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    • 8. 发明申请
    • Performance and durability improvement in compressor structure design
    • 压缩机结构设计的性能和耐久性改进
    • US20050158173A1
    • 2005-07-21
    • US10759928
    • 2004-01-15
    • Ly NguyenLori WheelerGreg OckenfelsDarrell JamesGeorge Zurmehly
    • Ly NguyenLori WheelerGreg OckenfelsDarrell JamesGeorge Zurmehly
    • F02C7/04F03B1/00F04D29/42F04D29/44F04D29/68
    • F02C7/04F04D29/4206F04D29/444F04D29/681F05D2220/50Y10T29/49236
    • An integral assembly that may improve control over thermal and mechanical behaviors of assembly structures during various transient operation conditions is disclosed. The integral assembly comprises a continuous ring disposed coaxial with, and orthogonal to a central axis, the continuous ring comprising a plurality of surfaces, the plurality of surfaces having a continuous outer surface and a continuous inner surface; the plurality of surfaces being characterized by a continuous cross section having a first cross sectional dimension longitudinally disposed parallel to the central axis; the plurality of surfaces comprising a bell mouth surface in physical communication with a compressor shroud surface; the compressor shroud surface being in physical communication with a diffuser surface; and the diffuser surface being in physical communication with the bell mouth surface. The integral assembly comprising a compressor shroud is also provided. An auxiliary power unit including the integral assembly, and a method of making the integral assembly are also disclosed.
    • 公开了一种整体组件,其可以在各种瞬态操作条件期间改善对组装结构的热和机械特性的控制。 整体组件包括与中心轴同轴并且与中心轴正交的连续环,连续环包括多个表面,多个表面具有连续的外表面和连续的内表面; 所述多个表面的特征在于具有平行于所述中心轴线纵向设置的第一横截面尺寸的连续横截面; 所述多个表面包括与压缩机护罩表面物理连通的喇叭口表面; 压缩机护罩表面与扩散器表面物理连通; 并且扩散器表面与喇叭口表面物理连通。 还提供了包括压缩机护罩的整体组件。 还公开了包括整体组件的辅助动力单元以及制造整体组件的方法。
    • 9. 发明申请
    • Thermally stabilized turbine scroll retention ring for uniform loading application
    • 用于均匀加载应用的热稳定型涡轮涡旋保持环
    • US20050100441A1
    • 2005-05-12
    • US10712434
    • 2003-11-12
    • Ly NguyenJames HadderGregory WoodcockStony Kujala
    • Ly NguyenJames HadderGregory WoodcockStony Kujala
    • F01D9/02F01D9/04F01D1/02
    • F01D9/026F01D9/045F05D2230/642
    • A turbine scroll retention ring may comprise a retainer ring, a plurality of ring fingers, and a plurality of ring joggles. The turbine scroll retention ring may surround and be attached to a radial nozzle. The ring joggles may allow for thermal growth variations between the radial nozzle and the turbine scroll retention ring. The radially outer end portions of the ring fingers may be in contact with a turbine scroll component (for example, an aft scroll ring), such that the turbine scroll retention ring may force contact between the turbine scroll component and the radial nozzle. The finger joggles of the ring fingers may allow for thermal growth variations between the radial nozzle and the turbine scroll component. The turbine scroll retention ring may provide constant axial loading to the aft scroll ring during all engine operating conditions.
    • 涡轮机涡旋保持环可以包括保持环,多个无名指和多个环形滑轨。 涡轮机涡旋保持环可围绕并附接到径向喷嘴。 环形滑轨可以允许径向喷嘴和涡轮涡旋保持环之间的热生长变化。 环形指状物的径向外端部分可以与涡轮机涡旋部件(例如,后涡旋环)接触,使得涡轮涡旋保持环可以迫使涡轮机涡旋部件和径向喷嘴之间的接触。 环形指状物的手指可以允许径向喷嘴和涡轮机涡旋部件之间的热生长变化。 涡轮机涡旋保持环可以在所有发动机操作条件期间为后涡旋环提供恒定的轴向负载。
    • 10. 发明申请
    • Multi-action on multi-surface seal with turbine scroll retention method in gas turbine engine
    • 多功能多功能涡轮发动机涡轮涡轮保持法多表面密封
    • US20050076643A1
    • 2005-04-14
    • US10682217
    • 2003-10-08
    • Ly NguyenGregory WoodcockStony Kujala
    • Ly NguyenGregory WoodcockStony Kujala
    • F23R3/50F23R3/52F23R3/54F23R3/60F02C7/00
    • F23R3/54F23R3/50F23R3/52F23R3/60
    • A gas turbine engine comprises a turbine scroll inside a combustor housing, discouragers with 90-degree bending angles, a radial nozzle contacting a forward bayonet on the forward side of the turbine scroll at a bayonet engagement point and a B-width measured between the discouragers. Retaining ring maintains the size of the B-width. The turbine scroll may have eight surfaces sealing at four locations and a provision to maintain constant “B-width” for the thin sheet metal scroll within the combustion system. The design allows the scroll to operate at high temperature while maintaining lowest possible thermal and mechanical stresses. It can be easily assembled with excellent capability to control gas leakage and minimal component interface wearing or fretting. The gas turbine engine is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially high performance, high cycle flight vehicles.
    • 燃气涡轮发动机包括在燃烧器壳体内的涡轮机涡旋件,具有90度弯曲角度的气门,在卡口接合点处与涡轮机涡旋体的前侧接触前方卡口的径向喷嘴和在气门机构之间测量的B宽度 。 保持环保持B宽度的大小。 涡轮机涡旋件可以在四个位置处具有八个表面密封,并且在燃烧系统内为薄板金属涡卷保持恒定的“B宽度”。 该设计允许滚动体在高温下运行,同时保持尽可能低的热和机械应力。 它可以很容易地组装,具有极好的控制气体泄漏的能力和最小的组件界面磨损或微动。 燃气涡轮发动机适用于飞机,航天器,导弹和其他飞行器,特别是高性能,高周期的飞行器。