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    • 2. 发明申请
    • Turbine vane plate assembly
    • 涡轮叶片组件
    • US20050013686A1
    • 2005-01-20
    • US10619343
    • 2003-07-14
    • Anthony Schiavo
    • Anthony Schiavo
    • F01D5/18F01D5/14
    • F01D5/187F05D2240/12
    • A turbine vane assembly includes a turbine vane having first and second shrouds with an elongated airfoil extending between. Each end of the airfoil transitions into a shroud at a respective junction. Each of the shrouds has a plurality of cooling passages, and the airfoil has a plurality of cooling passages extending between the first and second shrouds. A substantially flat inner plate and an outer plate are coupled to each of the first and second shrouds so as to form inner and outer plenums. Each inner plenum is defined between at least the junction and the substantially flat inner plate; each outer plenum is defined between at least the substantially flat inner plate and the outer plate. Each inner plenum is in fluid communication with a respective outer plenum through at least one of the cooling passages in the respective shroud.
    • 涡轮叶片组件包括具有第一和第二护罩的涡轮叶片,其具有在其之间延伸的细长翼型件。 翼型件的每一端在相应的连接处转变成护罩。 每个护罩具有多个冷却通道,翼型件具有在第一和第二护罩之间延伸的多个冷却通道。 基本平坦的内板和外板联接到第一和第二护罩中的每一个,以便形成内部和外部增压室。 每个内部增压室至少限定在接合部和基本平坦的内板之间; 每个外部增压室至少限定在大致平坦的内板和外板之间。 每个内部增压室通过相应护罩中的至少一个冷却通道与相应的外部通气室流体连通。
    • 5. 发明申请
    • Vane shroud through-flow platform cover
    • 叶片护罩通流平台盖
    • US20070237630A1
    • 2007-10-11
    • US11401987
    • 2006-04-11
    • Anthony SchiavoBonnie Marini
    • Anthony SchiavoBonnie Marini
    • F04D29/58
    • F01D5/225F01D11/008F05D2240/80
    • A turbine vane array (10) for a combustion assembly (8) in a combustion turbine engine. The vane array (10) includes a plurality of stationary vane assemblies (12), each vane assembly (12) including at least one airfoil (24) and inner and outer shroud segments (26, 28) attached to opposing ends of the airfoil (24). The inner and outer shroud segments (26, 28) each include an inner face (34, 36) facing toward a gas path (13) extending through the vane array (10). A removable cover structure may be provided on the inner faces (34, 36) of the inner and outer shroud segments (26, 28). The cover structure may include removably attached insert elements (72, 72′) that are positioned on the inner faces (34, 36) extending between upstream edges (44) and downstream edges (46) of the shroud segments (26, 28) and extending between adjacent airfoils (24).
    • 一种用于燃气涡轮发动机中的燃烧组件(8)的涡轮叶片阵列(10)。 叶片阵列(10)包括多个静止叶片组件(12),每个叶片组件(12)包括至少一个翼型件(24)以及附接到翼型件的相对端部的内部和外侧护罩段(26,28) 24)。 内部和外部护罩段(26,28)各自包括面向延伸穿过叶片阵列(10)的气体路径(13)的内表面(34,36)。 可拆卸的盖结构可以设置在内护罩段和外护罩段(26,28)的内表面(34,36)上。 盖结构可以包括可移除地附接的插入元件(72,72'),其位于在护罩段(26,28)的上游边缘(44)和下游边缘(46)之间延伸的内表面(34,36)上,以及 在相邻翼型件(24)之间延伸。