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    • 1. 发明授权
    • Method and system for designing an impingement film floatwall panel system
    • 冲击膜浮法面板系统设计方法及系统
    • US06973419B1
    • 2005-12-06
    • US09517567
    • 2000-03-02
    • Thomas B. FortinGregory E. ChettaDavid W. LeungDuncan C. MeyersKeith C. BelsonJohn V. DiazThomas E. HolladayScott A. LaddRandall G. McKinneySergio RinellaAndreas SadilGeorge F. Titterton, III
    • Thomas B. FortinGregory E. ChettaDavid W. LeungDuncan C. MeyersKeith C. BelsonJohn V. DiazThomas E. HolladayScott A. LaddRandall G. McKinneySergio RinellaAndreas SadilGeorge F. Titterton, III
    • F23R3/00G06G7/48
    • F23R3/002F23R2900/00018F23R2900/03044Y02T50/675Y10T477/40
    • A method and system for designing an impingement film floatwall panel system for a combustion chamber for a gas turbine engine comprising the steps of creating an impingement film floatwall panel knowledge base of information. The knowledge base has a plurality of design rule signals with respect to a corresponding plurality of parameter signals of associated elements of impingement film floatwall panels for a combustion chamber, wherein the knowledge base comprises at least one data value signal for each one of the plurality of design rule signals. The steps also include entering a desired data value signal for a selected one of the plurality of parameter signals of an associated element of the impingement film floatwall panels and comparing the entered desired data value signal for the selected one of the plurality of parameters with the corresponding at least one data value signal in the knowledge base for the corresponding one of the plurality of design rule signals. If the result of the step of comparing is such that the entered desired data value signal for the selected one of the plurality of parameter signals is determined to have a first predetermined relationship with respect to the corresponding at least one data value signal in the knowledge base for the selected one of the plurality of design rule signals, create signals representative of a geometric representation of the selected one of the plurality of parameter signals of the associated element of the impingement film floatwall panels.
    • 一种用于设计用于燃气涡轮发动机的燃烧室的冲击膜浮动面板系统的方法和系统,包括以下步骤:创建冲击膜浮体墙板信息的知识库。 知识库相对于燃烧室的冲击膜浮动面板的相关元件的相应多个参数信号具有多个设计规则信号,其中知识库包括至少一个数据值信号,用于多个 设计规则信号。 这些步骤还包括为冲击薄膜浮动面板的相关元件的多个参数信号中选定的一个参数信号输入期望的数据值信号,并将输入的多个参数中所选择的一个参数的期望数据值信号与相应的 所述知识库中的所述多个设计规则信号中的相应一个的至少一个数据值信号。 如果比较步骤的结果是使得所输入的多个参数信号中所选择的一个参数信号的期望数据值信号被确定为相对于知识库中相应的至少一个数据值信号具有第一预定关系 对于所选择的多个设计规则信号中的一个,创建表示冲击膜浮体面板的相关元件的多个参数信号中所选择的一个的几何表示的信号。
    • 3. 发明授权
    • Turbine exhaust case duct
    • 涡轮排气箱管道
    • US08985942B2
    • 2015-03-24
    • US13539610
    • 2012-07-02
    • William A. DanielsJohn J. KorzendorferDavid A. DebyahScott A. Ladd
    • William A. DanielsJohn J. KorzendorferDavid A. DebyahScott A. Ladd
    • F01D25/24
    • F01D25/24Y02T50/671
    • An exhaust duct comprises a shroud body, a forward flange assembly, an aft flange assembly, an intermediate flange assembly, and a first plurality of bleed ports. The forward flange assembly extends radially inward from a forward shroud end for securing the forward shroud end downstream of a final turbine stage. The aft flange assembly extends circumferentially around and radially inward from an aft shroud end for securing the aft shroud end to an engine tail cone. The intermediate flange assembly is disposed forward of the aft flange assembly, and extends circumferentially around and radially inward from the shroud body for securing the shroud body to an engine bearing housing. The first plurality of bleed ports is disposed around the shroud body forward of a junction with the intermediate flange.
    • 排气管道包括护罩主体,前凸缘组件,后凸缘组件,中间凸缘组件和第一多个排气口。 前法兰组件从前护罩端径向向内延伸,以将前护罩端固定在最终涡轮级的下游。 后翼缘组件从后护罩端部周向地周向地径向向内延伸,以将后护罩端固定到发动机尾锥。 中间凸缘组件设置在后凸缘组件的前方,并且从罩主体周向地周向地和径向向内延伸,以将罩体固定到发动机轴承壳体上。 第一多个排出口设置在与中间凸缘的接合部的前方的护罩本体的周围。
    • 6. 发明申请
    • TURBINE EXHAUST CASE DUCT
    • 涡轮排气箱
    • US20140003922A1
    • 2014-01-02
    • US13539610
    • 2012-07-02
    • William A. DanielsJohn J. KorzendorferDavid A. DebyahScott A. Ladd
    • William A. DanielsJohn J. KorzendorferDavid A. DebyahScott A. Ladd
    • F01D25/24
    • F01D25/24Y02T50/671
    • An exhaust duct comprises a shroud body, a forward flange assembly, an aft flange assembly, an intermediate flange assembly, and a first plurality of bleed ports. The forward flange assembly extends radially inward from a forward shroud end for securing the forward shroud end downstream of a final turbine stage. The aft flange assembly extends circumferentially around and radially inward from an aft shroud end for securing the aft shroud end to an engine tail cone. The intermediate flange assembly is disposed forward of the aft flange assembly, and extends circumferentially around and radially inward from the shroud body for securing the shroud body to an engine bearing housing. The first plurality of bleed ports is disposed around the shroud body forward of a junction with the intermediate flange.
    • 排气管道包括护罩主体,前凸缘组件,后凸缘组件,中间凸缘组件和第一多个排气口。 前法兰组件从前护罩端径向向内延伸,以将前护罩端固定在最终涡轮级的下游。 后翼缘组件从后护罩端部周向地周向地径向向内延伸,以将后护罩端固定到发动机尾锥。 中间凸缘组件设置在后凸缘组件的前方,并且从罩主体周向地周向地和径向向内延伸,以将罩体固定到发动机轴承壳体上。 第一多个排出口设置在与中间凸缘的接合部的前方的护罩本体的周围。