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公开(公告)号：US06694742B2
公开(公告)日：2004-02-24
申请号：US10179277
申请日：2002-06-26
申请人： Ravi Rajamani , David Allen Flodman , Robert Scott Garry , Bruce Gordon Norman , Leroy Tomlinson
发明人： Ravi Rajamani , David Allen Flodman , Robert Scott Garry , Bruce Gordon Norman , Leroy Tomlinson
IPC分类号： F02C100
CPC分类号： F02C9/28 , F05D2270/114 , F05D2270/303 , F05D2270/3032 , F05D2270/44
摘要： Critical stress in a gas turbine can be estimated using one or more readily measurable temperatures in the gas turbine. First and second critical temperatures can be estimated based on the at least one measurable temperature using heat conduction and convection equations. Subsequently, the critical stress can be estimated in real time according to a stress model prediction based on the difference between the critical temperatures, and possibly the rotational speed of the turbine, and some parameter, such as air pressure, that is indicative of air flow around the turbine component. Operation of the gas turbine can thus be controlled using the estimated critical temperatures.
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公开(公告)号：US06595748B2
公开(公告)日：2003-07-22
申请号：US09921432
申请日：2001-08-02
IPC分类号： F01D518
CPC分类号： F01D5/186 , F05D2240/121 , F05D2240/303 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having a leading edge flow chamber disposed behind a leading edge in front of a pair of side channels. The leading edge channel receives coolant from the pressure side channel in isolation from the suction side channel.
摘要翻译： 涡轮机叶片包括具有前缘流动室的翼型件，其设置在一对侧通道前方的前缘之后。 前缘通道与吸力侧通道隔离地从压力侧通道接收冷却剂。
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公开(公告)号：US20100281879A1
公开(公告)日：2010-11-11
申请号：US11965402
申请日：2007-12-27
申请人： Jason David Shapiro , David Allen Flodman , Samuel Ross Rulli , Samir Dimitri Sayegh , Norman Clement Brackett
发明人： Jason David Shapiro , David Allen Flodman , Samuel Ross Rulli , Samir Dimitri Sayegh , Norman Clement Brackett
CPC分类号： F02C7/18 , F01D5/08 , F01D9/041 , F01D9/06 , F01D11/001 , F01D11/08 , F01D25/12 , F01D25/246 , F05D2220/3213 , F05D2240/11 , F05D2260/201 , Y02T50/676
摘要： A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle having: (i) spaced-apart arcuate inner and outer bands; and (ii) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the vane disposed in a primary flowpath of the engine; (b) a supporting structure coupled to the outer band such that an outer band cavity is defined between the outer band and the stationary structure; (c) a first conduit passing through the outer band cavity and communicating with the interior of the vane, the first conduit coupled to a first source of cooling air within the engine; and (d) a second conduit communicating with the outer band cavity, the second conduit coupled to a second source of cooling air within the engine.
摘要翻译： 用于燃气涡轮发动机的冷却装置包括：（a）涡轮喷嘴，其具有：（i）间隔开的弓形内部和外部带; 和（ii）在所述内带和外带之间延伸的中空翼型涡轮叶片，所述叶片设置在所述发动机的主流路中; （b）耦合到所述外带的支撑结构，使得在所述外带和所述固定结构之间限定外带空腔; （c）通过所述外带空腔并与所述叶片内部连通的第一管道，所述第一管道联接到所述发动机内的第一冷却空气源; 和（d）与外带空腔连通的第二导管，第二导管连接到发动机内的第二冷却空气源。
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公开(公告)号：US20090245999A1
公开(公告)日：2009-10-01
申请号：US12055101
申请日：2008-03-25
申请人： David Allen Flodman , Jason David Shapiro , Robert Francis Manning , Mark Douglas Gledhill , Tyler Frederick Hooper
发明人： David Allen Flodman , Jason David Shapiro , Robert Francis Manning , Mark Douglas Gledhill , Tyler Frederick Hooper
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.
摘要翻译： 用于燃气涡轮发动机的涡轮喷嘴包括：（a）间隔开的弓形内部和外部带; （b）在所述内部和外部带之间延伸的中空翼型涡轮机叶片，所述叶片的内部至少限定前腔和位于所述前腔后面的中空腔; （c）容纳在中空腔内的中空冲击插入件，冲击插入件具有用至少一个冲击冷却孔刺穿的壁; （d）在所述前腔的径向外端处的涡轮叶片中的通道，其适于联接到冷却空气源; 和（e）内带中的与前腔的径向内端流体连通的通道和冲击插入件的径向内端。
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公开(公告)号：US08172504B2
公开(公告)日：2012-05-08
申请号：US12055101
申请日：2008-03-25
申请人： David Allen Flodman , Jason David Shapiro , Robert Francis Manning , Mark Douglas Gledhill , Tyler Frederick Hooper
发明人： David Allen Flodman , Jason David Shapiro , Robert Francis Manning , Mark Douglas Gledhill , Tyler Frederick Hooper
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.
摘要翻译： 用于燃气涡轮发动机的涡轮喷嘴包括：（a）间隔开的弓形内部和外部带; （b）在所述内部和外部带之间延伸的中空翼型涡轮机叶片，所述叶片的内部至少限定前腔和位于所述前腔后面的中空腔; （c）容纳在中空腔内的中空冲击插入件，冲击插入件具有用至少一个冲击冷却孔刺穿的壁; （d）在所述前腔的径向外端处的涡轮叶片中的通道，其适于联接到冷却空气源; 和（e）内带中的与前腔的径向内端流体连通的通道和冲击插入件的径向内端。
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公开(公告)号：US07946801B2
公开(公告)日：2011-05-24
申请号：US11965402
申请日：2007-12-27
申请人： Jason David Shapiro , David Allen Flodman , Samuel Ross Rulli , Samir Dimitri Sayegh , Norman Clement Brackett
发明人： Jason David Shapiro , David Allen Flodman , Samuel Ross Rulli , Samir Dimitri Sayegh , Norman Clement Brackett
IPC分类号： F01D5/08
CPC分类号： F02C7/18 , F01D5/08 , F01D9/041 , F01D9/06 , F01D11/001 , F01D11/08 , F01D25/12 , F01D25/246 , F05D2220/3213 , F05D2240/11 , F05D2260/201 , Y02T50/676
摘要： A cooling arrangement for a gas turbine engine includes: (a) a turbine nozzle having: (i) spaced-apart arcuate inner and outer bands; and (ii) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the vane disposed in a primary flowpath of the engine; (b) a supporting structure coupled to the outer band such that an outer band cavity is defined between the outer band and the stationary structure; (c) a first conduit passing through the outer band cavity and communicating with the interior of the vane, the first conduit coupled to a first source of cooling air within the engine; and (d) a second conduit communicating with the outer band cavity, the second conduit coupled to a second source of cooling air within the engine.
摘要翻译： 用于燃气涡轮发动机的冷却装置包括：（a）涡轮喷嘴，其具有：（i）间隔开的弓形内部和外部带; 和（ii）在所述内带和外带之间延伸的中空翼型涡轮叶片，所述叶片设置在所述发动机的主流路中; （b）耦合到所述外带的支撑结构，使得在所述外带和所述固定结构之间限定外带空腔; （c）通过所述外带空腔并与所述叶片内部连通的第一管道，所述第一管道联接到所述发动机内的第一冷却空气源; 和（d）与外带空腔连通的第二导管，第二导管连接到发动机内的第二冷却空气源。
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公开(公告)号：US07377743B2
公开(公告)日：2008-05-27
申请号：US11311104
申请日：2005-12-19
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D9/041 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes a mid vane mounted between a pair of end vanes in outer and inner bands. The mid vane includes a first pattern of film cooling holes configured to discharge more cooling air than each of the two end vanes having respective second patterns of film cooling holes.
摘要翻译： 涡轮喷嘴包括安装在外带和内带中的一对末端叶片之间的中间叶片。 中间叶片包括第一图案的薄膜冷却孔，其被配置为比具有相应的第二图案的薄膜冷却孔的两个末端叶片中的每一个排出更多的冷却空气。
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公开(公告)号：US20090220331A1
公开(公告)日：2009-09-03
申请号：US12040482
申请日：2008-02-29
IPC分类号： F01D25/12
CPC分类号： F01D9/042 , F01D25/12 , F01D25/14 , F01D25/246 , F05D2240/81 , F05D2260/201
摘要： A turbine nozzle segment includes: (a) an arcuate outer band segment; (b) a hollow, airfoil-shaped turbine vane extending radially inward from the outer band segment; (c) a manifold cover secured to the outer band such that the manifold cover and the outer band segment cooperatively define an impingement cavity; and (d) an impingement blanket disposed in the impingement cavity, the impingement blanket having at least one impingement hole formed therethrough which is arranged to direct cooling air at the outer band segment. A method is provided for impingement cooling the outer band segment.
摘要翻译： 涡轮喷嘴段包括：（a）弓形外带段; （b）从外带段径向向内延伸的中空翼型涡轮叶片; （c）固定到外带的歧管盖，使得歧管盖和外带段协调地限定冲击腔; 和（d）设置在所述冲击腔中的冲击毯，所述冲击毯具有穿过其形成的至少一个冲击孔，所述冲击孔被布置成引导所述外带段处的冷却空气。 提供了一种冲击冷却外带段的方法。
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公开(公告)号：US07246999B2
公开(公告)日：2007-07-24
申请号：US10959615
申请日：2004-10-06
IPC分类号： B63H1/14
CPC分类号： F01D5/187 , F01D5/186 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil includes an internal cooling circuit between opposite pressure and suction sidewalls. The pressure sidewall includes a row of outlet slots for the circuit separated by converging partitions. Each slot includes an inlet, throat, and diverging outlet. Each of the partitions includes a step in a converging sidewall thereof for increasing divergence of the slots to diffuse coolant discharged therethrough.
摘要翻译： 涡轮机翼片包括在相对的压力和抽吸侧壁之间的内部冷却回路。 压力侧壁包括一排用于通过会聚隔板分开的电路的出口槽。 每个槽包括一个入口，喉部和发散出口。 每个分隔件包括在其会聚的侧壁中的台阶，用于增加槽的扩散，以扩散从其中排出的冷却剂。
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