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1.发明授权Turbine nozzle and related casting method for optimal fillet wall thickness control 失效涡轮喷嘴和相关铸造方法，用于最佳的圆角壁厚控制
公开(公告)号：US5662160A
公开(公告)日：1997-09-02
申请号：US542001
申请日：1995-10-12
摘要： In a method of investment casting a turbine nozzle which includes an outer band, an inner band and an airfoil section extending between the inner and outer bands, an improvement including shaping a temporary wax form, and external shell and internal core components used in casting such that during pouring of molten metal into a space created by removal of the wax form, shell material lies on opposite sides of an outer fillet connecting the outer band to the airfoil section. The resulting gas turbine nozzle includes first and second horizontally oriented ribs extending about interior peripheries of the airfoil section vertically adjacent the outer and inner band fillets.
摘要翻译： 在一种熔模铸造方法中，包括外带，内带和在内带和外带之间延伸的翼型部分的涡轮喷嘴，包括成型临时蜡形的改进，以及用于铸造的外壳和内芯部件 在将熔融金属浇注到通过除去蜡形而产生的空间中时，外壳材料位于将外带连接到翼型部的外圆角的相对侧上。 所得到的燃气涡轮喷嘴包括第一和第二水平定向的肋，所述第一和第二水平定向的肋沿着与外带和内带鱼片垂直相邻的翼型部分的内周延伸。
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2.发明授权Turbine nozzle and related casting method for optimal fillet wall thickness control 失效涡轮喷嘴和相关铸造方法，用于最佳的圆角壁厚控制
公开(公告)号：US5713722A
公开(公告)日：1998-02-03
申请号：US667157
申请日：1996-06-20
摘要： In a method of investment casting a turbine nozzle which includes an outer band, an inner band and an airfoil section extending between the inner and outer bands, an improvement including shaping a temporary wax form, and external shell and internal core components used in casting such that during pouring of molten metal into a space created by removal of the wax form, shell material lies on opposite sides of an outer fillet connecting the outer band to the airfoil section. The resulting gas turbine nozzle includes first and second horizontally oriented ribs extending about interior peripheries of the airfoil section vertically adjacent the outer and inner band fillets.
摘要翻译： 在一种熔模铸造方法中，包括外带，内带和在内带和外带之间延伸的翼型部分的涡轮喷嘴，包括成型临时蜡形的改进，以及用于铸造的外壳和内芯部件 在将熔融金属浇注到通过除去蜡形而产生的空间中时，外壳材料位于将外带连接到翼型部的外圆角的相对侧上。 所得到的燃气涡轮喷嘴包括第一和第二水平定向的肋，所述第一和第二水平定向的肋沿着与外带和内带鱼片垂直相邻的翼型部的内周延伸。
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3.发明授权Impingement cooling and cooling medium retrieval system for turbine shrouds and methods of operation 失效用于涡轮罩的冲击冷却和冷却介质回收系统及其操作方法
公开(公告)号：US5391052A
公开(公告)日：1995-02-21
申请号：US152363
申请日：1993-11-16
CPC分类号： F01D11/10 , F01D11/24 , F05D2260/201 , F05D2260/2322
摘要： The steam impingement cooling and retrieval system for turbine shrouds includes a plurality of circumferentially spaced housings about a turbine shroud, each housing being divided by an impingement plate defining first and second chambers on opposite sides of the housing. Steam supplied into a first chamber passes through a plurality of apertures formed in the impingement plate into the second chamber for impingement cooling of the shroud surface forming the opposite wall of the housing. Post-impingement steam passes from the compartment into a manifold for flow through and exhaust passage. In one form, a plurality of compartments are formed in the impingement plate. A first set of the plurality of compartments include through apertures for delivering steam from the first chamber into the second chamber. The second set of compartments communicates only with the second chamber and an exhaust passage whereby post-impingement steam passes from the second chamber through apertures of the impingement plate into the second set of compartments for flow to a manifold at the end wall of the housing for delivery to the exhaust passage.
摘要翻译： 用于涡轮机护罩的蒸汽冲击冷却和回收系统包括围绕涡轮机护罩的多个周向间隔开的壳体，每个壳体由限定在壳体的相对侧上的第一和第二腔室的冲击板分隔。 供应到第一室的蒸汽穿过形成在冲击板中的多个孔进入第二室，用于冲击冷却形成壳体的相对壁的护罩表面。 后冲击蒸汽从隔室进入歧管以流过和排出通道。 在一种形式中，在冲击板中形成多个隔室。 多个隔室的第一组包括用于将蒸汽从第一室输送到第二室中的通孔。 第二组隔间仅与第二腔室和排气通道连通，由此后冲击蒸汽从第二腔室通过冲击板的孔通入第二组隔室，以流动到壳体的端壁处的歧管 输送到排气通道。
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公开(公告)号：US5509669A
公开(公告)日：1996-04-23
申请号：US491757
申请日：1995-06-19
申请人： Christopher E. Wolfe , Osman S. Dinc , Bharat S. Bagepalli , Victor H. Correia , Mahmut F. Aksit
发明人： Christopher E. Wolfe , Osman S. Dinc , Bharat S. Bagepalli , Victor H. Correia , Mahmut F. Aksit
CPC分类号： F01D11/005 , F02K1/805 , F16J15/122
摘要： A gas-path leakage seal for generally sealing a gas-path leakage-gap between spaced-apart first and second members of a gas turbine (such as combustor casing segments). The seal includes a generally imperforate foil-layer assemblage which is generally impervious to gas and is located in the leakage-gap. The seal also includes a cloth-layer assemblage generally enclosingly contacting the foil-layer assemblage. In one seal, the first edge of the foil-layer assemblage is left exposed, and the foil-layer assemblage resiliently contacts the first member near the first edge to reduce leakage in the "plane" of the cloth-layer assemblage under conditions which include differential thermal growth of the two members. In another seal, such leakage is reduced by having a first weld-bead which permeates the cloth-layer assemblage, is attached to the metal-foil-layer assemblage near the first edge, and unattachedly contacts the first member.
摘要翻译： 一种用于大致密封燃气轮机间隔开的第一和第二构件之间的气体路径泄漏间隙的气体通道泄漏密封件（例如燃烧器壳体段）。 密封件包括通常无孔的箔层组合件，其通常不透气体并且位于泄漏间隙中。 密封件还包括通常围绕箔层组合接触的布层组合件。 在一个密封件中，箔层组合件的第一边缘被暴露，并且箔层组合件弹性地接触第一边缘附近的第一构件，以减少布层组件的“平面”中的泄漏，条件包括 两个成员的差热发展。 在另一个密封件中，通过具有渗透布层组合件的第一焊道，附着到第一边缘附近的金属箔层组件，并且不附着地接触第一构件，这种泄漏被减小。
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公开(公告)号：US06733229B2
公开(公告)日：2004-05-11
申请号：US10092572
申请日：2002-03-08
IPC分类号： F01D906
CPC分类号： F01D5/189 , F01D9/065 , F05D2260/201
摘要： The invention comprises a metering plate which is assembled to an impingement insert for use in the nozzle of a gas turbine. The metering plate can have one or more metering holes and is used to balance the cooling flow within the nozzle. A metering plate with multiple holes reduces static pressure variations which result from the cooling airflow through the metering plate. The metering plate can be assembled to the insert before or after the insert is inserted into the nozzle.
摘要翻译： 本发明包括计量板，其被组装到用于燃气轮机的喷嘴中的冲击插入件。 计量板可以具有一个或多个计量孔，并用于平衡喷嘴内的冷却流。 具有多个孔的计量板减少了由通过计量板的冷却气流引起的静压变化。 在将插入件插入喷嘴之前或之后，计量盘可以组装到插入件上。
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