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    • 9. 发明授权
    • Convectively cooled liner for a combustor
    • 用于燃烧器的对流冷却衬套
    • US5737922A
    • 1998-04-14
    • US380777
    • 1995-01-30
    • Leonard SchoenmanJerrold E. Franklin
    • Leonard SchoenmanJerrold E. Franklin
    • F23R3/00F02C7/12
    • F23R3/002F23R3/005F05B2260/202Y02T50/67Y02T50/675Y10S165/908
    • A combustor liner (2) for convectively cooling a combustor chamber (16) in a gas turbine (4) comprises a chamber wall (30) with an array of coolant channels (60) formed therein. Supply manifolds (50) are coupled to the coolant channel inlets for directing bypass air through the channels, where the bypass air removes heat from the chamber wall, and discharge manifolds (52) are coupled to the coolant channel outlets for discharging the heated bypass air to the turbine (10). The coolant channels are spaced and distributed throughout the combustor liner so that the coolant flows through a substantial portion of the liner. The coolant channels are minute channels with relatively short flow paths to minimize both the pressure drop and the quantity of bypass air required to cool the wall. In addition, the channels are completely enclosed within the chamber wall to significantly improve the heat transfer characteristics of the combustor liner. Because the chamber wall is cooled convectively, without bleeding air directly into the combustion chamber, the combustor liner is particularly suited for fuel-rich combustors, such as the first stage of a two stage low NOx combustor.
    • 用于对流地冷却燃气轮机(4)中的燃烧室(16)的燃烧器衬套(2)包括具有形成在其中的冷却剂通道(60)阵列的室壁(30)。 供应歧管(50)联接到冷却剂通道入口,用于引导旁路空气通过通道,其中旁路空气从室壁移除热量,并且排出歧管(52)联接到冷却剂通道出口,用于排出加热的旁路空气 到涡轮(10)。 冷却剂通道间隔开并分布在整个燃烧器衬套中,使得冷却剂流过衬套的大部分。 冷却剂通道是具有相对较短流动路径的微通道,以最小化冷却壁所需的压降和旁路空气量。 此外,通道被完全封闭在室壁内,以显着提高燃烧器衬套的传热特性。 由于腔壁对流冷却,不会直接将空气直接排入燃烧室,所以燃烧器衬套特别适用于富燃料燃烧器,例如两级低NOx燃烧器的第一级。