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    • 1. 发明申请
    • Gas turbine combustion chambers
    • 燃气轮机燃烧室
    • US20020189260A1
    • 2002-12-19
    • US10173259
    • 2002-06-18
    • SNECMA MOTEURS
    • Etienne DavidJean-Michel DuretDidier HernandezDenis SandelisAlain Wloczysiak
    • F23R003/42
    • F23R3/045Y02T50/675
    • A combustion chamber for a gas turbine made up of outer and inner side walls, the combustion chamber being received in a casing so as to define an annular space between the combustion chamber and the casing in which there flows air for combustion, for dilution, and for cooling the combustion chamber, the side walls of the combustion chamber being pierced by a plurality of holes in which bushings of substantially elliptical right section are fixed to define air injection passages for injecting air into the combustion chamber, each bushing having a peripheral wall in which at least one additional orifice is formed opening out into the combustion chamber in the immediate vicinity of the side wall of the combustion chamber in which said bushing is fixed so that the air passing through said orifice flows substantially along said peripheral wall, the peripheral wall of each bushing having at least one groove opening out into the annular space and into which the or each orifice opens out so as to be fed with air and so as to cool the peripheral wall of the bushing.
    • 一种用于由外侧壁和内侧壁组成的燃气轮机的燃烧室,所述燃烧室被容纳在壳体中,以便在所述燃烧室和所述壳体之间形成环形空间,在所述燃烧室和所述壳体之间流动用于燃烧的空气用于稀释, 为了冷却燃烧室,燃烧室的侧壁被多个孔刺穿,其中基本上椭圆形的右部分的衬套被固定以限定用于将空气喷射到燃烧室中的空气注入通道,每个衬套具有周壁 其中至少一个另外的孔形成在燃烧室的紧邻燃烧室的侧壁附近,其中所述衬套固定在其中,使得通过所述孔的空气基本上沿着所述周壁流动,周壁 每个衬套具有至少一个开口进入环形空间的槽,并且每个孔或每个孔打开一个 以供给空气并且冷却套管的周壁。