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公开(公告)号：US20150226069A1
公开(公告)日：2015-08-13
申请号：US14418626
申请日：2013-07-30
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Steven Robert Brassfield , Stephen Mark Molter , Mark Edward Stegemiller , Nicholas Ertel , Vanessa Camarillo
CPC classification number: F01D5/185 , B23P15/04 , F01D5/147 , F01D5/187 , F05D2250/14 , Y10T29/49316 , Y10T29/49321
Abstract: A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.
Abstract translation: 涡轮机翼片包括：在前缘和后缘处连接在一起并且在根部和尖端之间延伸的凹形压力侧壁和凸形抽吸侧壁; 在所述压力侧壁和所述吸力侧壁之间延伸的内部肋; 以及形成在所述肋中的交叉孔，所述交叉孔具有非圆形横截面形状，所述横截面形状具有限定所述横截面形状的最大尺寸的长轴; 其中所述交叉孔的长轴位于与所述肋的平面中，并且不平行于限定位于所述压力和抽吸侧壁之间的中心位置的虚拟曲线横向中心线。 交叉孔的方向最小化由交叉孔的存在引起的应力集中。
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公开(公告)号：US09869185B2
公开(公告)日：2018-01-16
申请号：US14418626
申请日：2013-07-30
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Steven Robert Brassfield , Stephen Mark Molter , Mark Edward Stegemiller , Nicholas Ertel , Vanessa Camarillo
CPC classification number: F01D5/185 , B23P15/04 , F01D5/147 , F01D5/187 , F05D2250/14 , Y10T29/49316 , Y10T29/49321
Abstract: A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.
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