method of setting a gas turbine firing temperature is disclosed that may comprise determining a critical temperature at which ash from ash bearing fuels becomes unremovable by conventional water wash procedures, determining hot gas path component metal surface temperatures, and adjusting the gas turbine firing temperature to maintain the metal surface temperatures below the critical temperature. Determining the metal surface temperatures may be based at least in part on measured gas turbine parameters, gas turbine performance models, and empirical models.

Abstract translation: 系统，方法和计算机可读介质设定燃气轮机的燃烧温度以维持燃气轮机的金属表面温度。 在某些实施例中，公开了一种设定燃气轮机燃烧温度的方法，其可以包括确定临界温度，在该临界温度下，通过常规水洗步骤确定来自含灰燃料燃料的灰分变得不可移动，确定热气体路径组分金属表面温度，并调节气体 涡轮机的燃烧温度，以保持金属表面温度低于临界温度。 确定金属表面温度可以至少部分地基于测量的燃气轮机参数，燃气轮机性能模型和经验模型。

公开(公告)号：US20150068213A1

公开(公告)日：2015-03-12

申请号：US14019891

申请日：2013-09-06

Applicant: General Electric Company

Inventor： Ariel Harter Lomas ,  Bradley Steven Carey ,  Kevin Michael Elward ,  Richard Francis Gutta ,  George Jason Kaliope

IPC: F02C7/12

CPC classification number: F02C7/12 ,  F02C7/1435

Abstract: A method of cooling a gas turbine engine is provided. The method includes removing a load from the gas turbine engine. The method also includes operating the gas turbine engine at a rated speed of the gas turbine engine. The method further includes modulating an angle of at least one stage of inlet guide vanes disposed proximate an inlet of a compressor section of the gas turbine engine, wherein modulating the angle modifies a flow rate of an inlet flow for reducing a cooling time of the gas turbine engine.

Abstract translation: 提供一种冷却燃气轮机的方法。 该方法包括从燃气涡轮发动机移除负载。 该方法还包括以燃气涡轮发动机的额定速度操作燃气涡轮发动机。 该方法还包括调节设置在燃气涡轮发动机的压缩机部分的入口附近的入口导叶的至少一级的角度，其中调节角度改变入口流的流速以减少气体的冷却时间 涡轮发动机。

公开(公告)号：US20140260287A1

公开(公告)日：2014-09-18

申请号：US13832270

申请日：2013-03-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Robert Thomas Thatcher ,  Bradley Steven Carey ,  Paul Burchell Glaser ,  Ariel Harter Lomas ,  Andrew Mitchell Rodwell

IPC: F02C7/30 ,  G01N25/02 ,  F02C9/00

CPC classification number: F02C7/30 ,  F02C9/00 ,  F02C9/40 ,  F05D2270/303 ,  G01N25/02

Abstract: Gas turbine firing temperature optimization based on a measured sulfur content of a fuel supply of the gas turbine system is provided. In one embodiment, a system includes a diagnostic system configured to determine a maximum firing temperature for a combustor of a gas turbine system. The diagnostic system may determine the maximum firing temperature based on a predetermined sulfur content to maximum firing temperature correlation and an actual sulfur content of a fuel supplied to the combustor. The diagnostic system may also be configured to provide an indicator for a change in an actual firing temperature in the combustor of the gas turbine system. The diagnostic system may provide the indicator in response to the determined maximum firing temperature differing from the actual firing temperature of the combustor of the gas turbine system.

Abstract translation: 提供了基于燃气轮机系统的燃料供给量的测量硫含量的燃气轮机燃烧温度优化。 在一个实施例中，系统包括被配置为确定燃气轮机系统的燃烧器的最高点火温度的诊断系统。 诊断系统可以基于预定的硫含量至最高焙烧温度相关性以及供应到燃烧器的燃料的实际硫含量来确定最大烧制温度。 诊断系统还可以被配置为提供用于燃气轮机系统的燃烧器中的实际燃烧温度的变化的指示器。 诊断系统可以响应于确定的与燃气轮机系统的燃烧器的实际燃烧温度不同的最大燃烧温度来提供指示器。

公开(公告)号：US20150075265A1

公开(公告)日：2015-03-19

申请号：US14488693

申请日：2014-09-17

Applicant: General Electric Company

Inventor： John David Memmer ,  Thomas John Freeman ,  Robert Flynn ,  Ariel Harter Lomas ,  Bradley Steven Carey

IPC: G01M15/14 ,  G01B5/008

CPC classification number: G01M15/14 ,  F01D11/14 ,  F01D17/20 ,  G01B5/008 ,  G01B11/14

Abstract: Measurement devices and methods for evaluating clearances between adjacent components in turbomachines are provided. A measurement device may include a tool and a controller. The tool and controller may determine the clearance by measuring the distance between the adjacent components. The controller may compare the clearance to a predetermined engineering clearance limit and/or a previously measured clearance. A method may include measuring the clearance with a device which includes a controller. The method may further include comparing the clearance in the controller to a predetermined engineering clearance limit and/or a previously measured clearance.

Abstract translation: 提供了用于评估涡轮机中相邻部件之间的间隙的测量装置和方法。 测量装置可以包括工具和控制器。 工具和控制器可以通过测量相邻部件之间的距离来确定间隙。 控制器可以将间隙与预定的工程间隙限制和/或先前测量的间隙进行比较。 一种方法可以包括用包括控制器的装置测量间隙。 该方法还可以包括将控制器中的间隙与预定的工程间隙限制和/或先前测量的间隙进行比较。