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公开(公告)号：US20070253815A1
公开(公告)日：2007-11-01
申请号：US11207892
申请日：2005-08-22
申请人： Michiel Kopmels , Ian Tibbott , Edwin Dane , Mark Mitchell
发明人： Michiel Kopmels , Ian Tibbott , Edwin Dane , Mark Mitchell
IPC分类号： F01D5/18
摘要： An internal fluid cooling system for a gas turbine aerofoil (2) comprises a plurality of multi-pass cooling arrangements each of which consists of a serpentine passage (50,52,54 & 48,56,58) in the interior of the aerofoil (2). The cooling fluid—in particular air—is supplied to an inlet end (22,24) of each passage (50,52,54 & 48,56,58) and exhausted through a multiplicity of discharge holes (60,62,64,68) to provide tip, leading edge, trailing edge and surface film cooling. The inlet end (22) of a first serpentine passage (50,52,54) is positioned close to the leading edge (26) and flows rearwards while the inlet end (24) of the second serpentine passage (48,56,58) is positioned close to the trailing edge (28) and flows forwards. These serpentine passages are disposed side-by-side, one adjacent the pressure surface (14) and the other adjacent the suction surface (16) on opposite sides of a main load carrying member (30) which comprises a major part of the internal structure (30,36,38,40,42,44) of the aerofoil (2).
摘要翻译： 用于燃气轮机机翼（2）的内部流体冷却系统包括多个多通道冷却装置，每个多通道冷却装置由机翼内部的蛇形通道（50,52,54和48,56,58） 2）。 冷却流体 - 特别是空气 - 被供应到每个通道（50,52,54和48,56,58）的入口端（22,24），并通过多个排放孔（60,62,64， 68）提供尖端，前缘，后缘和表面膜冷却。 第一蛇形通道（50,52,54）的入口端（22）定位成靠近前缘（26）并向后流动，同时第二蛇形通道（48,56,58）的入口端（24） 定位成靠近后缘（28）并向前流动。 这些蛇形通道并排设置，一个邻近压力表面（14），另一个邻近主负载承载构件（30）的相对侧的吸附表面（16），该主负载承载构件（30）包括内部结构的主要部分 （30,36,38,40,42,44）的机翼（2）。
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公开(公告)号：US07442008B2
公开(公告)日：2008-10-28
申请号：US11207892
申请日：2005-08-22
申请人： Michiel Kopmels , Ian Tibbott , Edwin Dane , Timothy M Mitchell
发明人： Michiel Kopmels , Ian Tibbott , Edwin Dane , Timothy M Mitchell
IPC分类号： F01D5/18
摘要： An internal fluid cooling system for a gas turbine aerofoil comprises a plurality of multi-pass cooling arrangements each of which consists of a serpentine passage in the interior of the aerofoil. The cooling fluid—in particular air—is supplied to an inlet end of each passage and exhausted through a multiplicity of discharge holes to provide tip, leading edge, trailing edge and surface film cooling. The inlet end of a first serpentine passage is positioned close to the leading edge and flows rearwards while the inlet end of the second serpentine passage is positioned close to the trailing edge and flows forwards. These serpentine passages are disposed side-by-side, one adjacent the pressure surface and the other adjacent the suction surface on opposite sides of a main load carrying member which comprises a major part of the internal structure of the aerofoil.
摘要翻译： 用于燃气涡轮机翼型的内部流体冷却系统包括多个多通道冷却装置，每个多通道冷却装置由机翼内部的蛇形通道组成。 冷却流体 - 特别是空气 - 被供应到每个通道的入口端并通过多个排出孔排出以提供尖端，前缘，后缘和表面膜冷却。 第一蛇形通道的入口端定位成靠近前缘并向后流动，而第二蛇形通道的入口端靠近后缘定位并向前流动。 这些蛇形通道并排设置，一个邻近压力表面，另一个邻近主负荷承载构件的相对侧的吸入表面，该主负载承载构件包括机翼的内部结构的主要部分。
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公开(公告)号：US07976277B2
公开(公告)日：2011-07-12
申请号：US11976286
申请日：2007-10-23
IPC分类号： F01D11/00
CPC分类号： F01D5/188 , F01D5/186 , Y02T50/673 , Y02T50/676
摘要： A component such as a turbine blade of a gas turbine engine has a cooling arrangement comprising a cascade impingement array in which cooling air flows from a supply chamber through impingement passages in webs to an internal passageway comprising first and second limbs. The cooling air flow through the limbs, provides improved heat transfer compared with continued impingement cooling in the chordwise direction of the blade.
摘要翻译： 诸如燃气涡轮发动机的涡轮叶片的部件具有冷却装置，该冷却装置包括级联冲击阵列，其中冷却空气从供应室通过腹板中的冲击通道流动到包括第一和第二分支的内部通道。 通过四肢的冷却空气流动，与叶片的弦向方向上的持续冲击冷却相比，提供了更好的传热。
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公开(公告)号：US07273351B2
公开(公告)日：2007-09-25
申请号：US11266358
申请日：2005-11-04
申请人： Michiel Kopmels
发明人： Michiel Kopmels
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A component such as a turbine blade of a gas turbine engine includes a film cooling arrangement which is optimized by a process in which a component is manufactured having a film cooling arrangement of an initial design and evaluation of the performance of the film cooling arrangement is conducted, for example on the basis of the blowing rate of cooling holes present in the initial design. The configuration of a cooling hole of the initial design is subsequently modified in order to improve the performance of the film cooling arrangement and a component is manufactured in accordance with the modified design. By way of example, the initial design may provide a single cooling hole 128 and the modification may comprise the provision of additional cooling holes 126, 130, each intersecting the initial cooling hole 128 adjacent its inlet end which opens into a source of cooling fluid 120.
摘要翻译： 诸如燃气涡轮发动机的涡轮机叶片的部件包括薄膜冷却装置，其通过制造具有初始设计的薄膜冷却布置并且评估薄膜冷却装置的性能的方法进行优化 ，例如基于初始设计中存在的冷却孔的吹送速率。 随后修改初始设计的冷却孔的结构，以便提高膜冷却装置的性能，并且根据改进的设计制造部件。 作为示例，初始设计可以提供单个冷却孔128，并且修改可以包括设置附加的冷却孔126,130，其各自与初始冷却孔128相邻，其邻近其入口端，该入口端通向冷却流体源120 。
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公开(公告)号：US20080112816A1
公开(公告)日：2008-05-15
申请号：US11976286
申请日：2007-10-23
CPC分类号： F01D5/188 , F01D5/186 , Y02T50/673 , Y02T50/676
摘要： A component such as a turbine blade of a gas turbine engine has a cooling arrangement comprising a cascade impingement array in which cooling air flows from a supply chamber through impingement passages in webs to an internal passageway comprising first and second limbs. The cooling air flow through the limbs, provides improved heat transfer compared with continued impingement cooling in the chordwise direction of the blade.
摘要翻译： 诸如燃气涡轮发动机的涡轮叶片的部件具有冷却装置，该冷却装置包括级联冲击阵列，其中冷却空气从供应室通过腹板中的冲击通道流动到包括第一和第二分支的内部通道。 通过四肢的冷却空气流动，与叶片的弦向方向上的持续冲击冷却相比，提供了更好的传热。
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公开(公告)号：US20070286729A1
公开(公告)日：2007-12-13
申请号：US11207869
申请日：2005-08-22
申请人： Michiel Kopmels
发明人： Michiel Kopmels
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/147 , F01D5/18 , F01D5/186 , F05D2260/231 , Y02T50/671 , Y02T50/676
摘要： A shroudless, air cooled gas turbine blade has an internal structure including load-carrying members (36,38,40) that support the blade outer wall (10) and divide the blade interior into cooling passages (28,30,32,34). The dimensions of the structure in particular the load-carrying members (36,38,40) are chosen with respect to inward heat flow during operation to tend to reduce heat transfer from the outer wall (10) to the load-carrying members (36,38,40) and with respect to mass distribution in the structure to reduce centrifugal forces during operation.
摘要翻译： 无风扇的空气冷却的燃气轮机叶片具有内部结构，其包括支撑叶片外壁（10）并将叶片内部分成冷却通道（28,30,32,34）的承载构件（36,38,40） 。 结构的尺寸，特别是承载构件（36,38,40）的尺寸在操作期间相对于向内的热流量被选择以倾向于减少从外壁（10）到承载构件（36）的热传递 ，38,40），并且关于结构中的质量分布以减少操作期间的离心力。
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公开(公告)号：US07273350B2
公开(公告)日：2007-09-25
申请号：US11272969
申请日：2005-11-15
申请人： Michiel Kopmels , Keith C. Sadler
发明人： Michiel Kopmels , Keith C. Sadler
CPC分类号： F01D5/187 , F05D2250/231 , F05D2250/241 , F05D2250/313 , F05D2250/314 , F05D2260/201
摘要： A heat transfer arrangement comprises a target member (28 or 30), and an impingement member (32). The impingement member (32) defines a fluid path (38 or 40) there through to direct fluid onto the target member. The arrangement includes a fluid directing formation (42) on the impingement member (32). The fluid path (38 or 40) extends through the fluid directory formation (42) such that the fluid path directs fluid to exit there from at an exit angle that is substantially orthogonal to the fluid directing formation.
摘要翻译： 传热装置包括目标构件（28或30）和冲击构件（32）。 冲击构件（32）在其上限定流体路径（38或40）以将流体引导到目标构件上。 该装置包括在冲击构件（32）上的流体引导构件（42）。 流体路径（38或40）延伸穿过流体目录形成（42），使得流体路径引导流体从基本上垂直于流体引导结构的出射角度离开该流体路径。
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公开(公告)号：US20060039787A1
公开(公告)日：2006-02-23
申请号：US11199180
申请日：2005-08-09
申请人： Peter Goodman , Keith Sadler , Michiel Kopmels
发明人： Peter Goodman , Keith Sadler , Michiel Kopmels
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/202
摘要： A component such as a turbine blade for a gas turbine engine has a cooling arrangement comprising a supply passage 18 within the blade from which extend cooling passages 28 of a first array which open at discharge openings 29, for example at a trailing edge of the blade. Cooling passages 30 of a second array extend into the blade from discharge openings 31, and intersect the passages 28. The passages 30 terminate short of the supply passage 18. As a result of this arrangement, the limiting flow area for cooling air is defined by the cooling passages 28 of the first array, and is not affected by the accuracy with which the cooling passages 30 of the second array intersect the cooling passages 28 of the first array.
摘要翻译： 诸如用于燃气涡轮发动机的涡轮机叶片的部件具有冷却装置，该冷却装置包括在叶片内的供应通道18，在其中延伸第一阵列的冷却通道28，其在排出开口29处例如在叶片的后缘处打开 。 第二阵列的冷却通道30从排出口31延伸到叶片中，并与通道28相交。通道30终止于供应通道18的末端。由于这种布置，冷却空气的限制流动面积由 第一阵列的冷却通道28不受第二阵列的冷却通道30与第一阵列的冷却通道28相交的精度的影响。
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公开(公告)号：US08262355B2
公开(公告)日：2012-09-11
申请号：US12230159
申请日：2008-08-25
申请人： Michiel Kopmels
发明人： Michiel Kopmels
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/22141
摘要： A component, such as a turbine blade of a gas turbine engine, has an internal cooling system which includes a passage (28) having a passage inlet (22) and a passage exit (30), which may be in the form of passageways at or adjacent to the trailing edge of the component. The passage (28) is divided into chambers (52, 54, 56, 58) by partitions (40, 42, 44) which extend from one wall (34) of the component and terminate short of the opposite wall (36) to provide gaps (46, 48, 50) to permit chord-wise cooling air flow from the passage inlet (22) to the passage exit (30). The gaps (46, 48, 50) force the cooling air to pass adjacent the hot walls (34, 36), so increasing the heat transfer coefficient between the cooling air and the material of the component.
摘要翻译： 诸如燃气涡轮发动机的涡轮叶片的部件具有内部冷却系统，其包括具有通道入口（22）和通道出口（30）的通道（28），通道出口（30）可以是通道 或邻近部件的后缘。 所述通道（28）通过从所述部件的一个壁（34）延伸并且终止于相对的壁（36）的端部的分隔件（40,42,44）分成室（52,54,56,58），以提供 间隙（46,48,50），以允许从通道入口（22）到通道出口（30）的和弦冷却空气流。 间隙（46,48,50）迫使冷却空气相邻于热壁（34,36）通过，从而增加冷却空气与部件材料之间的传热系数。
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公开(公告)号：US20100047057A1
公开(公告)日：2010-02-25
申请号：US12385249
申请日：2009-04-02
申请人： Michiel Kopmels
发明人： Michiel Kopmels
CPC分类号： F01D5/20
摘要： An aerofoil comprising a pressure-side wall, a suction-side wall and an intermediate wall extending from a free end of the pressure-side wall at an acute angle relative thereto towards the suction-side wall. A cooling fluid passageway extends through a region where the intermediate wall meets the pressure-side wall at an apex. The fluid passageway has an opening, at least in part, in the face of the pressure-side wall.
摘要翻译： 一种机翼，包括压力侧壁，吸力侧壁和从压力侧壁的自由端相对于吸入侧壁以锐角延伸的中间壁。 冷却流体通道延伸穿过中间壁在顶点处与压力侧壁相遇的区域。 流体通道至少部分地具有在压力侧壁的表面上的开口。
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