-
公开(公告)号：US09297310B2
公开(公告)日：2016-03-29
申请号：US13654818
申请日：2012-10-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sheo Narain Giri , Sanjeev Kumar Jha , Bhaskar Pemmi , Harish Bommanakatte , Santhosh Donkada , Krishna Kishore Gumpina , Indrajit Mazumder , Rajarshi Saha
CPC classification number: F01D17/10 , F01D5/08 , F01D5/082 , F01D17/105 , F01D25/08 , F01D25/12 , F01D25/14 , F02C3/04 , F02C6/08 , F02C7/12 , F02C7/141 , F02C7/18 , F02C9/18 , F04D29/522 , F04D29/582 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F05D2300/173 , F05D2300/502 , F05D2300/504 , F05D2300/505
Abstract: A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.
Abstract translation: 一种用于燃气涡轮发动机的冷却装置。 冷却装置包括用于来自压缩机的气流的排出通道，第一冷却通道和提供通过排放通道的空气流与第一冷却通道之间的连通的至少一个孔。 孔中的限流装置调节排放通道和第一冷却通道之间的空气流。 限制器装置变形以响应于发动机的物理状况改变流过孔的空气。 发动机的这种物理状态可以是流过排放通道的空气的温度，限制装置响应于基于该温度调节空气的流量。 限流装置可以是双向形状记忆合金。
-
公开(公告)号：US20140154079A1
公开(公告)日：2014-06-05
申请号：US13690361
申请日：2012-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Rohit Chouhan , Harish Bommanakatte , Sumeet Soni , Srinivasa Govardhan Jayana , Spencer Aaron Kareff
IPC: F01D5/22
CPC classification number: F01D5/225 , F01D5/143 , F05D2240/307 , F05D2250/74
Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.
Abstract translation: 提供涡轮转子叶片。 涡轮转子叶片包括翼型件，翼型件末端，尖端护罩和围绕翼型件末端和尖端护罩的相交处的圆角。 圆角定义了一个关于交点的圆角轮廓变量，作为交叉点的空气动力学气流的函数。
-
公开(公告)号：US10138736B2
公开(公告)日：2018-11-27
申请号：US14949544
申请日：2015-11-23
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Spencer Aaron Kareff
Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.
-
公开(公告)号：US20170191366A1
公开(公告)日：2017-07-06
申请号：US14988070
申请日：2016-01-05
Applicant: General Electric Company
Inventor： Spencer A. Kareff , Sheo Narain Giri , Kevin Lee Worley , Harish Bommanakatte
CPC classification number: F01D5/22 , F01D11/006 , Y02T50/671
Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define an outer surface of the elongated body. The outer surface is configured to contact with a groove defined between the adjacent turbine blades. The elongated body defines a slot that extends radially inwardly through the outer surface and axially through the elongated body.
-
公开(公告)号：US20150110640A1
公开(公告)日：2015-04-23
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
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。
-
Patent Agency Ranking
公开(公告)号：US20140271225A1
公开(公告)日：2014-09-18
申请号：US13737023
申请日：2013-01-09
Applicant: General Electric Company
Inventor： Jason Douglas Herzlinger , Bradley Taylor Boyer , Harish Bommanakatte , Anthony Louis Giglio
IPC: F01D5/18
CPC classification number: F01D5/187 , B22C9/10 , F05D2230/21 , F05D2250/232 , Y02T50/676 , Y10T29/49341
Abstract: A rotor blade comprising an airfoil portion and a root portion, and an internal cooling circuit having flow passages in the root portion and the airfoil portion, wherein the internal cooling circuit includes: a first flow passage; and a non-integral plug. The plug may include a plug channel configured to correspond to a desired level of coolant flow through the first cooling passage. The plug may be connected to the rotor blade in a fixed blocking position relative to the first flow passage.
Abstract translation: 一种包括翼型部分和根部的转子叶片，以及具有根部和翼型部分中的流动通道的内部冷却回路，其中内部冷却回路包括：第一流动通道; 和非整体插头。 塞子可以包括被配置为对应于通过第一冷却通道的期望水平的冷却剂流动的塞通道。 塞子可以相对于第一流动通道以固定的阻塞位置连接到转子叶片。
-
公开(公告)号：US10253638B2
公开(公告)日：2019-04-09
申请号：US14824953
申请日：2015-08-12
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Paul Kendall Smith , Srinivasa Govardhan Jayana , Sylvain Pierre , Harish Bommanakatte , Santhosh Kumar Vijayan , Spencer Aaron Kareff
Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.
-
公开(公告)号：US09765630B2
公开(公告)日：2017-09-19
申请号：US13737023
申请日：2013-01-09
Applicant: General Electric Company
Inventor： Jason Douglas Herzlinger , Bradley Taylor Boyer , Harish Bommanakatte , Anthony Louis Giglio
CPC classification number: F01D5/187 , B22C9/10 , F05D2230/21 , F05D2250/232 , Y02T50/676 , Y10T29/49341
Abstract: A rotor blade including an airfoil portion and a root portion, and an internal cooling circuit having flow passages in the root portion and the airfoil portion, wherein the internal cooling circuit includes: a first flow passage; and a non-integral plug. The plug may include a plug channel configured to correspond to a desired level of coolant flow through the first cooling passage. The plug may be connected to the rotor blade in a fixed blocking position relative to the first flow passage.
-
公开(公告)号：US09376922B2
公开(公告)日：2016-06-28
申请号：US13737031
申请日：2013-01-09
Applicant: General Electric Company
Inventor： Harish Bommanakatte , Jalindar Appa Walunj , Anthony Louis Giglio , Jason Douglas Herzlinger
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：US20150107265A1
公开(公告)日：2015-04-23
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 , 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。
-
-
-
-
-
-
-
-
-
Search Results
21
records
(took 0.016 seconds)
