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1. 发明申请

US20190001955A1 PROPULSION SYSTEM FOR AN AIRCRAFT 审中-公开
公开(公告)号：US20190001955A1
公开(公告)日：2019-01-03
申请号：US15639134
申请日：2017-06-30
申请人： General Electric Company
发明人： Michael Thomas Gansler , Robert Charles Hon
IPC分类号： B60W20/10 , B64D27/24 , B64D27/12 , B64D35/08 , F01D15/10 , B60K6/22 , B60L11/14
CPC分类号： B60W20/10 , B60K6/22 , B60L50/16 , B60L2200/10 , B64D27/02 , B64D27/12 , B64D27/24 , B64D35/08 , B64D2027/026 , F01D15/10 , F01N3/10 , F01N9/00 , F02B37/013 , F02B73/00 , F02D43/00 , F05D2270/051 , F05D2270/071 , F05D2270/303
摘要： A hybrid-electric propulsion system includes a turbomachine, a propulsor coupled to the turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating a hybrid-electric propulsion system includes operating, by one or more computing devices, the turbomachine in an idle operating condition; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the idle operating condition; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine and increase an acceleration of the turbomachine in response to the received command to accelerate the turbomachine.

2. 发明授权

US5584171A Gas turbine control method and apparatus 失效
标题翻译：燃气轮机控制方法及装置
公开(公告)号：US5584171A
公开(公告)日：1996-12-17
申请号：US365439
申请日：1994-12-28
申请人： Isao Sato , Fumiyuki Hirose , Minoru Takaba , Akira Shimura , Shoei Takahashi , Hiraku Ikeda
发明人： Isao Sato , Fumiyuki Hirose , Minoru Takaba , Akira Shimura , Shoei Takahashi , Hiraku Ikeda
IPC分类号： F02C9/50
CPC分类号： F02C9/50 , F05D2270/071
摘要： A gas turbine engine control method and apparatus as disclosed for optimizing fuel/air mixture, especially during decreasing load conditions. In a large capacity gas turbine engine system used for generation of electric power, the system is designed to operate at a relatively constant rotational speed of the turbine which drives an electric generator unit. The load of the turbine engine varies throughout the day due to changes in electrical power demands. During normal rated load conditions, the control of the fuel/air mixture is by way of changes in fuel supply, corrected to return the turbine exhaust temperature to a desired rated temperature. During this mode of operation, the compressor inlet guide vanes are maintained in a substantially constant open position. For accommodating decreasing load conditions where the temperature drops below a predetermined temperature level below the rated temperature operation, the system is switched to an inlet guide vane control mode of operation. During the guide vane control mode of operation, the inlet guide vanes are controlled at a more precise temperature correction sensitivity than is the case for normal load operations. This more precise inlet guide vane control during decreasing load conditions assures improved fuel/air mixture during decreasing load and consequent improved efficiency and minimal NO.sub.x compound emissions, especially during changing ambient temperature conditions where cold air would otherwise increase the air supply.
摘要翻译：公开的用于优化燃料/空气混合物的燃气涡轮发动机控制方法和装置，特别是在减小负载条件下。在用于产生电力的大容量燃气涡轮发动机系统中，该系统设计成以驱动发电机单元的涡轮机的相对恒定的转速运行。由于电力需求的变化，涡轮发动机的负载在一整天内变化。在正常的额定负载条件下，燃料/空气混合物的控制是通过燃料供应的变化来进行的，这被校正以将涡轮排气温度恢复到所需的额定温度。在这种操作模式下，压缩机入口导叶保持在基本恒定的打开位置。为了适应温度下降到低于额定温度运行的预定温度水平的降低负载条件，系统被切换到入口导叶控制操作模式。在导叶控制操作模式下，入口导流叶片的控制精度比正常加载操作更为精确。在降低负载条件下，这种更为精确的入口引导叶片控制确保了在减少负载的同时改善了燃料/空气混合物，从而提高了效率和最小化的NOx化合物排放，特别是在其他空气会增加空气供给的环境温度变化的环境中。

3. 发明授权

US11686250B2 Gas turbine energy supplementing systems and heating systems, and methods of making and using the same 有权
公开(公告)号：US11686250B2
公开(公告)日：2023-06-27
申请号：US17307003
申请日：2021-05-04
申请人： PowerPHASE LLC
发明人： Robert J. Kraft
IPC分类号： F02C7/22 , F02C9/50 , F02C9/52
CPC分类号： F02C7/22 , F02C9/50 , F02C9/52 , F05D2270/06 , F05D2270/071 , F05D2270/082 , F05D2270/331 , Y02E20/16
摘要： A system and method for increasing power output of a gas turbine. A method of increasing a power output of a gas turbine comprises providing an auxiliary system configured to be coupled to the gas turbine. The auxiliary system includes a natural gas engine, a compressor, and a heat exchanger fluidly coupled to the compressor. The method includes fluidly coupling the auxiliary system to a combustor case of the gas turbine. The method comprises operating the natural gas engine to drive the compressor to compress air to form compressed air and directing exhaust of the natural gas engine to the heat exchanger. The method includes heating the compressed air in the heat exchanger using the exhaust of the natural gas engine to form heated compressed air and injecting the heated compressed air into the combustor case of the gas turbine.

4. 发明申请

US20150233296A1 Gas Turbine Energy Supplementing Systems and Heating Systems, and Methods of Making and Using the Same 审中-公开
标题翻译：燃气轮机能量补充系统和加热系统及其制造和使用方法
公开(公告)号：US20150233296A1
公开(公告)日：2015-08-20
申请号：US14351245
申请日：2013-10-21
申请人： Robert J. Kraft
发明人： Robert J. Kraft
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F02C9/50 , F02C9/52 , F05D2270/06 , F05D2270/071 , F05D2270/082 , F05D2270/331 , Y02E20/16
摘要： Electrical power systems, including generating capacity of a gas turbine, where additional electrical power is generated utilizing a separately fueled system during periods of peak electrical power demand.
摘要翻译：电力系统，包括燃气轮机的发电能力，其中在峰值电力需求期间，利用单独供电的系统产生额外的电力。

5. 发明授权

US06442945B1 Gas turbine engine 失效
标题翻译：燃气轮机
公开(公告)号：US06442945B1
公开(公告)日：2002-09-03
申请号：US09632911
申请日：2000-08-04
申请人： Anatoly Rakhmailov
发明人： Anatoly Rakhmailov
IPC分类号： F02C700
CPC分类号： F02C3/10 , F02C3/067 , F02C7/08 , F02C9/28 , F02C9/32 , F05D2270/071 , F05D2270/303
摘要： A gas turbine engine has a compressor, a combustor mounted downstream of the compressor, power turbine mounted downstream of the combustor, a counter-rotating compressor turbine having a temperature sensor at its outlet, a temperature control system for controlling the temperature at the outlet of the compressor turbine, and a fuel supply control system for supplying fuel to the combustor. The engine has a drive motor for causing the compressor to rotate and a motor control system having a motor power-up module with an input connected to the fuel supply control system, and a motor power output control module having a first input connected to the motor power-up module, a second input connected to the temperature sensor, and an output which is connected to the drive motor.
摘要翻译：燃气涡轮发动机具有压缩机，安装在压缩机下游的燃烧器，安装在燃烧器下游的动力涡轮机，在其出口具有温度传感器的反向旋转的压缩机涡轮机，用于控制出口处温度的温度控制系统压缩机涡轮机和用于向燃烧器供给燃料的燃料供给控制系统。发动机具有用于使压缩机旋转的驱动电动机和具有电动机上电模块的电动机控制系统，其具有连接到燃料供给控制系统的输入，以及电动机功率输出控制模块，其具有连接到电动机的第一输入上电模块，连接到温度传感器的第二输入端以及连接到驱动马达的输出端。

6. 发明授权

US11976589B2 Gas turbine engine system wear reduction 有权
公开(公告)号：US11976589B2
公开(公告)日：2024-05-07
申请号：US17720900
申请日：2022-04-14
申请人： RTX CORPORATION
发明人： Stephen A. Witalis , Ramesh Rajagopalan , Subhradeep Chowdhury
IPC分类号： F02C6/08 , F02C9/42 , F02C9/28
CPC分类号： F02C6/08 , F02C9/42 , F02C9/28 , F05D2260/96 , F05D2270/071
摘要： An engine system for an aircraft includes a first gas turbine engine, a second gas turbine engine, and a control system. The control system is configured to operate the first gas turbine engine with a sub-idle fuel burn schedule based on detecting landing of the aircraft, where the sub-idle fuel burn schedule includes a reduction of an idle fuel burn schedule. The control system is configured to operate the second gas turbine engine with the idle fuel burn schedule based on detecting landing of the aircraft.

7. 发明授权

US11725595B2 Control logic for gas turbine engine fuel economy 有权
公开(公告)号：US11725595B2
公开(公告)日：2023-08-15
申请号：US17648857
申请日：2022-01-25
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Daniel Coutu
IPC分类号： F02C9/42 , F01D9/04 , F01D17/06 , F01D17/16 , F02C9/54
CPC分类号： F02C9/42 , F01D9/041 , F01D17/06 , F01D17/16 , F02C9/54 , F05D2220/323 , F05D2270/071 , F05D2270/304
摘要： A method of operating an engine of a multi-engine aircraft includes sequentially operating the engine through a plurality of cycles, each cycle including a breathing-in phase followed by a breathing-out phase. The breathing-in phase includes: i) in response to a speed of a rotor of the engine being at a sub-idle threshold, opening variable guide vanes upstream a compressor and injecting fuel into the combustor to increase rotor speed to a pre-determined upper threshold, and then ii) in response to the rotor speed reaching the pre-determined upper threshold, reducing a supply rate of fuel into the combustor and substantially closing the variable guide vanes. The breathing-out phase includes maintaining the variable guide vanes closed at least until the speed drops from the pre-determined upper threshold to the pre-determined sub-idle threshold.

8. 发明申请

US20090056335A1 Gas turbine engine combustor assembly having integrated control valves 有权
标题翻译：具有集成控制阀的燃气轮机发动机燃烧器组件
公开(公告)号：US20090056335A1
公开(公告)日：2009-03-05
申请号：US11892859
申请日：2007-08-28
申请人： Geoffrey David Myers , Lewis Berkley Davis, JR. , Joseph Citeno
发明人： Geoffrey David Myers , Lewis Berkley Davis, JR. , Joseph Citeno
IPC分类号： F02C7/00
CPC分类号： F23N1/002 , F02C9/263 , F02C9/28 , F05D2270/071 , F05D2270/08 , F23N5/022 , F23N5/082 , F23N5/16 , F23N2027/04 , F23N2035/14 , F23N2037/02 , F23N2041/20 , F23R3/286
摘要： A combustor assembly for a gas turbine engine includes a combustor endcover having at least one fuel circuit and mounted thereto a plurality of pre-mixers and at least one control valve. The at least one control valve is fluidly connected to the at least one fuel circuit and operatively connected to a controller. The controller selectively operates the at least one control valve to deliver fuel through the at least one fuel circuit to the plurality of pre-mixers in order to achieve an enhanced level of operational flexibility by providing individual combustion chamber control.
摘要翻译：用于燃气涡轮发动机的燃烧器组件包括具有至少一个燃料回路并且安装到其上的多个预混合器和至少一个控制阀的燃烧器端盖。所述至少一个控制阀流体地连接到所述至少一个燃料回路并可操作地连接到控制器。控制器选择性地操作至少一个控制阀以将燃料通过至少一个燃料回路输送到多个预混合器，以通过提供单独的燃烧室控制来实现增强的操作灵活性水平。

9. 发明授权

US09729096B2 Electrical power generator for a gas turbine engine 有权
公开(公告)号：US09729096B2
公开(公告)日：2017-08-08
申请号：US14608860
申请日：2015-01-29
申请人： ROLLS-ROYCE PLC
发明人： Huw Llewelyn Edwards
IPC分类号： H02P9/04 , F02C6/20 , F02C9/00 , H02P9/00 , F01D15/10 , F02C9/28 , H02P9/48
CPC分类号： H02P9/04 , F01D15/10 , F02C6/20 , F02C9/00 , F02C9/28 , F05D2220/323 , F05D2220/764 , F05D2220/7642 , F05D2220/7646 , F05D2270/01 , F05D2270/02 , F05D2270/061 , F05D2270/071 , F05D2270/304 , F05D2270/309 , F05D2270/332 , F05D2270/335 , H02P9/007 , H02P9/48
摘要： An aircraft electrical power generation system includes an AC generator having a rotor including a plurality of electromagnetic rotor-windings and stator including plurality of electrical stator-windings. The rotor mechanically coupled to a shaft of a gas turbine engine by transmission-system. The generator includes a frequency controller, a torque sensor determining a torque on the transmission-system by the generator and controller to operate the system in first and second modes. In first mode, the power output frequency of the generator controlled by the frequency controller within limits, and reduced idle signal going to a turbine engine controller. In second mode, the power output frequency of the generator not controlled by the frequency controller and increased idle signal going to the turbine engine controller. The controller operates the system in first mode when the torque is below a limit, and in second mode when the torque is above a limit.

10. 发明申请

US20110265486A1 COMBUSTION SYSTEM WITH VARIABLE PRESSURE DIFFERENTIAL FOR ADDITIONAL TURNDOWN CAPABILITY OF A GAS TURINE ENGINE 审中-公开
标题翻译：具有可变压力的燃烧系统，用于气体涡轮发动机的附加涡度能力
公开(公告)号：US20110265486A1
公开(公告)日：2011-11-03
申请号：US12769934
申请日：2010-04-29
申请人： Adam D. Plant
发明人： Adam D. Plant
IPC分类号： F02C7/057
CPC分类号： F02C7/057 , F02C9/52 , F02C9/54 , F05D2270/071 , F05D2270/08 , F23R3/26
摘要： A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section, and the turbine engine having a base load. The combustor section includes a combustor and a combustor shell. A flow control device is located in a flow path between the combustor shell and an inlet to the combustor. The flow control device effects an increase in a pressure drop of shell air flowing from the combustor shell to the combustor. A controller is provided for operating the flow control device to change a pressure drop across the flow control device, wherein an increase in the pressure drop across the flow control device results in a corresponding reduction in mass flow through the combustor for effecting a reduction in power output from the turbine engine during a reduction in an operating load to less than the base load.
摘要翻译：一种用于发电机的涡轮发动机组件，其包括具有压缩机部分，燃烧器部分和涡轮部分的涡轮发动机，以及具有基本负载的涡轮发动机。燃烧器部分包括燃烧器和燃烧器壳体。流量控制装置位于燃烧器壳体与燃烧器入口之间的流动路径中。流量控制装置使得从燃烧器壳体流到燃烧器的壳体空气的压降增加。提供控制器用于操作流量控制装置以改变流量控制装置上的压降，其中跨越流量控制装置的压降的增加导致通过燃烧器的质量流量的相应减小以实现功率的降低在将操作负载降低到小于基本负载时，从涡轮发动机输出。

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