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51. 发明授权

US09903279B2 Systems and methods for optimizing stoichiometric combustion 有权
公开(公告)号：US09903279B2
公开(公告)日：2018-02-27
申请号：US13805646
申请日：2011-06-27
申请人： Franklin F. Mittricker , Richard A. Huntington
发明人： Franklin F. Mittricker , Richard A. Huntington
IPC分类号： F02C9/20 , F02C9/50 , F01K23/10 , F02C3/34
CPC分类号： F02C9/20 , F01K23/10 , F02C3/34 , F02C9/50 , F05D2270/08 , F05D2270/083 , Y02E20/16 , Y02T50/677
摘要： Provided are more efficient techniques for operating gas turbine systems. In one embodiment a gas turbine system comprises an oxidant system, a fuel system, a control system, and a number of combustors adapted to receive and combust an oxidant from the oxidant system and a fuel from the fuel system to produce an exhaust gas. The gas turbine system also includes a number of oxidant-flow adjustment devices, each of which are operatively associated with one of the combustors, wherein an oxidant-flow adjustment device is configured to independently regulate an oxidant flow rate into the associated combustor. An exhaust sensor is in communication with the control system. The exhaust sensor is adapted to measure at least one parameter of the exhaust gas, and the control system is configured to independently adjust each of the oxidant-flow adjustment devices based, at least in part, on the parameter measured by the exhaust sensor.

52. 发明授权

US09879561B2 Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan 有权
公开(公告)号：US09879561B2
公开(公告)日：2018-01-30
申请号：US14626452
申请日：2015-02-19
申请人： SNECMA
发明人： Jean-Loic Herve Lecordix , Nils Bordoni , Guillaume Patrice Kubiak
IPC分类号： F01B25/00 , F01D17/16 , F02C7/042 , F02C9/20
CPC分类号： F01D17/162 , F02C7/042 , F02C9/20 , F05D2220/36
摘要： A bypass turbine engine including: an inner casing, an inter-duct casing and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including, at an upstream end, a movable fan with radial blades of which the free ends face the outer casing to compress an air flow at least in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually adjusting the pitch of the radial vanes including a single control ring and rods for connecting the control ring to each of said radial vanes, is provided.

53. 发明授权

US09863315B2 Gas turbine and operation method of gas turbine 有权
公开(公告)号：US09863315B2
公开(公告)日：2018-01-09
申请号：US14070805
申请日：2013-11-04
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Hiroki Takeda , Ryo Akiyama , Yasuo Takahashi
IPC分类号： F02C3/30 , F02C9/20 , F01D17/16 , F01K21/04
CPC分类号： F02C3/30 , F01D17/16 , F01K21/047 , F02C9/20 , F05D2260/2322 , F05D2270/082 , F05D2270/101 , F05D2270/16 , Y02E20/14 , Y02E20/16
摘要： A gas turbine having a compressor for compressing air, a combustor for taking in compressed air discharged from the compressor, mixing it with fuel, and burning them, and a turbine driven by combustion gas generated in the combustor, comprising: inlet guide vanes installed at a stage near an inlet of the compressor for adjusting a compressor flow rate by changing an attaching angle thereof, a steam injection mechanism for injecting steam to the combustor, a steam adjustment valve for adjusting the steam injection rate, and a steam rate control mechanism for adjusting an opening of the steam adjustment valve, a steam monitoring mechanism for monitoring the steam rate injected to the combustor, an air temperature monitoring mechanism for monitoring an atmospheric temperature, and a control unit for determining whether a restriction value of the steam injection rate using a temperature, an opening of the inlet guide vanes, and the steam injection rate as indexes is satisfied, and controlling at least one of a temperature of air flowing into the compressor, the steam injection rate, and the inlet guide vane opening.

54. 发明授权

US09797265B2 Stator vane adjusting device of a gas turbine 有权
公开(公告)号：US09797265B2
公开(公告)日：2017-10-24
申请号：US13833271
申请日：2013-03-15
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Dirk Soehner
IPC分类号： F01D17/16 , F01D9/00 , F04D29/56 , F01D9/04 , F02C9/20
CPC分类号： F01D9/00 , F01D9/04 , F01D17/162 , F02C9/20 , F04D29/563 , F05D2260/56 , F05D2270/58 , F05D2270/66
摘要： The present invention relates to a stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least two radial planes, as well as at least two stator vane adjusting rings connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device, characterized in that the actuating device is connected to the stator vane adjusting rings by means of a first transmission device and that a second transmission device, which is not coupled to the actuating device, is arranged essentially opposite to the first transmission device, with the second transmission device being connected to the stator vane adjusting rings.

55. 发明申请

US20170284308A1 2-SHAFT GAS TURBINE, AND THE CONTROL METHOD OF OPENING DEGREE OF INLET GUIDE VANE OF THE GAS TURBINE 审中-公开
公开(公告)号：US20170284308A1
公开(公告)日：2017-10-05
申请号：US15417743
申请日：2017-01-27
申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.
发明人： Chihiro MYOREN , Kenji NANATAKI , Yasuo TAKAHASHI , Kota KAWAMURA
IPC分类号： F02C9/20 , F02C3/10
CPC分类号： F02C9/20 , F02C3/10 , F02C9/22 , F02C9/28 , F02C9/54 , F05D2270/024 , F05D2270/304 , F05D2270/313 , F05D2270/331
摘要： A 2-shaft gas turbine has a controller which controls the opening degree of an air inlet guide vane to adjust the inlet mass flow rate to a compressor. The air inlet guide vane control unit includes a first control unit that adjusts the opening degree of the inlet guide vane to keep the speed of a high pressure turbine shaft constant; a control status confirmation unit that confirms the actual speed and the opening degree of the inlet guide vane; and a low ambient temperature correction unit that reduces the actual speed in a case where the actual speed is equal to or greater than a predetermined threshold value, the opening degree of the inlet guide vane is equal to or greater than a predetermined threshold value, and the ambient temperature is equal to or less than a predetermined threshold value.

56. 发明申请

US20170191427A1 SYSTEM AND METHOD OF TRANSFERRING POWER IN A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170191427A1
公开(公告)日：2017-07-06
申请号：US14987271
申请日：2016-01-04
申请人： Rolls Royce North American Technologies Inc
发明人： Charles L. McNeil , John Kusnierek
IPC分类号： F02C9/20 , F02C3/04 , F02C3/113 , F02K3/02
摘要： A method of extracting work from a convertible gas turbine engine having a core flowpath and a bypass flowpath. The method comprises operating the convertible gas turbine engine at a first volumetric flow rate through the core flowpath and a second volumetric flow rate through the bypass flowpath to produce a first work output of the convertible gas turbine engine; extracting the first work output via an unshrouded fan and a shaft at a first fan to shaft extraction ratio; altering the second volumetric flowrate through the bypass flowpath while maintaining the first work output; and extracting the first work output via an unshrouded fan and a shaft at a second fan to shaft extraction ratio.

57. 发明申请

US20170121027A1 ENHANCING ENGINE PERFORMANCE TO IMPROVE FUEL CONSUMPTION BASED ON ATMOSPHERIC RAIN CONDITIONS 有权
公开(公告)号：US20170121027A1
公开(公告)日：2017-05-04
申请号：US14927709
申请日：2015-10-30
申请人： GE Aviation Systems LLC
发明人： Nicholas Visser , Sridhar Adibhatla , David Michael Lax
IPC分类号： B64D31/06 , G01S13/02 , F02C9/20
CPC分类号： B64D31/06 , F02C9/00 , F02C9/20 , F02C9/28 , F02C9/54 , F05D2270/096 , F05D2270/311 , F05D2270/805 , G01S13/02 , G01S13/953 , Y02A90/18 , Y02T50/671
摘要： Systems and methods for enhancing engine performance based on atmospheric rain conditions are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a radar reflectivity measurement for each of the one or more points obtained using a radar device located on the aircraft. The method can further include determining an estimate of liquid water content for each of the one or more points based at least in part on the radar reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable stator vane) based at least in part on the estimate of liquid water content for at least one of the plurality of points.

58. 发明申请

US20170074173A1 CONTROL SYSTEM AND METHOD OF CONTROLLING A VARIABLE AREA GAS TURBINE ENGINE 审中-公开
标题翻译：控制系统和控制可变区域燃气涡轮发动机的方法
公开(公告)号：US20170074173A1
公开(公告)日：2017-03-16
申请号：US14851907
申请日：2015-09-11
申请人： United Technologies Corporation
发明人： Paul R. Hanrahan , Daniel Bernard Kupratis
IPC分类号： F02C9/20
CPC分类号： F02C9/20 , F02C9/22 , F05D2270/708
摘要： A method of controlling a variable area gas turbine engine includes, running the variable area turbine engine at initial settings, monitoring two sets of operating parameters of the engine at the initial settings, and deducing vane angles of adjustable vanes without directly measuring the vane angles from mapped data of the two sets of operating parameters of a similar engine operated while direct vane angle measurements were being recorded.
摘要翻译：控制可变区域燃气轮机的方法包括：在初始设定时运行可变区域涡轮发动机，在初始设定时监测发动机的两组运行参数，并且在不直接测量叶片角度的情况下推导可调叶片的叶片角度在记录直接叶片角度测量时操作的类似发动机的两组操作参数的映射数据。

59. 发明申请

US20160333797A1 Adaptive Engine Exhaust Signature Suppressor 审中-公开
标题翻译：自适应发动机排气签名抑制器
公开(公告)号：US20160333797A1
公开(公告)日：2016-11-17
申请号：US15090013
申请日：2016-04-04
申请人： Bell Helicopter Textron Inc.
发明人： Robert Michael Laramee , David L. Miller
IPC分类号： F02C9/20 , F02C3/04 , B64D33/04 , F02C7/141
CPC分类号： B64D33/04 , B64D2033/045 , F02K1/825 , F05D2220/90
摘要： An exhaust system has an engine exhaust plane associated with an entrance to the exhaust system, an exhaust exit plane associated with an exit of the exhaust system, a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane, and an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane.
摘要翻译：排气系统具有与排气系统的入口相关联的发动机排气平面，与排气系统的出口相关联的排气出口平面，相对于发动机排气平面可移动并且构造成选择性地与发动机排气平面相交的前盖，以及后盖，其能够相对于排气出口平面移动并且被配置为选择性地与排气出口平面相交。

60. 发明授权

US09488102B2 Gas turbines in mechanical drive applications and operating methods 有权
标题翻译：机械驱动应用中的燃气轮机和操作方法
公开(公告)号：US09488102B2
公开(公告)日：2016-11-08
申请号：US14655195
申请日：2013-12-18
申请人： Nuovo Pignone Srl
发明人： Marco Santini
IPC分类号： F02C3/00 , F02C6/00 , F02C3/05 , F02C7/275 , F02C9/20 , F02C9/28 , F01D15/10 , F02C3/10 , F01D15/00 , F02C7/268
CPC分类号： F02C6/00 , F01D15/005 , F01D15/10 , F02C3/05 , F02C3/10 , F02C7/268 , F02C7/275 , F02C9/20 , F02C9/28 , F05D2220/76 , F05D2260/4023
摘要： A drive system for driving a load by a gas turbine. The gas turbine comprises a gas generator having a gas-generator rotor and comprising at least one gas-generator compressor and one high-pressure turbine driving the gas-generator compressor. The gas turbine further comprises a power turbine having a power-turbine rotor, which is torsionally independent of the gas-generator rotor. The load is connected to the power-turbine rotor. The system further comprises an electric motor/generator mechanically connected to the gas-generator rotor and electrically connected to an electric power grid. The electric motor/generator is adapted to function alternatively: as a generator for converting mechanical power from the gas turbine into electrical power; and as a motor for supplementing driving power to the load. A set of movable nozzle guide vanes is arranged at the inlet of the power turbine.
摘要翻译：一种用于通过燃气轮机驱动负载的驱动系统。燃气轮机包括具有气体发生器转子并且包括至少一个气体发生器压缩机和驱动气体发生器压缩机的一个高压涡轮机的气体发生器。燃气轮机还包括具有动力涡轮转子的动力涡轮机，该动力涡轮机转子是扭转地独立于气体发生器转子的。负载连接到动力 - 水轮机转子。该系统还包括机电连接到气体发生器转子并电连接到电网的电动机/发电机。电动机/发电机适用于作为替代的功能：作为用于将来自燃气轮机的机械功率转换成电力的发电机; 并作为用于补充负载的驱动力的电动机。一组可动喷嘴导向叶片设置在动力涡轮机的入口处。

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