公开(公告)号：US09670784B2

公开(公告)日：2017-06-06

申请号：US14061193

申请日：2013-10-23

Applicant: General Electric Company

Inventor： Jason Douglas Herzlinger ,  Harish Bommanakatte ,  Anthony Louis Giglio ,  Jacob Charles Perry, II

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  Y02E20/16 ,  Y02T50/672 ,  Y02T50/676

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base including: a casing having at least one exhaust aperture on an outer surface of the casing; and a core within the casing, the core having: a serpentine cooling passage; and at least one outlet passage fluidly connected with the serpentine cooling passage and the exhaust aperture, wherein the at least one outlet passage permits flow of a coolant from the serpentine cooling passage to the at least one exhaust aperture on the outer surface of the casing; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side.

公开(公告)号：US09551226B2

公开(公告)日：2017-01-24

申请号：US14061107

申请日：2013-10-23

Applicant: General Electric Company

Inventor： Paul Kendall Smith ,  Harish Bommanakatte ,  Anthony Louis Giglio ,  Jason Douglas Herzlinger ,  Jacob Charles Perry, II ,  Alexander Stein

IPC: F01D5/14

CPC classification number: F01D5/143 ,  F05D2250/711 ,  F05D2250/74 ,  Y02E20/16 ,  Y02T50/671 ,  Y02T50/673

Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using an airfoil profile and/or an endwall contour including at least one of a pressure side bump, a pressure side leading edge bump, or a suction side trough. In particular, by including two endwall bumps on the pressure side and a trough on the suction side combined with a particular airfoil profile, performance can be further improved.

Abstract translation: 可以使用包括压力侧凸块，压力侧前缘凸起或吸力侧槽中的至少一个的翼型轮廓和/或端壁轮廓来改善涡轮机频率调谐，流体动力学效率和性能。 特别地，通过在压力侧包括两个端壁凸起和在特定翼型轮廓上结合吸力侧的槽，可以进一步提高性能。

公开(公告)号：US09528379B2

公开(公告)日：2016-12-27

申请号：US14061363

申请日：2013-10-23

Applicant: General Electric Company

Inventor： Jason Douglas Herzlinger ,  Harish Bommanakatte ,  Anthony Louis Giglio ,  Jacob Charles Perry, II

IPC: F01D5/14 ,  F01D5/18 ,  B22C9/10 ,  B22C9/24

CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/103 ,  B22C9/24 ,  F01D5/147 ,  F05D2230/211 ,  F05D2250/185 ,  F05D2250/74 ,  Y02T50/673 ,  Y02T50/676

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a casing having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, the casing including an aperture on the leading edge; and a core within the casing, the core having a serpentine shape for supporting the casing and a leading edge passage fluidly connected with the aperture on the leading edge of the casing.

Abstract translation: 本发明的各种实施例包括涡轮机桶和采用这种铲斗的系统。 各种具体实施例包括涡轮机桶，其具有：基座; 以及在所述翼型件的第一端处与所述基座连接的翼型件，所述翼型件包括：壳体，其具有：吸力侧; 与吸力侧相对的压力侧; 位于压力侧和吸力侧之间的前缘; 以及与所述前缘相对并且跨越所述压力侧和所述吸力侧的后缘，所述壳体在所述前缘上包括孔; 以及壳体内的芯部，芯部具有用于支撑壳体的蛇形形状，以及与壳体前缘上的孔流体连接的前缘通路。

公开(公告)号：US20150110641A1

公开(公告)日：2015-04-23

申请号：US14061193

申请日：2013-10-23

Applicant: General Electric Company

Inventor： Jason Douglas Herzlinger ,  Harish Bommanakatte ,  Anthony Louis Giglio ,  Jacob Charles Perry, II

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  Y02E20/16 ,  Y02T50/672 ,  Y02T50/676

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base including: a casing having at least one exhaust aperture on an outer surface of the casing; and a core within the casing, the core having: a serpentine cooling passage; and at least one outlet passage fluidly connected with the serpentine cooling passage and the exhaust aperture, wherein the at least one outlet passage permits flow of a coolant from the serpentine cooling passage to the at least one exhaust aperture on the outer surface of the casing; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side

Abstract translation: 本发明的各种实施例包括涡轮机桶和采用这种铲斗的系统。 各种特定实施例包括涡轮机桶，其具有：底座，包括：壳体，其在壳体的外表面上具有至少一个排气孔; 以及壳体内的芯，所述芯具有：蛇形冷却通道; 以及与蛇形冷却通道和排气孔流体连接的至少一个出口通道，其中所述至少一个出口通道允许冷却剂从所述蛇形冷却通道流动到所述壳体的外表面上的所述至少一个排气孔; 以及在所述翼型件的第一端处与所述基座连接的翼型件，所述翼型件包括：吸力侧; 与吸力侧相对的压力侧; 位于压力侧和吸力侧之间的前缘; 以及与前缘相对并跨越压力侧和吸力侧的后缘

公开(公告)号：US20140193273A1

公开(公告)日：2014-07-10

申请号：US13737031

申请日：2013-01-09

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Harrish Bommanakatte ,  Jalindar Appa Walunj ,  Anthony Louis Giglio ,  Jason Douglas Herzlinger

IPC: F01D5/18

CPC classification number: F01D5/189 ,  F01D5/187 ,  F05D2240/303 ,  F05D2260/201 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine is provided. The interior cooling configuration may include a first flow passage and a second flow passage that have a side-by-side configuration for a segment, and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage. The crossover passages may be staggered.

Abstract translation: 提供了形成在燃气涡轮发动机的叶片的翼型内的内部冷却构造。 内部冷却构造可以包括具有用于段的并排构造的第一流动通道和第二流动通道，以及在第一流动通道和第二流动通道之间延伸并且将流体连接到第二流动通道的多个横向跨接通道。 交叉通道可能交错。

公开(公告)号：US20140154063A1

公开(公告)日：2014-06-05

申请号：US13705804

申请日：2012-12-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Xiuzhang James Zhang ,  Stephen Paul Wassynger ,  Aaron Ezekiel Smith ,  Anthony Louis Giglio

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil includes an outer surface having a leading edge, a trailing edge downstream from the leading edge, and a convex surface between the leading and trailing edges. A cavity is inside the outer surface, and a platform is connected to the outer surface and defines a top surface around at least a portion of the outer surface. A first plurality of trenches is beneath the top surface of the platform upstream from the leading edge, wherein each trench in the first plurality of trenches is in fluid communication with the cavity inside the outer surface. A first plurality of cooling passages provide fluid communication from the first plurality of trenches through the top surface of the platform.

Abstract translation: 翼型件包括具有前缘的外表面，在前缘下游的后缘以及前缘和后缘之间的凸面。 空腔在外表面内，并且平台连接到外表面并且围绕外表面的至少一部分限定顶表面。 第一多个沟槽位于平台的顶表面上方的前缘上游，其中第一多个沟槽中的每个沟槽与外表面内的空腔流体连通。 第一多个冷却通道提供从第一多个沟槽通过平台的顶表面的流体连通。