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40 条记录 (耗时 0.022 秒)

    FUEL INJECTOR HAVING TIP COOLING
    6.
    发明申请
    FUEL INJECTOR HAVING TIP COOLING 有权
    燃油喷射器具有提示冷却

    公开(公告)号：US20120132725A1

    公开(公告)日：2012-05-31

    申请号：US12957232

    申请日：2010-11-30

    申请人： Constantin Dinu

    发明人： Constantin Dinu

    IPC分类号： B05B15/00

    CPC分类号： F23D11/38 ,  C10J3/506 ,  C10J2200/152 ,  C10J2300/0959 ,  C10J2300/0976 ,  C10J2300/1653 ,  C10J2300/1678 ,  F23D1/005 ,  F23D2214/00 ,  F23D2900/00006 ,  Y02E20/16 ,  Y02E20/18

    摘要： According to various embodiments, a system includes a gasification fuel injector. The gasification fuel injector includes a tip portion, an annular coolant chamber disposed in the tip portion, a recessed surface for cooling control and a first structural support extending through the annular coolant chamber. The first structural support divides the annular coolant chamber into a first passage and a second passage.

    摘要翻译： 根据各种实施例，系统包括气化燃料喷射器。 气化燃料喷射器包括尖端部分，设置在尖端部分中的环形冷却剂室，用于冷却控制的凹陷表面和延伸穿过环形冷却剂室的第一结构支撑件。 第一结构支撑件将环形冷却剂室分成第一通道和第二通道。

    Control Systems and Method for Controlling a Load Point of a Gas Turbine Engine
    7.
    发明申请
    Control Systems and Method for Controlling a Load Point of a Gas Turbine Engine 有权
    用于控制燃气轮机发动机负载点的控制系统和方法

    公开(公告)号：US20110308256A1

    公开(公告)日：2011-12-22

    申请号：US13218712

    申请日：2011-08-26

    申请人： Constantin Dinu

    发明人： Constantin Dinu

    IPC分类号： F02C9/00

    CPC分类号： F02C9/54 ,  F02K1/16 ,  F05D2270/082 ,  F05D2270/0831 ,  F05D2270/3013 ,  F05D2270/303

    摘要： Control systems and a method for controlling a load point of a gas turbine engine are provided. A control system includes a controller that receives a temperature signal and a pressure signal associated with exhaust gases from the gas turbine engine. The controller is further configured to generate the fuel control signal. The controller is further configured to generate an actuator control signal such that flow restriction member is moved from the first operational position to the second operational position to restrict the flow path such that the exhaust gases have a temperature level within a desired turndown temperature range, the pressure level in the exhaust gases is less than a threshold pressure level, and the load point of the gas turbine engine is adjusted to toward a target load point.

    摘要翻译： 提供了控制系统和用于控制燃气涡轮发动机的负载点的方法。 控制系统包括控制器，其接收与来自燃气涡轮发动机的废气相关联的温度信号和压力信号。 控制器还被配置为产生燃料控制信号。 控制器还被配置为产生致动器控制信号，使得流量限制构件从第一操作位置移动到第二操作位置，以限制流动路径，使得废气具有在期望的向下温度范围内的温度水平， 废气中的压力水平小于阈值压力水平，并且将燃气涡轮发动机的负荷点调整为朝向目标负荷点。

    COOLING CHAMBER ASSEMBLY FOR A GASIFIER
    9.
    发明申请
    COOLING CHAMBER ASSEMBLY FOR A GASIFIER 审中-公开
    用于气化器的冷却室组件

    公开(公告)号：US20100325956A1

    公开(公告)日：2010-12-30

    申请号：US12494434

    申请日：2009-06-30

    申请人： Constantin Dinu ,  Judeth Brannon Corry ,  James Michael Storey ,  Denise Marie Rico ,  Richard L. Zhao

    发明人： Constantin Dinu ,  Judeth Brannon Corry ,  James Michael Storey ,  Denise Marie Rico ,  Richard L. Zhao

    IPC分类号： C10J3/20

    CPC分类号： C10J3/485 ,  C10J3/526 ,  C10J3/74 ,  C10J3/76 ,  C10J3/84 ,  C10J3/845 ,  C10J2300/093 ,  C10J2300/0943 ,  C10J2300/0956 ,  C10J2300/0959

    摘要： A gasifier includes a combustion chamber in which a combustible fuel is burned to produce a syngas and a particulated solid residue. A cooling chamber having a liquid coolant is disposed downstream of the combustion chamber. A dip tube is disposed coupling the combustion chamber to the cooling chamber. The syngas is directed from the combustion chamber to the cooling chamber via the dip tube to contact the liquid coolant and produce a cooled syngas. An asymmetric or symmetric liquid separator is disposed proximate to an exit path of the cooling chamber and configured to remove entrained liquid content from the cooled syngas directed through the annular passage to the exit path.

    摘要翻译： 气化器包括燃烧室，其中燃烧可燃燃料以产生合成气和颗粒状固体残余物。 具有液体冷却剂的冷却室设置在燃烧室的下游。 将燃烧室连接到冷却室的汲取管被设置。 合成气通过汲取管从燃烧室引导到冷却室，以接触液体冷却剂并产生冷却的合成气。 非对称或对称的液体分离器设置在冷却室的出口路径附近，并且被配置为从被引导通过环形通道的冷却的合成气除去夹带的液体内容物到出口路径。

    SWOZZLE DESIGN FOR GAS TURBINE COMBUSTOR
    10.
    发明申请
    SWOZZLE DESIGN FOR GAS TURBINE COMBUSTOR 有权
    气动涡轮搅拌机的旋转设计

    公开(公告)号：US20090183511A1

    公开(公告)日：2009-07-23

    申请号：US12016799

    申请日：2008-01-18

    申请人： Constantin Dinu

    发明人： Constantin Dinu

    IPC分类号： F02C7/22 ,  F23R3/14

    CPC分类号： F23R3/286 ,  F23R3/14

    摘要： Disclosed is a fuel nozzle for a combustor of a gas turbine engine includes a nozzle inlet, a combustion area and a swirler disposed between the nozzle inlet and combustion area. The swirler includes a plurality of swirler vanes, each swirler vane capable of creating a pressure difference in fluid flow through the swirler between a pressure side and suction side of the swirler vane. The swirler further includes at least one through airflow hole located in at least one swirler vane of the plurality of swirler vanes. The at least one through airflow hole is capable of utilizing the pressure difference between the pressure side and suction side to promote fluid flow through the at least one airflow hole. Also disclosed is a method for operating a combustor.

    摘要翻译： 公开了一种燃气涡轮发动机的燃烧器的燃料喷嘴，其包括设置在喷嘴入口和燃烧区域之间的喷嘴入口，燃烧区域和旋流器。 旋流器包括多个旋流器叶片，每个旋流器叶片能够在旋流器叶片的压力侧和吸入侧之间产生通过旋流器的流体流动的压力差。 旋流器还包括位于多个旋流器叶片的至少一个旋流器叶片中的至少一个穿过气流孔。 所述至少一个通气孔能够利用所述压力侧和吸入侧之间的压差来促进流过所述至少一个气流孔的流体。 还公开了一种操作燃烧器的方法。