-
公开(公告)号：US11906166B2
公开(公告)日：2024-02-20
申请号：US17450897
申请日：2021-10-14
CPC分类号： F23R3/28 , F02K9/52 , F02K9/72 , F05D2260/963 , F05D2260/964 , F23R2900/00014
摘要： An injector device for an engine device for introducing a fluidic, in particular a liquid, fuel and a fluid, in particular liquid, oxidizing agent into a combustion chamber of the engine device is provided. The injector device defines a longitudinal axis and comprises at least one first injection element, which is configured in the form of a first fluid channel for fluidically connecting a first collection space for the fluidic oxidizing agent and the combustion chamber, and at least one second injection element, which is configured in the form of a second fluid channel for fluidically connecting a second collection space for the fluidic fuel and the combustion chamber. At least one first resonator element is associated with the at least one first injection element and/or at least one second resonator element is associated with the at least one second injection element.
-
公开(公告)号：US20170342912A1
公开(公告)日：2017-11-30
申请号：US15164946
申请日：2016-05-26
CPC分类号： F02C9/26 , F02C7/222 , F02C7/228 , F05D2220/32 , F05D2240/35 , F05D2260/964 , F23R3/28 , F23R3/346 , Y02T50/672
摘要： A gas turbine engine includes a combustion section, the combustion section including a plurality of fuel nozzles. A fuel delivery system for the gas turbine engine includes a feed tube and a fuel manifold fluidly connected to the feed tube for receiving fuel from the feed tube. The fuel delivery system also includes a pigtail fuel line fluidly connected to the fuel manifold and configured to fluidly connect to a fuel nozzle of the plurality of fuel nozzles when the fuel delivery system is installed in the gas turbine engine. In order to reduce an amount of hydraulic instability of a fuel flow through the fuel delivery system, at least one of the fuel manifold or the pigtail fuel line includes a means for damping a hydraulic instability within the fuel delivery system.
-
公开(公告)号：US20170328567A1
公开(公告)日：2017-11-16
申请号：US15152182
申请日：2016-05-11
CPC分类号： F23R3/28 , F02C7/22 , F02C9/28 , F02C9/54 , F02D41/30 , F05D2260/964 , F05D2270/092 , F23N1/002 , F23N5/003 , F23N5/242 , F23N2031/06 , F23N2041/20
摘要： A multivariable fuel control and estimator (MFCE) of a gas turbine engine for preventing combustor blowout is provided. The MFCE includes a first input port that receives controller requests and provide system usage commands, a second input port that receives measured disturbance values, a third input that receives system and component limits, a fourth input port that receives sensed parameters, a fuel system model of the fuel system of the gas turbine engine and an engine model of the engine system that includes the combustor of the gas turbine engine, a processor that generates a control signal for controlling the fuel valve and generates a control signal for controlling the actuator using the fuel system and engine model based on the controller requests, the measured disturbance values, the system and component limits, and the sensed parameters, and an output port that transmits the control signals to the fuel system.
-
4.发明授权公开(公告)号：US09644846B2
公开(公告)日：2017-05-09
申请号：US14248194
申请日：2014-04-08
CPC分类号： F23R3/34 , F05D2260/964 , F23M20/005 , F23R3/286 , F23R2900/00013 , F23R2900/03342
摘要： A gas turbine engine system including a first combustor having a first fuel nozzle and a second combustor having a second fuel nozzle. The system further includes a first acoustic adjuster having a first drive coupled to a first piston with a first fuel orifice. The first piston is disposed along a first fuel passage leading to the first fuel nozzle of the first combustor. The system further includes a second acoustic adjuster having a second drive coupled to a second piston with a second fuel orifice. The second piston is disposed along a second fuel passage leading to the second fuel nozzle of the second combustor.
-
公开(公告)号：US20170044996A1
公开(公告)日：2017-02-16
申请号：US15306574
申请日：2015-04-17
IPC分类号： F02C9/48
CPC分类号： F02C9/48 , F02C9/00 , F05D2260/964 , F23N5/16 , F23R2900/00013
摘要： A method for operating a burner assembly, in particular a burner assembly of a gas turbine, wherein an evaluation variable representing the combustion stability is determined and at least one control variable is altered, at least based on the determined evaluation variable, when the determined evaluation variable does not fall within a previously defined desired range, the desired range of the evaluation variable being constant over the entire output range of the machine, and wherein the evaluation variable is determined based on measured maximum actual amplitudes in previously defined frequency bands and measured actual outputs of the burner assembly.
摘要翻译： 一种用于操作燃烧器组件，特别是燃气轮机的燃烧器组件的方法，其中确定表示燃烧稳定性的评估变量，并且至少基于所确定的评估变量改变至少一个控制变量，当确定的评估 变量不在先前定义的期望范围内，评估变量的期望范围在机器的整个输出范围内是恒定的，并且其中评估变量基于先前定义的频带中测量的最大实际振幅和测量的实际值 燃烧器组件的输出。
-
6.发明申请公开(公告)号：US20160376929A1
公开(公告)日：2016-12-29
申请号：US14753384
申请日：2015-06-29
申请人： Siemens Energy, Inc.
CPC分类号： F01D25/30 , F01D25/04 , F01D25/162 , F05D2240/121 , F05D2260/964 , F15D1/0025
摘要： An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided.
摘要翻译： 提供了一种用于控制燃气轮机排气扩散器中的振动的装置。 该装置包括联接到涡轮机排气筒支柱的突起，用于控制燃气轮机扩散器中的冲击感应振荡。 受控的冲击诱导振荡使燃气轮机排气扩散器中的压力波动最小化，使得围绕涡轮排气气缸支柱的流体流动的不稳定性降低。 还提供了一种用于燃气轮机扩散器中的流体流动引起的振动的方法。
-
公开(公告)号：US20150315969A1
公开(公告)日：2015-11-05
申请号：US14268696
申请日：2014-05-02
IPC分类号： F02C7/22
CPC分类号： F02C7/222 , F05D2260/606 , F05D2260/96 , F05D2260/964 , F23R3/28 , F23R2900/00013
摘要： A fuel supply system includes a main fuel line path configured to route a fuel to a combustion inlet region and a secondary fuel line path fluidly coupled to the main fuel line path. The secondary fuel line path is configured to divert a portion of the fuel from the main fuel line path through a first segment of the secondary fuel line path and return the fuel to the main fuel line path through a second segment of the secondary fuel line path. An obstruction mechanism is located proximate the main fuel line path at an obstruction location and is configured to cyclically translate into the main fuel line path to cyclically alter a cross-sectional area of the main fuel line path to effectively oscillate fuel flow pressure into a combustion system.
摘要翻译： 燃料供给系统包括：主燃料路径路径，其被配置为将燃料路由到燃料入口区域和与主燃料路径路径流体耦合的二次燃料路径路径。 辅助燃料路径路径被配置成使来自主燃料管路路径的燃料的一部分通过二次燃料路径路径的第一段转向，并且通过第二燃料路径路径的第二段将燃料返回到主燃料路径路径 。 阻塞机构位于障碍物位置处的主燃料路径附近，并被构造成循环地平移到主燃料管线路径中以循环地改变主燃料管线路径的横截面面积，以有效地将燃料流动压力摆动到燃烧 系统。
-
公开(公告)号：US07966823B2
公开(公告)日：2011-06-28
申请号：US11327008
申请日：2006-01-06
CPC分类号： F02K1/822 , F02K1/386 , F05D2250/184 , F05D2250/611 , F05D2260/964 , Y02T50/675
摘要： A gas turbine engine augmentor includes an augmentor outer casing 502 and an annular augmentor liner 504 disposed radially within and radially separated from the augmentor outer casing 502 to form a generally annular augmentor liner cooling flow path 500 between the augmentor casing and the annular augmentor liner, and an augmentor flow splitter duct 506 disposed at the upstream end of the augmentor liner and radially between the augmentor outer casing 502 and the annular augmentor liner 504 and defining a splitter flow path 520 between the annular augmentor liner 504 and the annular augmentor flow splitter duct 506. A method of operating a gas turbofan engine including an augmentor includes directing a portion of fan bypass air into a generally annular augmentor liner cooling flow path 500 between an augmentor outer casing 502 and an annular augmentor liner 504, directing a portion of the air in the augmentor liner cooling flow path 500 into a splitter flow path 520 disposed radially outside the augmentor liner 504 and maintaining positive backflow pressure margin between air flow within the splitter flow path and the augmentor liner cooling flow path 500.
摘要翻译： 燃气涡轮发动机增压器包括增压器外壳体502和径向设置在增压器外壳体502内并与放大器外壳体502径向分离的环形增压器衬垫504，以在增压器壳体和环形增压器衬套之间形成大致环形的增强衬套冷却流路500， 以及设置在增压器衬套的上游端并且在径向上在增压器外壳体502和环形增压器衬套504之间并且在环形增压器衬套504和环形增压器流量分配器管道之间限定分流器流路520的增压器分流器管道506 操作包括增压器的气体涡轮风扇发动机的方法包括将风扇旁路空气的一部分引导到增压器外壳体502和环形增压器衬套504之间的大致环形增压器衬套冷却流路500中，引导空气的一部分 在增压器衬套冷却流路500中成径向设置的分流器流路520 在增压器衬套504外部并且保持分流器流动路径内的气流和增压器衬套冷却流动路径500之间的正回流压力裕度。
-
公开(公告)号：US12086517B2
公开(公告)日：2024-09-10
申请号：US17110099
申请日：2020-12-02
申请人： GTL Company
发明人： Paul Gloyer , Eric Jacob , Jonathan French , Joshua Batterson , Tina Rice , Gary Flandro
IPC分类号： G06F30/28 , F02K9/52 , F02K9/62 , F02K9/64 , F02K9/97 , F23R3/00 , F23R3/18 , G06F30/15 , G06F30/20 , G06F111/10
CPC分类号： G06F30/28 , F02K9/52 , F02K9/62 , F02K9/97 , F23R3/002 , F23R3/18 , G06F30/15 , G06F30/20 , F02K9/64 , F05D2260/81 , F05D2260/964 , F23R2900/00018 , G06F2111/10
摘要： A method comprising performing simulations to determine energy transfer between the bulk fluid motion of gases through a combustion chamber and resonant acoustic modes of the combustion chamber using a simulation model. The method also comprises configuring one or more combustion chamber parameters for the simulation model to shape the resonant acoustic modes to diminish coupling between the resonant acoustic modes and driving mechanisms at a head portion of the combustion chamber and to enhance coupling between the resonant acoustic modes and damping mechanisms at an aft portion of the combustion chamber. The method further comprises determining whether the combustion chamber meets a predetermined performance level in response to determining that the combustion chamber meets a predetermined combustion stability level.
-
公开(公告)号：US11668194B2
公开(公告)日：2023-06-06
申请号：US17044813
申请日：2019-03-14
发明人： Martin Naismith
IPC分类号： F01D5/02
CPC分类号： F01D5/026 , F01D5/027 , F05D2230/60 , F05D2240/24 , F05D2240/60 , F05D2260/964
摘要： A rotor shaft cap for a gas turbine has a disk-shaped body defining a first axial face, a second axial face, and an outer radial face. The disk-shaped body has a first annular jaw provided on the first axial face. The first annular jaw includes a plurality of teeth projecting from the first axial face. A plurality of apertures are defined by the disk-shaped body, each aperture of the plurality of apertures extends through the disk-shaped body along an axial direction.
-
-
-
-
-
-
-
-
-
搜索结果
67 条记录 (耗时 0.022 秒)
