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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.
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公开(公告)号：US20120163969A1
公开(公告)日：2012-06-28
申请号：US12977115
申请日：2010-12-23
申请人： Chaitanya Venkata Rama Krishna Ongole , Subhrajit Dey , Dale William Ladoon , Manisekaran Santhanakrishnan , Hiteshkumar Rameshchandra Mistry
发明人： Chaitanya Venkata Rama Krishna Ongole , Subhrajit Dey , Dale William Ladoon , Manisekaran Santhanakrishnan , Hiteshkumar Rameshchandra Mistry
IPC分类号： F04D29/54
CPC分类号： F01D25/30
摘要： A turbine includes an inner casing, a rotor extending in a longitudinal direction, and rows of buckets transversely disposed on the rotor. A bearing cone covering a portion of the rotor and a flow guide extending from the inner casing define an annular passage for flow of exhaust gases. Exhaust gas movement is facilitated by a guide cap having a streamlined surface and situated in a downstream direction of the flow guide, a tip leakage flow injection channel to inject exhaust gases at the inner surface of the flow guide, an incline of the casing of the turbine surrounding the last stage buckets relative to the longitudinal axis, or use of a first portion of the annular passage with a substantially constant surface area and a second portion of the annular passage with a progressively increasing surface area.
摘要翻译： 涡轮机包括内壳体，沿纵向方向延伸的转子和横向设置在转子上的排排。 覆盖转子的一部分的轴承锥体和从内壳延伸的流动引导件限定用于排出气体的环形通道。 通过具有流线型表面并且位于流动引导件的下游方向上的引导帽促进排气运动，在流动引导件的内表面处注入废气的末端泄漏流注入通道， 围绕最后一级铲斗相对于纵向轴线的涡轮机，或者使用具有基本上恒定的表面积的环形通道的第一部分和具有逐渐增加的表面积的环形通道的第二部分。
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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.
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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.
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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).
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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.
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