公开(公告)号：US09988153B2

公开(公告)日：2018-06-05

申请号：US14797850

申请日：2015-07-13

Applicant: HAMILTON SUNDSTRAND CORPORATION

Inventor： Peter Zywiak

IPC: F04D27/02 ,  B64D13/08 ,  F04D19/00 ,  F04D25/06 ,  F04D27/00

CPC classification number: B64D13/08 ,  F04D19/002 ,  F04D25/06 ,  F04D27/001 ,  F04D27/0261 ,  F05D2270/3013

Abstract: A ram air fan (RAF) assembly is provided and includes a ram air inlet, a heat exchanger disposed in the ram air inlet, an RAF disposed in the ram air inlet to drive airflow through the heat exchanger, a sensor disposed in the ram air inlet proximate to the RAF and a controller. The controller is operably coupled to the RAF and the sensor and is configured to drive rotations of the RAF to achieve a target RAF rotational speed in accordance with a determination that a reading generated by the sensor is indicative of a surge event.

公开(公告)号：US20170342995A1

公开(公告)日：2017-11-30

申请号：US15165728

申请日：2016-05-26

Applicant: Rolls-Royce Corporation

Inventor： Nathan Ottow ,  Jonathan Acker ,  Nate Cooper ,  Mark Whitlock ,  Michael Nesteroff

IPC: F04D27/00 ,  F04D29/42 ,  F04D29/16 ,  F04D29/28

CPC classification number: F04D29/4206 ,  F01D11/08 ,  F01D11/22 ,  F01D25/24 ,  F04D27/0246 ,  F04D29/162 ,  F04D29/622 ,  F05D2220/3219 ,  F05D2240/11 ,  F05D2250/281 ,  F05D2260/57 ,  F05D2270/3013 ,  F05D2270/305

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.

公开(公告)号：US09719377B2

公开(公告)日：2017-08-01

申请号：US14444253

申请日：2014-07-28

Applicant: ALSTOM Technology Ltd

Inventor： Richard Carroni ,  Jürgen Hoffmann

IPC: F01K23/10 ,  F01D25/30 ,  F02C6/04

CPC classification number: F01D25/30 ,  F01K23/101 ,  F02C6/04 ,  F05D2260/61 ,  F05D2260/611 ,  F05D2270/08 ,  F05D2270/3013 ,  Y02C10/06 ,  Y02E20/16 ,  Y02E20/326

Abstract: The invention relates to a method for operating a gas turbine power plant, including a gas turbine, a HRSG following the gas turbine, an exhaust gas blower, and a carbon dioxide separation plant which separates the carbon dioxide contained in the exhaust gases and discharges it to a carbon dioxide outlet, the gas turbine, HRSG, exhaust gas blower, and carbon dioxide separation plant being connected by means of exhaust gas lines. According to the method a trip of the gas turbine power plant includes the steps of: stopping the fuel supply, switching off the exhaust gas blower, and controlling the opening angle of a VIGV at a position bigger or equal to a position required to keep a pressure in the exhaust gas lines between the HRSG and the exhaust gas blower above a minimum required pressure. The invention relates, further relates to a gas turbine power plant configured to carry out such a method.

公开(公告)号：US09611857B2

公开(公告)日：2017-04-04

申请号：US14261106

申请日：2014-04-24

Applicant: Control Components, Inc.

Inventor： Fabio Giove ,  Flavio Tondolo ,  Marco Mastrovito

IPC: F04D27/02

CPC classification number: F04D27/0223 ,  F04D27/0215 ,  F04D27/023 ,  F05D2270/3011 ,  F05D2270/3013

Abstract: An anti-surge system capable of anticipating a surge event in a compressor for readying the actuator to quickly actuate the anti-surge valve from the closed position to the open position. The control system includes a compressor surge controller configured to transmit a signal to the valve positioner when the operating point of the valve is approaching the surge control line. The compressor surge controller may monitor an operating margin equal to the difference between the operating point and the surge control line, and when the operating margin falls below a prescribed threshold, the compressor surge controller may send a signal to the positioner. In turn, the positioner may vent some pressure from the actuator. In this way, the dead time of the anti-surge valve on the valve seat is minimized and the valve will react more promptly to an opening signal.

公开(公告)号：US20160325843A1

公开(公告)日：2016-11-10

申请号：US15110842

申请日：2015-01-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David Lloyd Ripley ,  Michael E. Mehrer

IPC: B64D37/32 ,  B64D27/10 ,  B64D41/00 ,  F02C9/28 ,  F01D21/00

CPC classification number: B64D37/32 ,  B64D27/10 ,  B64D41/00 ,  F01D21/003 ,  F02C7/232 ,  F02C9/28 ,  F02D41/221 ,  F02D2200/0602 ,  F02D2200/101 ,  F05D2220/50 ,  F05D2260/80 ,  F05D2260/83 ,  F05D2270/021 ,  F05D2270/3013 ,  Y02T10/40

Abstract: The present disclosure relates generally to system and method for detecting fuel shutoff valve failures in a system including multiple fuel shutoff valves connected in series. By commanding different fuel shutoff valves to close and detecting changes in the system operating conditions, the system and method may determine if any of the fuel shutoff valves are not working properly.

Abstract translation: 本公开总体上涉及用于检测包括串联连接的多个燃料截止阀的系统中的燃料截止阀故障的系统和方法。 通过指示不同的燃油截止阀来关闭和检测系统运行状况的变化，系统和方法可以确定燃油截止阀中是否有不正常工作。

公开(公告)号：US09347323B2

公开(公告)日：2016-05-24

申请号：US14624240

申请日：2015-02-17

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

IPC: F01D5/14 ,  F02C3/04

CPC classification number: F04D29/384 ,  F01D5/141 ,  F02C3/04 ,  F02C3/14 ,  F02C7/36 ,  F02K3/04 ,  F04D29/325 ,  F05D2220/36 ,  F05D2240/35 ,  F05D2250/71 ,  F05D2250/713 ,  F05D2250/75 ,  F05D2260/4031 ,  F05D2270/3013 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm).

Abstract translation: 用于涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。 翼型具有总弦长和跨度位置之间的关系，并且对应于从0％跨度位置到第一峰具有增加的总弦长的曲线。 第一个峰出现在45-65％跨度位置的范围内，并且该曲线或者保持一般恒定或具有从第一峰到100％跨度位置的总弦长减小。 总和弦长度在8.2-10.5英寸（20.8-26.7厘米）范围内的0％跨度位置。

公开(公告)号：US08528316B2

公开(公告)日：2013-09-10

申请号：US12429003

申请日：2009-04-23

Applicant: Mark H. Baker ,  Steve Abel ,  George Woessner

Inventor： Mark H. Baker ,  Steve Abel ,  George Woessner

IPC: F02K9/80 ,  F02K9/84 ,  F02K9/26 ,  F02K9/86

CPC classification number: F02K9/80 ,  F02K9/563 ,  F05D2270/051 ,  F05D2270/3013

Abstract: Systems and methods of controlling solid propellant gas pressure and vehicle thrust are provided. Propellant gas pressure and a vehicle inertial characteristic are sensed. Propellant gas pressure commands and vehicle thrust commands are generated. A propellant gas pressure error is determined based on the propellant gas pressure commands and the sensed propellant gas pressure, and vehicle thrust error is determined based on the vehicle thrust commands and the sensed vehicle inertial characteristic. Reaction control valves are moved between closed and full-open positions based on the determined propellant gas pressure error and on the determined vehicle thrust error. The system and method allow the reaction control valves to operate at variable frequencies or at fixed frequencies. The system and method also allows propellant pressure to be commanded to follow a predetermined pressure profile or commanded to vary “on-the-fly.”

Abstract translation: 提供了控制固体推进剂气体压力和车辆推力的系统和方法。 检测到推进剂气体压力和车辆惯性特性。 产生推进剂气体压力指令和车辆推力指令。 基于推进剂气体压力指令和感测到的推进剂气体压力确定推进剂气体压力误差，并且基于车辆推力命令和所感测的车辆惯性特性来确定车辆推力误差。 基于确定的推进剂气体压力误差和确定的车辆推力误差，反应控制阀在闭合位置和全开位置之间移动。 该系统和方法允许反应控制阀以可变频率或固定频率运行。 该系统和方法还允许命令推进剂压力遵循预定的压力分布或命令“即时”变化。

公开(公告)号：US08307650B2

公开(公告)日：2012-11-13

申请号：US12718645

申请日：2010-03-05

Applicant: Lee J. Robinson ,  James A. McEwen

Inventor： Lee J. Robinson ,  James A. McEwen

IPC: F02B33/44 ,  F02D23/00

CPC classification number: F02B37/004 ,  F02B37/001 ,  F02B37/002 ,  F02B37/007 ,  F02B37/013 ,  F02B37/16 ,  F02B37/18 ,  F02B37/183 ,  F02B39/00 ,  F02D9/06 ,  F05D2210/12 ,  F05D2220/40 ,  F05D2240/40 ,  F05D2270/3013 ,  Y02T10/144

Abstract: A turbocharger system comprises a first relatively small turbocharger and a second relatively large turbocharger connected in series and an exhaust gas flow control valve. The exhaust control valve has an inlet port communicating with the exhaust gas flow upstream of the first turbine a first outlet port communicating with the exhaust flow downstream of said first turbine but upstream of said second turbine, and a second outlet port communicating with the exhaust flow downstream of said second turbine. The valve is operable to selectively permit or block flow through the first and second outlet ports.

Abstract translation: 涡轮增压器系统包括第一相对较小的涡轮增压器和串联连接的第二较大涡轮增压器和排气流量控制阀。 排气控制阀具有与第一涡轮机上游的废气流连通的入口端口，与所述第一涡轮机下游的排气流，与所述第二涡轮机的上游连通的第一出口端口，以及与排气流连通的第二出口 在所述第二涡轮机的下游。 阀可操作以选择性地允许或阻止流过第一和第二出口。

公开(公告)号：US20120111020A1

公开(公告)日：2012-05-10

申请号：US13253316

申请日：2011-10-05

Applicant: Luca BOZZI ,  Marco MANTERO ,  Federico BONZANI

Inventor： Luca BOZZI ,  Marco MANTERO ,  Federico BONZANI

IPC: F02C6/08

CPC classification number: F02C9/18 ,  F02C7/18 ,  F05D2260/205 ,  F05D2270/08 ,  F05D2270/082 ,  F05D2270/3011 ,  F05D2270/3013 ,  F05D2270/303

Abstract: A control method for cooling a turbine stage of a gas turbine, whereby cooling air is bled from combustion air flowing in a compressor of the gas turbine, and is fed to a cooling circuit staring from a stator of the turbine stage; and cooling airflow is adjusted as a function of the pressure at the inlet of the cooling circuit, and as a function of the combustion air pressure at the exhaust of the compressor; more specifically, there is a feedback control setting a setpoint, which is predetermined as a function of the power output of the turbine to reduce contaminating emissions.

Abstract translation: 一种用于冷却燃气轮机的涡轮级的控制方法，其中，从燃气轮机的压缩机中流动的燃烧空气排出冷却空气，并且将其供给到从涡轮机级的定子凝结的冷却回路; 并且作为冷却回路入口处的压力的函数调节冷却气流，并且作为压缩机排气处的燃烧空气压力的函数; 更具体地，存在设置设定点的反馈控制，该设定点是根据涡轮机的功率输出预先确定的，以减少污染的排放。

公开(公告)号：US20120006032A1

公开(公告)日：2012-01-12

申请号：US12830644

申请日：2010-07-06

Applicant: Scott Alan Kopcho ,  Garth Curtis Frederick ,  Timothy Andrew Healy

Inventor： Scott Alan Kopcho ,  Garth Curtis Frederick ,  Timothy Andrew Healy

IPC: F02C7/264 ,  G01M15/14

CPC classification number: F02C7/264 ,  F01D21/003 ,  F05D2260/80 ,  F05D2260/83 ,  F05D2270/3013 ,  F05D2270/303

Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for confirming ignition in a gas turbine. According to an example embodiment of the invention, a method is provided for confirming ignition associated with a gas turbine combustor. The method can include receiving one or more permissive signals associated with one or more gas flow control valves, receiving one or more fuel supply pressure signals, receiving one or more fuel igniter signals, and receiving one ore more compressor pressure discharge (CPD) signals. The method can also include determining an ignition status associated with the gas turbine combustor based at least in part on the one or more permissive signals, the one or more fuel supply pressure signals, the one or more fuel igniter signals, and a qualified change in the one or more CPD signals. The method can also include outputting an ignition status signal based on the determined ignition status.

Abstract translation: 本发明的某些实施例可以包括用于确认燃气轮机中的点火的系统，方法和设备。 根据本发明的示例性实施例，提供了一种用于确认与燃气轮机燃烧器相关联的点火的方法。 该方法可以包括接收与一个或多个气体流量控制阀相关联的一个或多个允许信号，接收一个或多个燃料供应压力信号，接收一个或多个燃料点火器信号，以及接收一个或多个压缩机压力放电（CPD）信号。 该方法还可以包括至少部分地基于一个或多个许可信号，一个或多个燃料供应压力信号，一个或多个燃料点火器信号和合格的变化来确定与燃气涡轮机燃烧器相关联的点火状态 一个或多个CPD信号。 该方法还可以包括基于所确定的点火状态来输出点火状态信号。