-
公开(公告)号：US20180298825A1
公开(公告)日：2018-10-18
申请号：US15486872
申请日：2017-04-13
Applicant: General Electric Company
Inventor： Fei Han
CPC classification number: F02C7/222 , F05D2220/32 , F05D2260/96 , F23R3/28 , F23R2900/00013 , F23R2900/00014
Abstract: The present disclosure is directed to a fuel manifold assembly for a gas turbine engine. The fuel manifold assembly defines a walled conduit through which a fuel flows in a fuel passage. The walled conduit defines a first end and a second end opposite of the first end along a length of the walled conduit. The fuel manifold assembly includes an exit manifold to which a fuel nozzle attaches. The fuel manifold assembly includes a damper assembly coupled to the walled conduit of the fuel manifold assembly. The damper assembly includes a walled tube extended from the walled conduit. The damper assembly further includes a walled enclosure defining a damper cavity therein. The damper cavity is in fluid communication with a damper passage defined within the walled tube, and the damper passage is in fluid communication with the fuel passage.
-
公开(公告)号：US20180258865A1
公开(公告)日：2018-09-13
申请号：US15453421
申请日：2017-03-08
Applicant: General Electric Company
IPC: F02C9/28
CPC classification number: F02C9/28 , F01D19/00 , F05D2220/32 , F05D2260/964 , F05D2270/082 , F05D2270/11 , F05D2270/20 , F05D2270/301 , F05D2270/333 , F05D2270/706 , F23N5/16 , F23N2041/20 , F23R2900/00013
Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for closed loop control of a gas turbine. An example apparatus includes a frequency band splitter to separate a combustion pulsation signal into a plurality of frequency bands. The example apparatus includes a plurality of subcontrollers, each subcontroller corresponding to one of the frequency bands. Each subcontroller is to be activated at an amplitude threshold associated with the normal operating set point of the frequency band and to generate a correction value while the corresponding frequency band is operating beyond the amplitude threshold. The example apparatus includes a net correction output calculator to aggregate the correction values to generate an aggregated correction value. The example apparatus includes a subcontroller limiter having a maximum limit and/or a minimum limit to inhibit subcontroller(s) from increasing their respective correction values when aggregated correction value is to exceed the maximum limit and/or minimum limit.
-
公开(公告)号：US20180017017A1
公开(公告)日：2018-01-18
申请号：US15208141
申请日：2016-07-12
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Steven Wesley Tomlinson , Victor Lewis Oechsle
CPC classification number: F02K1/46 , F02C3/04 , F02C7/057 , F02C9/18 , F02K7/16 , F05D2220/323 , F05D2220/80 , F05D2240/35 , F23R3/005 , F23R3/06 , F23R3/20 , F23R2900/00013 , Y02T50/675
Abstract: A gas turbine engine assembly for high Mach number operation comprising an inlet turbine assembly, a gas turbine engine core, and a ramburner arranged along a common axis. During high Mach number operation, working fluid flow is selectively directed through the inlet turbine assembly to cool the working fluid prior to entry in the gas turbine engine core. Working fluid exiting the gas turbine engine core may be reheated by a ramburner for thrust augmentation.
-
4.发明授权公开(公告)号：US09845732B2
公开(公告)日：2017-12-19
申请号：US14288875
申请日：2014-05-28
Applicant: General Electric Company
CPC classification number: F02C7/24 , F01D9/023 , F05B2260/96 , F05B2260/966 , F05D2260/96 , F23D2210/00 , F23N1/022 , F23N5/242 , F23R3/28 , F23R3/346 , F23R2900/00013 , F23R2900/00014
Abstract: A system includes a gas turbine engine having a first combustor and a second combustor. The first combustor includes a first fuel conduit having a first plurality of injectors. The first plurality of injectors are disposed in a first configuration within the first combustor along a first fuel path, and the first plurality of injectors are configured to route a fuel to a first combustion chamber. The system further includes a second combustor having a second fuel conduit having a second plurality of injectors. The second plurality of injectors are disposed in a second configuration within the second combustor along a second fuel path, and the second plurality of injectors are configured to route the fuel to a second combustion chamber. The second configuration has at least one difference relative to the first configuration.
-
公开(公告)号：US20170356344A1
公开(公告)日：2017-12-14
申请号：US15687598
申请日：2017-08-28
Applicant: General Electric Company
Inventor： Sarah Lori Crothers , Matthew Durham Collier , Scott Edward Sherman , Joseph Vincent Citeno
CPC classification number: F02C7/24 , F01D25/04 , F01D25/06 , F02C9/18 , F05D2260/96 , F05D2270/083 , F05D2270/10 , F05D2270/14 , F23R2900/00013
Abstract: Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency. Specifically, the compressor discharge temperature may be modified by adjusting the inlet guide vanes of the compressor or by adjusting a temperature of air entering the compressor.
-
Patent Agency Ranking
公开(公告)号：US09765975B2
公开(公告)日：2017-09-19
申请号：US13233369
申请日：2011-09-15
Applicant: Hans Peter Knöpfel , Adnan Eroglu
Inventor： Hans Peter Knöpfel , Adnan Eroglu
CPC classification number: F23R3/346 , F23C2900/07002 , F23N2037/02 , F23R3/286 , F23R2900/00013
Abstract: A combustion chamber of a gas turbine including first and second premixed fuel supply devices connected to a combustion device having first zones connected to the first premixed fuel supply devices and second zones connected to the second premixed fuel supply devices. The second fuel supply devices are shifted along a combustion device longitudinal axis with respect to the first fuel supply devices. The first zones are axially upstream of the second premixed fuel supply devices.
-
公开(公告)号：US09671797B2
公开(公告)日：2017-06-06
申请号：US13767933
申请日：2013-02-15
Applicant: Gas Turbine Efficiency Sweden AB
Inventor： Christopher Chandler
CPC classification number: G05D17/00 , F02C9/28 , F05D2260/80 , F05D2270/082 , F05D2270/083 , F05D2270/303 , F05D2270/31 , F23N1/002 , F23N5/003 , F23N5/242 , F23N2041/20 , F23R3/34 , F23R2900/00013
Abstract: Provided herein is a system and method for tuning the operation of a turbine and optimizing the mechanical life of a heat recovery steam generator. Provided therewith is a turbine controller, sensor means for sensing operational parameters, control means for adjusting operational control elements. The controller is adapted to tune the operation of the gas turbine in accordance preprogrammed steps in response to operational priorities selected by a user. The operational priorities preferably comprise optimal heat recovery steam generator life.
-
公开(公告)号：US20160377285A1
公开(公告)日：2016-12-29
申请号：US15192013
申请日：2016-06-24
Inventor： Jin Woo SONG
CPC classification number: F23N1/02 , F02C9/28 , F05D2260/964 , F05D2270/14 , F23N5/02 , F23N5/16 , F23N5/24 , F23N2037/02 , F23N2041/20 , F23R3/00 , F23R2900/00013
Abstract: The present disclosure provides a method for controlling combustor cans of a gas turbine. Detectors disposed on combustor cans are operable to detect combustion vibration values of the combustor cans. The combustion vibration value is compared to a reference value. Combustor cans having a combustion vibration value greater than a reference value are assigned to a first group, and combustor cans having a combustion vibration value not greater than the reference value are assigned to a second group. The output of each combustor can in the first group is regulated to lower the combustion vibration value, thereby improving the stability of the gas turbine.
Abstract translation: 本公开提供了一种用于控制燃气轮机的燃烧器罐的方法。 设置在燃烧器罐上的检测器可操作以检测燃烧器罐的燃烧振动值。 将燃烧振动值与参考值进行比较。 具有大于参考值的燃烧振动值的燃烧器罐被分配给第一组，并且具有不大于参考值的燃烧振动值的燃烧器罐被分配给第二组。 调节第一组中每个燃烧室的输出，以降低燃烧振动值，从而提高燃气轮机的稳定性。
-
9.发明申请BURNER FOR A GAS TURBINE AND METHOD FOR REDUCING THERMOACOUSTIC OSCILLATIONS IN A GAS TURBINE 审中-公开用于气体燃烧器的燃烧器和用于减少气体涡轮机中的热膨胀振荡的方法公开(公告)号：US20160195271A1
公开(公告)日：2016-07-07
申请号：US14911766
申请日：2014-09-23
Applicant: SIEMENS AKTIENGESELLSCHAFT
Inventor： Berthold Köstlin , Bernd Prade
CPC classification number: F23M20/005 , F23C2900/06043 , F23D14/70 , F23D2900/00008 , F23R3/286 , F23R3/346 , F23R2900/00002 , F23R2900/00013
Abstract: A burner for a gas turbine, has an air passage supplied with compressed air and a fuel passage supplied with fuel gas, each passage has a main outlet opening leading into the combustion chamber of the gas turbine, the air and fuel passages connected fluidically together via a connection duct arranged upstream of the main outlet openings. The burner is configured such that, when air passage is supplied with compressed air and fuel passage is supplied with fuel gas, a portion of the fuel gas flowing in the fuel passage flows via at least one connection duct into the air passage and, for combustion thereof, is introduced through the main outlet opening of the air passage into the interior of the combustion chamber and a remaining portion of the fuel gas is introduced through the main outlet opening of the fuel passage into the interior of the combustion chamber.
Abstract translation: 燃气轮机的燃烧器具有供给压缩空气的空气通道和供给燃料气体的燃料通路，每个通道具有通向燃气轮机的燃烧室的主出口，空气和燃料通道流体连接在一起，通过 连接管道，布置在主出口开口的上游。 燃烧器构造成使得当空气通道被供应压缩空气并且燃料通道被供应燃料气体时，在燃料通道中流动的一部分燃料气体经由至少一个连接管道流入空气通道并用于燃烧 其通过空气通道的主出口开口引入燃烧室的内部，并且燃料气体的剩余部分通过燃料通道的主出口被引入燃烧室的内部。
-
公开(公告)号：US20160108820A1
公开(公告)日：2016-04-21
申请号：US14982691
申请日：2015-12-29
Applicant: Gas Turbine Efficiency Sweden AB
Inventor： Christopher Chandler
CPC classification number: G05B13/00 , F02C9/28 , F02C9/40 , F05D2260/80 , F05D2270/082 , F05D2270/083 , F05D2270/303 , F05D2270/31 , F23K2301/204 , F23K2301/206 , F23N1/002 , F23N5/003 , F23N5/242 , F23N2037/08 , F23N2041/20 , F23R3/34 , F23R3/36 , F23R2900/00013 , G05B19/05 , G05B2219/1204
Abstract: Provided herein is a method for automated control of the gas turbine fuel composition through automated modification of the ratio of fuel gas from multiple sources. The method includes providing first and second fuel sources. The method further includes sensing the operational parameters of a turbine and determining whether the operational parameters are within preset operational limits. The method also adjusting the ration of the first fuel source to the second fuel source, based on whether the operational parameters are within the preset operational limits.
-
-
-
-
-
-
-
-
-
Search Results
334
records
(took 0.025 seconds)
