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81. 发明授权

US5537864A Apparatus and method for determining and controlling combustor primary zone temperature 失效
标题翻译：用于确定和控制燃烧器主区温度的装置和方法
公开(公告)号：US5537864A
公开(公告)日：1996-07-23
申请号：US500027
申请日：1995-07-10
申请人： Virendra M. Sood
发明人： Virendra M. Sood
IPC分类号： F02C9/00 , F02C9/20 , F02C9/28 , F23R3/26 , G01L3/26
CPC分类号： F23R3/26 , F05B2270/303
摘要： An apparatus and method for determining and maintaining the temperature of a primary zone of a combustor of a gas turbine engine at a predetermined level is provided. A first sensor senses the inlet air temperature of the combustor, a second sensor senses the inlet temperature of the turbine gases, and a third sensor senses the speed of or measures the load of the engine. Based on the first and second sensed temperatures, the speed or the load, and the preestablished combustor design parameter, the primary zone temperature of the combustor T.sub.pz is calculated. A controller maintains the combustor at a predetermined setpoint temperature by moving an air bleed valve between open and closed position, or a plurality of inlet guide vanes between open and closed positions.
摘要翻译：提供了一种用于确定和保持燃气涡轮发动机的燃烧器的主区域的温度达预定水平的装置和方法。第一传感器感测燃烧器的入口空气温度，第二传感器感测涡轮气体的入口温度，第三传感器感测发动机的负载的速度或测量发动机的负载。基于第一和第二感测温度，速度或负载以及预先建立的燃烧器设计参数，计算燃烧器Tpz的主区域温度。控制器通过在打开和关闭位置之间移动排气阀或在打开和关闭位置之间的多个入口导向叶片将燃烧器维持在预定的设定点温度。

82. 发明授权

US4821506A Radial turbine with variable axial nozzle 失效
标题翻译：径向涡轮机带可变轴向喷嘴
公开(公告)号：US4821506A
公开(公告)日：1989-04-18
申请号：US105866
申请日：1987-10-08
申请人： Colin Rodgers
发明人： Colin Rodgers
IPC分类号： F01D17/16 , F02C3/05 , F02C7/18 , F02C9/20 , F02C9/22
CPC分类号： F02C9/20 , F01D17/162 , F02C3/05 , F05D2220/50
摘要： Thermal degradation of variable nozzle components in a gas turbine power plant is minimized by a construction including a radial outflow compressor 16 on a shaft 10 with a radial inflow turbine 18, combustion gas delivery path 78 which is generally concentric about the shaft 10, a compressed gas delivery path 40 from the compressor 16 to the turbine 18 which is parallel to the axial combustion gas path 78 and rotatably mounted guide vanes 80 located in the axial combustion path 78 which are provided with control elements 82 that extend through the compressed gas path 40 so as to be cooled by compressed gas flowing in such path 40.
摘要翻译：燃气轮机发电厂中可变喷嘴部件的热降解通过包括径向流入涡轮18的轴10上的径向流出压缩机16，与轴10大致同心的燃烧气体输送路径78，气体输送路径40从压缩机16流向涡轮18，涡轮机18平行于轴向燃烧气体路径78，并且可转动地安装在轴向燃烧路径78中的导向叶片80设置有延伸穿过压缩气体路径40的控制元件82 以便通过在这种路径40中流动的压缩气体来冷却。

83. 发明授权

US4430043A Variable stator vane operating mechanism for turbomachines 失效
标题翻译：用于涡轮机的可变定子叶片操作机构
公开(公告)号：US4430043A
公开(公告)日：1984-02-07
申请号：US272550
申请日：1981-06-11
申请人： Ronald W. Knight , Clive E. Olive
发明人： Ronald W. Knight , Clive E. Olive
IPC分类号： F01D17/16 , F02C9/20 , F04D29/56 , F01B25/02
CPC分类号： F01D17/162 , F04D29/563
摘要： A variable stator vane operating mechanism for a gas turbine engine includes a plurality of unison rings 21,22 and 23 each connected by a drag link 18,19 and 20 respectively to a pivoting beam 14. The unison rings are connected to each of vanes 10 in a stator vane row by first arms 24. In order to minimize side loads on the unison rings by the drag links during pivoting of the beam, the beam is connected at its free end to a second arm 30 which is pivotable about an axis 28 by means of a torque tube 26 or other suitable actuator, and the length of the second arm 30 between the axis 28 and its point of connection 44 to the beam is made as nearly as possible equal to the length of the first arms 24. By this means the fore and aft movement of the beam can be matched to the fore and aft movement of the unison rings, or at least in the case of one of them, and the drag links remain substantially in the plane of the unison rings.
摘要翻译：用于燃气涡轮发动机的可变定子叶片操作机构包括多个共同环21,22和23，每个共同环21,22和23分别通过牵引连杆18,19和20连接到枢转梁14.共振环连接到每个叶片10 在第一臂24的定子叶片行中。为了在梁的枢转期间通过牵引连杆最小化协调环上的侧向载荷，梁在其自由端处连接到第二臂30，第二臂30可绕轴线28枢转通过扭矩管26或其他合适的致动器，并且第二臂30在轴线28与其到梁的连接点44之间的长度尽可能地等于第一臂24的长度。通过这意味着梁的前后运动可以与协调环的前后运动匹配，或者至少在其中一个的情况下，并且牵引连杆基本上保持在协调环的平面中。

84. 发明授权

US4005572A Gas turbine engine control system 失效
标题翻译：燃气轮机发动机控制系统
公开(公告)号：US4005572A
公开(公告)日：1977-02-01
申请号：US569579
申请日：1975-04-18
申请人： William A. Giffhorn
发明人： William A. Giffhorn
IPC分类号： F01D5/04 , F02C3/08 , F02C7/18 , F02C9/20 , F23R3/32 , F02C9/04
CPC分类号： F01D5/045 , F01D5/048 , F02C3/085 , F02C7/18 , F02C9/20 , F23R3/32 , Y02T50/673 , Y02T50/675
摘要： A gas turbine engine which comprises a rotary air compressor and a gas turbine, each with a rotor mounted on opposite ends of a rotor shaft, which is journalled in a housing positioned between the compressor and the turbine. The housing includes reduction gears. A combustion chamber is connected between the outlet air duct of the compressor and the hot gas inlet duct of the turbine. The power output is controlled by varying the air inlet to the compressor by means of an axially moving throttle control which limits the air passage into the compressor, either alone or in conjunction with variable angle compressor inlet pre-whirl vanes. It is also controlled by a shroud which surrounds the nozzle blades of the turbine. The shroud can be moved axially to limit the cross-section of flow of hot gas to the turbine blades. Auxiliary blades are mounted on the back of the turbine rotor which serves to draw cool outside air into the space between the housing and the hot gas inlet duct of the turbine, and up along the back surface of the turbine rotor, and through a plurality of axial holes drilled through the hub of the turbine rotor, all of which helps to cool the critical parts of the engine. Improved construction of the turbine rotor and the compressor rotor involves assembling the unit from a plurality of separate pieces which serve to provide a combined radial and axial flow of gases around the rotor blades. The fuel supply is controlled to be a function of the flow of air into the combustion chamber.
摘要翻译：一种燃气涡轮发动机，其包括旋转空气压缩机和燃气轮机，每个转子安装在转子轴的相对端上，该转子安装在位于压缩机和涡轮机之间的壳体中。壳体包括减速齿轮。燃烧室连接在压缩机的出风管和涡轮的热气进口管之间。通过轴向移动的节流控制改变压缩机的空气入口来控制动力输出，该节流控制将空气通道限制在压缩机中，单独地或与可变角度的压缩机入口预旋翼相结合。它还由围绕涡轮机的喷嘴叶片的护罩控制。护罩可以轴向移动以限制热气体流向涡轮机叶片的横截面。辅助叶片安装在涡轮机转子的背面，其用于将外部空气抽吸到壳体和涡轮机的热气体入口管道之间的空间中，并且沿着涡轮机转子的后表面，并且通过多个通过涡轮机转子的轮毂钻出的轴向孔，这些都有助于冷却发动机的关键部件。涡轮转子和压缩机转子的改进结构包括从多个单独的部件组装单元，其用于提供围绕转子叶片的气体的径向和轴向组合。燃料供应被控制为进入燃烧室的空气的流动的函数。

85. 发明授权

US3836822A Control apparatus for temporarily reducing turbine torque 失效
标题翻译：用于临时减少涡轮扭矩的控制装置
公开(公告)号：US3836822A
公开(公告)日：1974-09-17
申请号：US28486572
申请日：1972-08-30
申请人： KRAFTWERK UNION AG
发明人： SCHONFELD P , BORGMANN H , PLOHN G
IPC分类号： F01D21/00 , F01D21/02 , F02C9/20 , H02P9/04
CPC分类号： F01D21/02
摘要： In the event the load on a generator of a turbo generator is temporarily removed, either partially or completely, the turbine setting or control valves are closed by providing a brief interruption of a power control device until the malfunctioning part of the system is disconnected and power is again called for by the system. This is accomplished by providing control apparatus which is operable in parallel to the power control device and which responds to load jumps exceeding predetermined and adjustable valves to interrupt the power control device and thereby close the turbine setting valves.
摘要翻译：在涡轮发电机的发电机上的负载部分地或完全地暂时移除的情况下，通过提供功率控制装置的短暂中断来关闭涡轮机设置或控制阀，直到系统的故障部分断开并且电力被系统再次呼叫。这通过提供与电力控制装置并行操作并且响应于超过预定和可调节阀的负载跳跃的控制装置来实现，以中断电力控制装置，从而关闭涡轮机设定阀。

86. 发明授权

US3720217A Fluidic systems 失效
标题翻译：流体系统
公开(公告)号：US3720217A
公开(公告)日：1973-03-13
申请号：US3720217D
申请日：1970-03-25
申请人： PLESSEY CO LTD
发明人： MATTHEWS R , FITZMAURICE C
IPC分类号： F02C9/20 , F04B53/10 , F04D27/02 , F15B9/06 , F15C1/00 , G05D16/18 , F15C1/12 , F15C1/16
CPC分类号： F15C1/002 , F02C9/20 , F04B53/1092 , F04D27/0246 , F15B9/06 , G05D16/18 , Y10T137/2071 , Y10T137/2147
摘要： A fluidic control system includes a pair of fluid restrictors connected in series whereby a tapping between them provides an output pressure which is a fraction of the input pressure. A planar jet collector gives an output which is a non-linear function of the input pressure. Thus, when both the jet collector and the orifices or restrictors are supplied with fluid from the same source then their difference in output pressures will vary as a function of input pressure. The output pressure difference is communicated to a fluidic proportional amplifier whose output pressure can be used to control the bleed valve or inlet guide vane of a gas turbine whence the input fluid pressure is derived.
摘要翻译：流体控制系统包括串联连接的一对流体限制器，由此在它们之间的攻丝提供输入压力，该输出压力是输入压力的一部分。平面喷射收集器给出输出，该输出是输入压力的非线性函数。因此，当喷射收集器和孔口或节流器都从相同的源供应流体时，其输出压力的差异将随输入压力的函数而变化。输出压力差被传送到流体比例放大器，其输出压力可用于控制输入流体压力的燃气轮机的排放阀或入口引导叶片。

87. 发明授权

US3657881A Gas turbine control with prewhirl of air entering the compressor 失效
标题翻译：具有进口压缩机空气的燃气涡轮机控制
公开(公告)号：US3657881A
公开(公告)日：1972-04-25
申请号：US3657881D
申请日：1969-09-02
申请人： GEN MOTORS CORP
发明人： AMANN CHARLES A , RUCINS ERIK H
IPC分类号： F02C9/20 , F02C9/54 , F02C9/56 , F02C9/14
CPC分类号： F02C9/54 , F02C9/20 , F02C9/56 , Y10T477/40
摘要： A vehicle turbine of the gas-coupled type propels the vehicle through a change-speed transmission. To reduce vehicle acceleration time with an acceptable penalty with respect to fuel consumption, the compressor of the engine has variable inlet guide vanes which are shifted into a positive prewhirl angle at idling speeds when the transmission is shifted into a drive condition. Thus the engine gas generator has a low speed idle, with axially oriented guide vanes and normal air entrance, when the transmission is in neutral, and a high speed idle with positive prewhirl when the transmission is in drive condition. Also, the vanes are shifted at full speed of the gas generator to provide negative prewhirl and thus reduce the engine speed corresponding to maximum power output. Because of the higher idle and lower maximum speeds, the acceleration time of the gas generator, and thus of the power turbine, is reduced. Because positive prewhirl reduces compressor pressure ratio at the high speed idle, the power turbine does not have an undue tendency to cause creep of the vehicle in the high speed idle.
摘要翻译：气体联接式的车辆涡轮通过变速传动推动车辆。为了以相对于燃料消耗的可接受的惩罚来减少车辆加速时间，发动机的压缩机具有可变的入口导向叶片，当变速器转换到驱动条件时，它们以空转速度偏移到正的预旋转角度。因此，发动机气体发生器具有低速怠速，当变速器处于空档状态时，具有轴向定向的导向叶片和正常空气入口，以及当变速器处于驱动状态时具有正向预热的高速怠速。此外，叶片以气体发生器的全速移动以提供负的前翅，并因此降低对应于最大功率输出的发动机转速。由于较高的怠速和较低的最大速度，所以气体发生器和动力涡轮机的加速时间减小。因为正偏压在高速怠速时降低了压缩机压力比，所以动力涡轮机不会在高速怠速时引起车辆蠕变的不适当倾向。

88. 发明公开

US20240352866A1 ACTIVE CLEARANCE CONTROL ASSEMBLY 审中-公开
公开(公告)号：US20240352866A1
公开(公告)日：2024-10-24
申请号：US18354021
申请日：2023-07-18
申请人： General Electric Company , GE Avio S.r.l.
发明人： Randy M. Vondrell , Kevin William Caldwell , John Carl Glessner , Javier Barba Fuentes , Dorota Kopkowicz
IPC分类号： F01D11/20 , F02C9/20
CPC分类号： F01D11/20 , F05D2260/213
摘要： A gas turbine engine includes a fan section, an engine inlet, and a fan duct splitter in serial flow order. The fan duct splitter splits an airflow entering the engine inlet from the fan section into a fan duct and a core duct. The core duct includes a compressor section, a combustion section, and a turbine section in serial flow order. A duct assembly is coupled to the fan duct to extract a portion of a fan duct airflow passing through the fan duct and deliver the portion of the fan duct airflow to an active clearance control mechanism of the turbine section.

89. 发明授权

US11939924B2 Synchronized air modulating system 有权
公开(公告)号：US11939924B2
公开(公告)日：2024-03-26
申请号：US17958682
申请日：2022-10-03
申请人： Raytheon Technologies Corporation
发明人： Nicholas W. Kantany , Edward Boucher , Kristine Marie Carnavos , Robert Russell Mayer , Donald W. Peters
IPC分类号： F02C7/28 , F02C9/20 , F02K3/075 , F02K3/115
CPC分类号： F02C7/28 , F02C9/20 , F02K3/075 , F02K3/115
摘要： A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

90. 发明授权

US11781490B2 Operability geared turbofan engine including compressor section variable guide vanes 有权
公开(公告)号：US11781490B2
公开(公告)日：2023-10-10
申请号：US17579938
申请日：2022-01-20
申请人： RAYTHEON TECHNOLOGIES CORPORATION
发明人： Glenn Levasseur , Gabriel L. Suciu , Gary M. Stetson
IPC分类号： F02C7/36 , F02C3/06 , F02C7/32 , F01D17/16 , F02C9/20
CPC分类号： F02C7/36 , F01D17/162 , F02C3/064 , F02C7/32 , F02C9/20 , F05D2220/32 , F05D2260/4031
摘要： A gas turbine engine includes a propulsor having a plurality of blades, a compressor section including a first compressor and a second compressor aft of the first compressor. The first compressor includes at least one array of first variable guide vanes that control operation of the first compressor. The second compressor includes at least one array of second variable guide vanes that control operation of the second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture is driven by the second turbine for rotating the propulsor.

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