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公开(公告)号：US06599092B1
公开(公告)日：2003-07-29
申请号：US10039719
申请日：2002-01-04
IPC分类号： F01D906
CPC分类号： F01D5/187 , F05D2240/10 , F05D2260/22141 , Y02T50/676
摘要： A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge, forming a plurality of slots in the pressure side of the airfoil extending towards the trailing edge, and extending a plurality of pins arranged in rows between the airfoil suction and pressure sides, such that at each of a first row of pins has a substantially elliptical cross-sectional area, wherein the first row of pins is between the remaining rows of pins and the airfoil pressure side slots.
摘要翻译： 一种用于制造用于燃气涡轮发动机的喷嘴的方法有助于延长喷嘴的使用寿命。 喷嘴包括翼型件。 所述方法包括形成所述翼型件以包括吸入侧和连接在前缘和后缘处的压力侧，在所述翼型件的压力侧中形成多个狭槽，所述多个狭槽朝向所述后缘延伸，并且延伸多个销布置 在翼型吸力和压力侧之间的行中，使得在第一排销的每一个具有基本上椭圆形的横截面积，其中第一排销在剩余的销排和翼型压力侧槽之间。
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公开(公告)号：US06139257A
公开(公告)日：2000-10-31
申请号：US249205
申请日：1999-02-12
CPC分类号： F01D11/08 , F01D9/04 , F05D2260/201 , F05D2260/202
摘要： To cool the shroud assembly in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow to baffle plenums and thence through baffle perforations to impingement cool the rails and back surfaces of the shroud. Impingement cooling air then flows through elongated, convection cooling passages in the shroud sections and exits to flow along the shroud front surface with the main gas stream to provide film cooling. The aft rail of the shroud sections is provided with one or more cooling holes to impingement cool the annular retaining ring or C-clip retaining the shroud sections on the shroud hangers. This cooling air then travels aftward on the inboard side of the C-clip to provide convection cooling of the C-clip. In an alternative embodiment, cooling air is directed at the aft corners of the shroud base to avoid overheating.
摘要翻译： 为了冷却燃气轮机发动机的高压涡轮机部分中的护罩组件，将高压冷却空气以计量流量导向挡板增压室，从而通过挡板穿孔冲击以冷却护罩的轨道和后表面。 冲击冷却空气然后流过护罩部分中的细长的对流冷却通道并且离开以沿着护罩前表面与主气流一起流动以提供膜冷却。 护罩部分的后导轨设置有一个或多个冷却孔，以将保持护罩部分的环形固定环或C形夹子冷却到护罩悬挂器上。 然后，该冷却空气在C形夹的内侧向后行进，以提供C形夹的对流冷却。 在替代实施例中，冷却空气被引导到护罩底座的后角以避免过热。
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