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    • 42. 发明申请
    • GAS TURBINE
    • 燃气轮机
    • US20110293402A1
    • 2011-12-01
    • US13116523
    • 2011-05-26
    • Erich KreiselmaierChiara ZambettiThomas Wilhelm
    • Erich KreiselmaierChiara ZambettiThomas Wilhelm
    • F04D31/00
    • F01D11/10F01D5/225F01D25/12F05D2260/2212F05D2260/22141
    • A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.
    • 一种燃气轮机,包括具有带护罩和翅片的可旋转刀片的内壳和转子,以及布置在壳体中的空腔中并围绕可旋转叶片的冷却装置。 叶片护罩包括从叶片前缘延伸到空腔中的突起和用于冷却流体的空腔壁中的开口。 突起由相对于流动通道壁的角度限定。 突起影响通过开口进入的冷却流体的涡流和从流动通道进入空腔的热气体的涡流。 双涡流形成减少了冷却流与热气流的混合,并提高了叶片罩和空腔壁的冷却布置的效率。
    • 43. 发明申请
    • BLADE FOR A GAS TURBINE
    • 燃气轮机叶片
    • US20110223036A1
    • 2011-09-15
    • US13071219
    • 2011-03-24
    • Thomas WilhelmCaroline MarchmontSergei Riazantsev
    • Thomas WilhelmCaroline MarchmontSergei Riazantsev
    • F01D5/18
    • F01D5/187F01D5/225
    • The blade for a gas turbine includes a blade airfoil having a leading edge and a trailing edge and extending in the blade longitudinal direction up to a blade tip, and at the blade tip the blade airfoil merges into a shroud segment, wherein on the shroud segment a first rib, projecting upwards, is arranged in the flow direction, extending transversely to the flow direction, and upstream of the first rib, in the region of the leading edge of the blade airfoil, a winglet is formed on the shroud segment for guiding of the hot gas flow in this region. With such a blade, a longer service life is achieved by provision being made for direct cooling of the winglet.
    • 用于燃气涡轮的叶片包括具有前缘和后缘并且在叶片纵向方向上延伸直到叶片尖端的叶片翼型件,并且在叶片尖端处,叶片翼型件合并成护罩段,其中在护罩段 向上突出的第一肋沿流动方向布置,横向于流动方向延伸,并且在第一肋的上游处在叶片翼型的前缘的区域中,在护罩段上形成小翼以用于引导 的热气流在这个地区。 利用这种叶片,通过提供用于小翼的直接冷却来实现更长的使用寿命。