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公开(公告)号：US07625178B2
公开(公告)日：2009-12-01
申请号：US11513759
申请日：2006-08-30
申请人： Mark C. Morris , George W. Wolfmeyer , Luis A. Tapia , Vivek Agarwal , Kin Poon , Jason C. Smoke , William C. Baker , Henry M. Armstrong
发明人： Mark C. Morris , George W. Wolfmeyer , Luis A. Tapia , Vivek Agarwal , Kin Poon , Jason C. Smoke , William C. Baker , Henry M. Armstrong
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , B22C7/02 , B22C9/04 , B22C9/10 , F05D2230/211 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341
摘要： An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.
摘要翻译： 本发明提供一种风冷式涡轮机叶片，其具有由凸形的吸入侧壁，凹入压力侧壁，前缘，后缘，根部和尖端形成的翼面形状，所述壁和端部各自包括内表面 其限定具有根部的内部，所述后缘包括形成在其上的多个狭槽。 叶片包括形成在其中的吸入侧流动回路，包括前进和后部流动回路。 叶片还包括尖端流动回路，其沿着尖端内表面延伸到至少一个后缘槽，并且包括第一和第二开口，第一开口与吸力侧向前流动回路出口流动连通， 打开与吸入侧后流道的交叉孔流动连通。 还提供了制造叶片的方法。
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公开(公告)号：US20080056908A1
公开(公告)日：2008-03-06
申请号：US11513759
申请日：2006-08-30
申请人： Mark C. Morris , George W. Wolfmeyer , Luis A. Tapia , Vivek Agarwal , Kin Poon , Jason C. Smoke , William C. Baker , Henry M. Armstrong
发明人： Mark C. Morris , George W. Wolfmeyer , Luis A. Tapia , Vivek Agarwal , Kin Poon , Jason C. Smoke , William C. Baker , Henry M. Armstrong
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , B22C7/02 , B22C9/04 , B22C9/10 , F05D2230/211 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341
摘要： An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.
摘要翻译： 本发明提供一种风冷式涡轮机叶片，其具有由凸形的吸入侧壁，凹入压力侧壁，前缘，后缘，根部和尖端形成的翼面形状，所述壁和端部各自包括内表面 其限定具有根部的内部，所述后缘包括形成在其上的多个狭槽。 叶片包括形成在其中的吸入侧流动回路，包括前进和后部流动回路。 叶片还包括尖端流动回路，其沿着尖端内表面延伸到至少一个后缘槽，并且包括第一和第二开口，第一开口与吸力侧向前流动回路出口流动连通， 打开与吸入侧后流道的交叉孔流动连通。 还提供了制造叶片的方法。
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公开(公告)号：US07540083B2
公开(公告)日：2009-06-02
申请号：US11238528
申请日：2005-09-28
IPC分类号： B21K3/04
CPC分类号： F01D5/147 , F01D5/187 , F05D2230/10 , F05D2230/23 , F05D2260/221 , Y02T50/676 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341 , Y10T29/49343 , Y10T29/49771
摘要： Methods are provided for modifying an airfoil internal cooling circuit that include a flow path configured to direct air through the airfoil in a direction and the airfoil having a leading edge, a trailing edge, and a first and a second wall therebetween, each wall having an inner and an outer surface, the inner surfaces defining a cavity and having features forming at least a portion of the internal cooling circuit. The methods may include the steps of forming a pilot hole through the airfoil first and second walls at a predetermined location, forming an insert hole based on the predetermined location, the insert hole enveloping the pilot hole and configured to receive at least a portion of an insert configured to modify the internal cooling circuit flow path, placing the insert into the insert hole, and bonding the insert to the airfoil first and second walls.
摘要翻译： 提供了用于修改翼型件内部冷却回路的方法，所述翼型件内部冷却回路包括被构造成沿着一个方向引导空气通过翼型的流动路径，并且所述翼型件具有前缘，后缘以及其间的第一和第二壁，每个壁具有 内表面和外表面，内表面限定空腔并且具有形成内部冷却回路的至少一部分的特征。 所述方法可以包括以下步骤：在预定位置处通过翼型件形成导向孔，形成基于预定位置的插入孔，所述插入孔包围导向孔并且构造成容纳至少一部分 插入件被配置为修改内部冷却回路流动路径，将插入件放入插入孔中，并将插入件接合到翼型件第一和第二壁。
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公开(公告)号：US20080164001A1
公开(公告)日：2008-07-10
申请号：US11650265
申请日：2007-01-05
摘要： A core assembly including two cores is used to manufacture a blade. The first core has an outer surface shaped to complement the tip wall bottom surface. The second core has a tip surface, a side surface, and a protrusion or a depression. The tip surface is shaped to complement at least a portion of the tip wall top surface and is configured to be disposed proximate the first core. The side surface is shaped to complement at least a portion of the side wall, and the protrusion extends from the second core side surface to contact at least a portion of the ceramic mold inner surface. In embodiments employing a depression, the depression is formed in the side surface.
摘要翻译： 使用包括两个芯的芯组件来制造刀片。 第一芯具有成形为补充尖端壁底面的外表面。 第二芯具有尖端表面，侧表面和突起或凹陷。 尖端表面被成形为补充尖端壁顶表面的至少一部分并且被构造成邻近第一芯配置。 侧表面成形为补充侧壁的至少一部分，并且突起从第二芯侧表面延伸以接触陶瓷模具内表面的至少一部分。 在使用凹陷的实施例中，凹陷形成在侧表面中。
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公开(公告)号：US07610946B2
公开(公告)日：2009-11-03
申请号：US11650265
申请日：2007-01-05
摘要： A core assembly including two cores is used to manufacture a blade. The first core has an outer surface shaped to complement the tip wall bottom surface. The second core has a tip surface, a side surface, and a protrusion or a depression. The tip surface is shaped to complement at least a portion of the tip wall top surface and is configured to be disposed proximate the first core. The side surface is shaped to complement at least a portion of the side wall, and the protrusion extends from the second core side surface to contact at least a portion of the ceramic mold inner surface. In embodiments employing a depression, the depression is formed in the side surface.
摘要翻译： 使用包括两个芯的芯组件来制造刀片。 第一芯具有成形为补充尖端壁底面的外表面。 第二芯具有尖端表面，侧表面和突起或凹陷。 尖端表面被成形为补充尖端壁顶表面的至少一部分并且被构造成邻近第一芯配置。 侧表面成形为补充侧壁的至少一部分，并且突起从第二芯侧表面延伸以接触陶瓷模具内表面的至少一部分。 在使用凹陷的实施例中，凹陷形成在侧表面中。
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公开(公告)号：US06968697B2
公开(公告)日：2005-11-29
申请号：US10666611
申请日：2003-09-17
申请人： Ly D. Nguyen , Cristopher Frost , Ronald P. Maty , John M. Wait , Jason C. Smoke , Lori M. Wheeler , Richard D. Kocher
发明人： Ly D. Nguyen , Cristopher Frost , Ronald P. Maty , John M. Wait , Jason C. Smoke , Lori M. Wheeler , Richard D. Kocher
CPC分类号： F02C7/20 , F02C7/06 , F04D29/4206 , F05D2230/52 , Y02T50/672
摘要： A turbine engine compressor design utilizing multiple component integration, thereby reducing the number of required engine components. In conventional compressor designs, a multiple component system makes it difficult to predict the structural behaviors due to thermal and mechanical loading during transient conditions. The compressor design of the present invention has three main parts: a forward bearing housing, a bell-mouth (heat shield) and a coupled impeller shroud/diffuser. Such a design achieves the design objectives of the present invention, including reducing weight, reducing cost, minimizing tolerance build up and improving aerodynamic performance by utilizing multiple component integration for multiple modes of engine operation.
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公开(公告)号：US07097411B2
公开(公告)日：2006-08-29
申请号：US10829114
申请日：2004-04-20
CPC分类号： F04D29/444 , F01D9/026 , F04D29/624 , F05D2220/40 , F05D2250/52
摘要： A compressor scroll housing for use in conjunction with turbo-machinery, particularly applicable in aircraft. The scroll housing can include a plurality of scroll vanes arrayed around the scroll housing. Scroll vanes, integrally formed with the scroll housing, carry stress load on the scroll housing, including the load from fluid pressure within the scroll and carcass loading from the engine. The plurality of scroll vanes adapted for guiding flow of fluid from an inlet to an outlet while supporting the scroll housing. Chord length and cross sectional area of each scroll vane can be sized to maintain an equal stress in all scroll vanes. A method of making the scroll housing for use with an impeller connected to an engine is disclosed, as well as a method of operating turbo-machinery including supporting a load on the scroll housing with scroll vanes while maintaining an equal stress on each scroll vane.
摘要翻译： 一种与涡轮机械结合使用的压缩机涡旋壳体，特别适用于飞机。 涡旋壳体可以包括围绕涡旋壳体排列的多个涡旋叶片。 与涡旋壳体一体形成的涡旋叶片在涡旋壳体上承受应力负荷，包括来自涡卷内的流体压力的负载和来自发动机的胎体负载。 多个涡旋叶片适于在支撑涡旋壳体的同时引导流体从入口到出口的流动。 每个涡旋叶片的弦长和横截面面积的尺寸可以确保在所有涡旋叶片中保持相等的应力。 公开了一种制造与连接到发动机的叶轮一起使用的涡旋壳体的方法，以及一种操作涡轮机械的方法，包括在涡轮叶片上支撑负载，同时在每个涡旋叶片上保持相等的应力。
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