公开(公告)号：US07976277B2

公开(公告)日：2011-07-12

申请号：US11976286

申请日：2007-10-23

申请人： Michiel Kopmels ,  Mark T Mitchell ,  Peter J Goodman ,  Keith C Sadler

发明人： Michiel Kopmels ,  Mark T Mitchell ,  Peter J Goodman ,  Keith C Sadler

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。

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 。

公开(公告)号：US20080112816A1

公开(公告)日：2008-05-15

申请号：US11976286

申请日：2007-10-23

申请人： Michiel Kopmels ,  Mark T. Mitchell ,  Peter J. Goodman ,  Keith C. Sadler

发明人： Michiel Kopmels ,  Mark T. Mitchell ,  Peter J. Goodman ,  Keith C. Sadler

IPC分类号： F01D5/08 ,  F01D5/18

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。

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。

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

IPC分类号： F03B11/00 ,  F01D5/18

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。

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。

公开(公告)号：US08650940B2

公开(公告)日：2014-02-18

申请号：US13466581

申请日：2012-05-08

申请人： Darren L. Howard ,  Andrew Hewitt ,  Philip Ridland ,  Michiel Kopmels

发明人： Darren L. Howard ,  Andrew Hewitt ,  Philip Ridland ,  Michiel Kopmels

IPC分类号： G01M15/00

CPC分类号： F01D5/18 ,  F01D21/003 ,  F01D25/285 ,  F05D2260/81 ,  F05D2260/83 ,  G01M15/14 ,  Y02T50/676

摘要： A master component is provided for use in checking for any variation in the performance of a gas turbine test facility. The master component replaces a standard component, which is typically a turbine blade, vane or segment in the test facility. The master component is attached to the test facility in the same manner as the standard component. The flow rate through the master component is substantially the same as the flow rate through the standard component for a given inlet and outlet temperature and pressure. The flow through the master component is simpler than the flow through the standard component. This means that the flow through the master component is less likely to vary over time. As such, the master component is more suitable for use in checking for any variation in the performance of a test facility.

摘要翻译： 提供主组件用于检查燃气轮机测试设备的性能的任何变化。 主组件替代标准组件，该组件通常是测试设备中的涡轮机叶片，叶片或段。 主组件以与标准组件相同的方式连接到测试设备。 对于给定的入口和出口温度和压力，通过主组件的流速基本上与通过标准组件的流量相同。 通过主组件的流程比通过标准组件的流程更简单。 这意味着通过主组件的流量不太可能随时间而变化。 因此，主组件更适合用于检查测试设施的性能的任何变化。

公开(公告)号：US08052389B2

公开(公告)日：2011-11-08

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 that support the blade outer wall and divide the blade interior into cooling passages. The dimensions of the structure in particular the load-carrying members are chosen with respect to inward heat flow during operation to tend to reduce heat transfer from the outer wall to the load-carrying members and with respect to mass distribution in the structure to reduce centrifugal forces during operation.

摘要翻译： 无风扇的空气冷却燃气轮机叶片具有包括支撑叶片外壁并将叶片内部分成冷却通道的承载构件的内部结构。 结构的尺寸，特别是承载构件的尺寸关于操作期间的向内热流选择，以倾向于减少从外壁到承载构件的传热，并且关于结构中的质量分布以减少离心 运行期间的力量

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

CPC分类号： F01D5/188 ,  F01D5/18 ,  F01D5/186 ,  F01D5/20 ,  F01D5/225 ,  Y02T50/676

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）。

公开(公告)号：US20060140763A1

公开(公告)日：2006-06-29

申请号：US11262754

申请日：2005-11-01

申请人： Michiel Kopmels ,  Michael Jago ,  Keith Sadler ,  Peter Goodman

发明人： Michiel Kopmels ,  Michael Jago ,  Keith Sadler ,  Peter Goodman

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2260/201

摘要： A cooling arrangement 11 is provided in which an incident coolant flow 23 is presented to a passage 14 such that a proportion of that flow is diverted in order to create a standing relative overpressure in a chamber 24 compared to the actual static pressure of the flow 23 in the passage 14. In such circumstances through flow transfer apertures in the walls of the chamber 24 forced coolant flows are presented for impingement upon surfaces 26, 27 and therefore greater heat transfer. Generally, coolant flow is presented to both ends of the chamber 24 in order to create the relative standing overpressure in the chamber 24 relative to the current static pressure presented in the passage 14 through the incident flow 23. In such circumstances through utilising the dynamic rotation or other motion of a component incorporating the arrangement 11a higher relative pressure is achieved for greater force coolant flow 22 projection compared to the incident or actual static pressure of the incident coolant flow 23 in the passage 14.

摘要翻译： 提供了冷却装置11，其中入口冷却剂流23被提供到通道14，使得该流量的一部分被转向以便在腔室24中产生与流23的实际静压力相比的静止相对超压 在这种情况下，通过腔室24的壁中的流动传递孔被迫使冷却剂流动被施加以冲击在表面26,27上并且因此更大的热传递。 通常，冷却剂流动被呈现到腔室24的两端，以便相对于通过入射流23在通道14中呈现的当前静压力而在腔室24中产生相对站立的超压。在这种情况下，通过利用动态旋转 或者与通道14中的入射冷却剂流23的入射或实际静压相比，能够实现更大的力冷却剂流22的投影，或者包含结构11的部件的其它运动具有较高的相对压力。