-
公开(公告)号：US10301945B2
公开(公告)日：2019-05-28
申请号：US14974155
申请日：2015-12-18
发明人： Rohit Chouhan , Randall Richard Good , Hiteshkumar Rameshchandra Mistry , Shashwat Swami Jaiswal
摘要： A turbine rotor blade that includes: an airfoil defined between a pressure face and a suction face; a tip shroud that includes a seal rail projecting from an outboard surface and, formed thereon, a cutter tooth; and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; a cutter tooth segment is formed within the cutter tooth of the seal rail; and branching segments formed within at least one of the tip shroud and an outboard region of the airfoil. Each of the branching segments may extend between an upstream port, which connects to the cutter tooth segment, and an outlet port, which is formed on a target surface area, so that the branching segment bisects a target interior region.
-
公开(公告)号：US10774654B2
公开(公告)日：2020-09-15
申请号：US15749277
申请日：2015-07-31
摘要： A rotor blade for a turbine of a gas turbine includes an airfoil. The airfoil may have a leading edge, a trailing edge, an outboard, and an inboard end that attaches to a root configured to couple the rotor blade to a rotor disc. The airfoil may have a cooling configuration that includes elongated cooling channels for receiving and directing a coolant through the airfoil. The rotor blade may further include: a tip shroud connected to the airfoil; outlet ports formed through an outboard surface of the tip shroud that fluidly communicate with the cooling channels; and flow directing structure formed on the outboard surface of the tip shroud. The flow directing structure may be positioned relative to the outlet ports and configured for directing the flow of coolant discharged from the outlet ports. The rotor blade may be useful to reduce local tip shroud temperature as well as improved stage aerodynamic efficiency by reducing the coolant supply needed to maintain the component at desired temperature levels.
-
公开(公告)号：US10605099B2
公开(公告)日：2020-03-31
申请号：US15745165
申请日：2015-07-31
摘要： A rotor blade (16) for a turbine of a gas turbine that includes an airfoil (25). The airfoil may have a leading edge, a trailing edge, an outboard tip, and an inboard end where the airfoil attaches to a root configured to couple the turbine blade to a rotor disc. The airfoil (25) may include a tip shroud (55) at an outboard tip. The rotor blade may have a cooling configuration that includes: elongated cooling channels (33) for receiving and directing a coolant through the airfoil (25); and branching passages (75) formed through the tip shroud (55), each of which elongates between a connection with one of the cooling channels (33) and an outlet port (37) formed on a surface of the tip shroud (55). The branching passages (75) may have a canted orientation relative the outboard surface of the tip shroud (55).
-
公开(公告)号：US12083597B2
公开(公告)日：2024-09-10
申请号：US17978777
申请日：2022-11-01
发明人： James J. Murray , Shashwat Swami Jaiswal , Rajesh Kumar Venkata Gadamsetty , Hiteshkumar Rameshchandra Mistry
摘要： A gas manifold for single-nozzle deposition chambers comprising a base having a top surface and bottom surface defining a thickness; a primary nozzle having an inlet and outlet extending through the thickness of the base; and a secondary nozzle having an inlet extending partially through the top surface of the base and at least one channel extending a distance from a sidewall of the base having an outlet, the channel in fluid communication with the inlet of the secondary nozzle. The inlet of the primary nozzle has a hollow protrusion extending from the top surface of the base into the gas feed. The channel of the secondary nozzle includes a bend between the sidewall of the base and the outlet configured to pass between a first direct energy source and second direct energy source, the first energy source and second energy source disposed on a top wall of a chamber.
-
公开(公告)号：US20240139819A1
公开(公告)日：2024-05-02
申请号：US17978777
申请日：2022-11-01
发明人： James J. Murray , Shashwat Swami Jaiswal , Rajesh Kumar Venkata Gadamsetty , Hiteshkumar Rameshchandra Mistry
摘要： A gas manifold for single-nozzle deposition chambers comprising a base having a top surface and bottom surface defining a thickness; a primary nozzle having an inlet and outlet extending through the thickness of the base; and a secondary nozzle having an inlet extending partially through the top surface of the base and at least one channel extending a distance from a sidewall of the base having an outlet, the channel in fluid communication with the inlet of the secondary nozzle. The inlet of the primary nozzle has a hollow protrusion extending from the top surface of the base into the gas feed. The channel of the secondary nozzle includes a bend between the sidewall of the base and the outlet configured to pass between a first direct energy source and second direct energy source, the first energy source and second energy source disposed on a top wall of a chamber.
-
公开(公告)号：US20180223674A1
公开(公告)日：2018-08-09
申请号：US15749277
申请日：2015-07-31
申请人： Zachary James TAYLOR , Ying ZHOU , Ankit Rajesh SURTI , Hiteshkumar Rameshchandra MISTRY , GENERAL ELECTRIC COMPANY
摘要： A rotor blade for a turbine of a gas turbine includes an airfoil. The airfoil may have a leading edge, a trailing edge, an outboard, and an inboard end that attaches to a root configured to couple the rotor blade to a rotor disc. The airfoil may have a cooling configuration that includes elongated cooling channels for receiving and directing a coolant through the airfoil. The rotor blade may further include: a tip shroud connected to the airfoil; outlet ports formed through an outboard face of the tip shroud that fluidly communicate with the cooling channels; and flow directing structure formed on the outboard surface of the tip shroud. The flow directing structure may be positioned relative to the outlet ports and configured for directing the flow of coolant discharged from the outlet ports. The rotor blade may be useful to reduce local tip shroud temperature as well as improved stage aerodynamic efficiency by reducing the coolant supply needed to maintain the component at desired temperature levels.
-
公开(公告)号：US20170175535A1
公开(公告)日：2017-06-22
申请号：US14974155
申请日：2015-12-18
发明人： Rohit Chouhan , Randall Richard Good , Hiteshkumar Rameshchandra Mistry , Shashwat Swami Jaiswal
CPC分类号： F01D5/18 , F01D5/187 , F01D5/20 , F01D5/225 , F05D2220/32 , F05D2240/307 , F05D2240/55 , F05D2260/20 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine rotor blade that includes: an airfoil defined between a pressure face and a suction face; a tip shroud that includes a seal rail projecting from an outboard surface and, formed thereon, a cutter tooth; and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; a cutter tooth segment is formed within the cutter tooth of the seal rail; and branching segments formed within at least one of the tip shroud and an outboard region of the airfoil. Each of the branching segments may extend between an upstream port, which connects to the cutter tooth segment, and an outlet port, which is formed on a target surface area, so that the branching segment bisects a target interior region.
-
-
-
-
-
-
搜索结果
7 条记录 (耗时 0.016 秒)
