专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08523523B2 Cooling arrangements 有权
标题翻译：冷却装置
公开(公告)号：US08523523B2
公开(公告)日：2013-09-03
申请号：US12787758
申请日：2010-05-26
申请人： Roderick M. Townes , Ian Tibbott , Edwin Dane , Caner H. Helvaci
发明人： Roderick M. Townes , Ian Tibbott , Edwin Dane , Caner H. Helvaci
IPC分类号： F01D5/08 , F01D5/20
CPC分类号： F01D5/187 , F05D2250/11 , F05D2250/70 , F05D2260/2212 , F05D2260/22141
摘要： Providing cooling within hollow blades such as high pressure turbine blades in a gas turbine engine is important to maintain these components within operational margins for the materials from which they are formed. Traditionally, coolant flows in hollow passages have been used along with impingement apertures towards a leading passage for cooling effectiveness. It is known that opposed undulations or ribs can create rotational vortices within the passage. By shaping shaped portions between the opposed undulations and possibly providing undulations upon these shaped portions themselves it is possible to generate stronger more powerful vortices within the passage. These vortices are coupled with the impingement orifices to create proportionally greater impingement jet flow and pressure and therefore cooling effectiveness within the leading passage.
摘要翻译：在诸如燃气轮机发动机中的高压涡轮机叶片的中空叶片内提供冷却对于将这些部件保持在其形成的材料的操作边缘内是重要的。传统上，在中空通道中的冷却剂流已经与冲击孔一起使用，朝向前导通道以降低冷却效果。已知相对的起伏或肋可以在通道内产生旋转涡流。通过在相对的波纹之间成形成形部分并且可能在这些成形部分本身上提供起伏，可以在通道内产生更强大的更强大的涡流。这些涡流与冲击孔结合，以产生比例地更大的冲击射流和压力，从而在前导通道内产生冷却效果。

2. 发明申请

US20100303635A1 COOLING ARRANGEMENTS 有权
标题翻译：冷却安排
公开(公告)号：US20100303635A1
公开(公告)日：2010-12-02
申请号：US12787758
申请日：2010-05-26
申请人： Roderick M. TOWNES , Ian Tibbott , Edwin Dane , Caner H. Helvaci
发明人： Roderick M. TOWNES , Ian Tibbott , Edwin Dane , Caner H. Helvaci
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/11 , F05D2250/70 , F05D2260/2212 , F05D2260/22141
摘要： Providing cooling within hollow blades such as high pressure turbine blades in a gas turbine engine is important to maintain these components within operational margins for the materials from which they are formed. Traditionally, coolant flows in hollow passages have been used along with impingement apertures towards a leading passage for cooling effectiveness. It is known that opposed undulations or ribs can create rotational vortices within the passage. By shaping shaped portions between the opposed undulations and possibly providing undulations upon these shaped portions themselves it is possible to generate stronger more powerful vortices within the passage. These vortices are coupled with the impingement orifices to create proportionally greater impingement jet flow and pressure and therefore cooling effectiveness within the leading passage.
摘要翻译：在诸如燃气轮机发动机中的高压涡轮机叶片的中空叶片内提供冷却对于将这些部件保持在其形成的材料的操作边缘内是重要的。传统上，在中空通道中的冷却剂流已经与冲击孔一起使用，朝向前导通道以降低冷却效果。已知相对的起伏或肋可以在通道内产生旋转涡流。通过在相对的波纹之间成形成形部分并且可能在这些成形部分本身上提供起伏，可以在通道内产生更强大的更强大的涡流。这些涡流与冲击孔结合，以产生比例地更大的冲击射流和压力，从而在前导通道内产生冷却效果。

3. 发明授权

US08845280B2 Blades 有权
标题翻译：叶片
公开(公告)号：US08845280B2
公开(公告)日：2014-09-30
申请号：US13069011
申请日：2011-03-22
申请人： Stephen C. Diamond , Caner H. Helvaci , Roderick M. Townes , Ian Tibbott , Dougal R. Jackson
发明人： Stephen C. Diamond , Caner H. Helvaci , Roderick M. Townes , Ian Tibbott , Dougal R. Jackson
IPC分类号： F01D11/08 , F01D5/20
CPC分类号： F01D5/20
摘要： A turbine blade for a gas turbine engine has an aerofoil portion extending from a root to a tip. The tip carries winglets. A gutter extends across the tip to entrain gas leaking around the tip (over tip leakage). The aerofoil portion has a mean camber line and the gutter has a center line. In the examples described, the conditions that (a) the mean camber line and the centre line coincide at the exit when viewed from the tip towards the root, and (b) the mean camber line and the center line are parallel at the exit when viewed as aforesaid, are not both fulfilled.
摘要翻译：用于燃气涡轮发动机的涡轮机叶片具有从根部延伸到尖端的机翼部分。小提示带有小翼。沟槽延伸穿过尖端以夹带气体在尖端周围泄漏（超过尖端泄漏）。机翼部分具有平均曲线，并且沟槽具有中心线。在所描述的例子中，（a）平均弧线和中心线在从尖端朝向根部的出口处重合，和（b）平均弧线和中心线在出口处平行，如上所述，并不都是满足的。

4. 发明授权

US08851833B2 Blades 有权
标题翻译：叶片
公开(公告)号：US08851833B2
公开(公告)日：2014-10-07
申请号：US13053928
申请日：2011-03-22
申请人： Stephen C. Diamond , Caner H. Helvaci , Roderick M. Townes , Ian Tibbott , Dougal R. Jackson
发明人： Stephen C. Diamond , Caner H. Helvaci , Roderick M. Townes , Ian Tibbott , Dougal R. Jackson
IPC分类号： F01D11/08 , F01D5/20
CPC分类号： F01D5/20
摘要： A rotor blade 40 for a gas turbine engine has an aerofoil portion 42 from a root 48 to a tip 54. In use, combustion gas may leak over the tip 54 from the pressure face 52 to the suction face 50. A gutter 62 extends across the tip 54 to entrain any over tip leakage gap. The floor of the gutter defines an increased depth portion 72 at the exit end of the gutter 62.
摘要翻译：用于燃气涡轮发动机的转子叶片40具有从根部48到尖端54的机翼部分42.在使用中，燃烧气体可能在尖端54上从压力面52泄漏到吸力面50.沟槽62延伸越过尖端54夹带任何过度的尖端泄漏间隙。沟槽的地板在沟槽62的出口处限定增加的深度部分72。

5. 发明申请

US20100054955A1 Blades 审中-公开
标题翻译：叶片
公开(公告)号：US20100054955A1
公开(公告)日：2010-03-04
申请号：US12458540
申请日：2009-07-15
申请人： Caner H. Helvaci , Roderick M. Townes , Stephen Diamond
发明人： Caner H. Helvaci , Roderick M. Townes , Stephen Diamond
IPC分类号： F01D5/18 , B23P15/04
CPC分类号： F01D5/20 , F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2250/185 , Y10T29/49341
摘要： A rotary blade, such as a turbine blade for a gas turbine engine, has an aerofoil portion with a tip partly shrouded by winglets. A gutter extends across the radially outer face of the tip to leave upstands. Cooling air feed galleries are drilled into each upstand, from the trailing edge, toward the upper end of a cooling air feed void, which is spaced from the trailing edge. Cooling passages are drilled from the winglet edges to the gallery. Cooling air supplied through the void passes along the gallery, through the passages and leaves the blade at the cooling holes. This allows cooling to be provided near the trailing edge of the tip without requiring the geometry around the trailing edge to be thickened to accommodate a cooling air void.
摘要翻译：诸如用于燃气涡轮发动机的涡轮机叶片的旋转叶片具有机翼部分，其尖端部分地被小翼罩住。沟槽延伸穿过尖端的径向外表面以离开竖立。从后缘到冷却空气供给空隙的上端钻出冷却空气供给库，后者与后缘间隔开。从小翼边缘到画廊钻出冷却通道。通过空气供应的冷却空气沿着通道通过通道，并将叶片留在冷却孔处。这允许在尖端的后缘附近提供冷却，而不需要使后缘附近的几何形状加厚以适应冷却空气空隙。

6. 发明授权

US08353672B2 Turbine blade damper arrangement 有权
标题翻译：涡轮叶片阻尼器装置
公开(公告)号：US08353672B2
公开(公告)日：2013-01-15
申请号：US12458417
申请日：2009-07-10
申请人： Roderick M. Townes , Caner H. Helvaci , Adrian J. Webster
发明人： Roderick M. Townes , Caner H. Helvaci , Adrian J. Webster
IPC分类号： F01D11/00
CPC分类号： F01D5/26 , F01D5/10 , F01D5/22 , F01D11/006 , F01D11/008 , F01D25/06 , F05D2260/96
摘要： A turbine blade damper arrangement in which a damper is positioned against the undersides of the platforms of adjacent turbine blades. In operation, the damper is centrifugally urged into engagement with the blade platforms to provide damping of relative movement between the blades. The damper and platform surfaces that it engages are of part-cylindrical configuration in order to minimize gas leakage paths between the damper and blade platforms.
摘要翻译：一种涡轮叶片阻尼器装置，其中阻尼器抵靠相邻涡轮叶片的平台的下侧定位。在操作中，阻尼器被离心地推动与叶片平台接合以提供叶片之间的相对运动的阻尼。其接合的阻尼器和平台表面是部分圆柱形构造，以便最小化阻尼器和叶片平台之间的气体泄漏路径。

7. 发明申请

US20100061854A1 Turbine blade damper arrangement 有权
标题翻译：涡轮叶片阻尼器装置
公开(公告)号：US20100061854A1
公开(公告)日：2010-03-11
申请号：US12458417
申请日：2009-07-10
申请人： Roderick M. Townes , Caner H. Helvaci , Adrian J. Webster
发明人： Roderick M. Townes , Caner H. Helvaci , Adrian J. Webster
IPC分类号： F01D5/18 , F01D5/26
CPC分类号： F01D5/26 , F01D5/10 , F01D5/22 , F01D11/006 , F01D11/008 , F01D25/06 , F05D2260/96
摘要： A turbine blade damper arrangement in which a damper is positioned against the undersides of the platforms of adjacent turbine blades. In operation, the damper is centrifugally urged into engagement with the blade platforms to provide damping of relative movement between the blades. The damper and platform surfaces that it engages are of part-cylindrical configuration in order to minimise gas leakage paths between the damper and blade platforms.
摘要翻译：一种涡轮叶片阻尼器装置，其中阻尼器抵靠相邻涡轮叶片的平台的下侧定位。在操作中，阻尼器被离心地推动与叶片平台接合以提供叶片之间的相对运动的阻尼。其接合的阻尼器和平台表面是部分圆柱形构造，以便最小化阻尼器和叶片平台之间的气体泄漏路径。

8. 发明申请

US20090263235A1 Damper 有权
标题翻译：阻尼器
公开(公告)号：US20090263235A1
公开(公告)日：2009-10-22
申请号：US12382535
申请日：2009-03-18
申请人： Ian Tibbott , Caner H. Helvaci
发明人： Ian Tibbott , Caner H. Helvaci
IPC分类号： F01D25/04
CPC分类号： F01D11/006 , F01D5/22 , F05D2250/314 , Y10S416/50
摘要： Dampers (56, 76, 96) are utilised with regard to mounting arrangements (50, 70, 90) in gas turbine engines (10) in order to facilitate cooling. It is known to provide slotted upper surface or cottage roof dampers to enhance cooling effect. However, cooling efficiency cannot be optimised and improving cooling effectiveness particularly between the parts of a mounting arrangement can be difficult without detrimental reductions in overall efficiency of a gas turbine engine (10) incorporating such a mounting. By provision of impingement jets (54, 75, 94) which extend through the damper (56, 76, 96) into slots (51, 71, 91) which define an upper surface of the damper (56, 76, 96) improvements in cooling efficiency can be achieved. The slots (51, 71 91) are typically closed to reduce requirements with respect to pressure differentials. However, open ended slots (51, 71, 91) with impingement jets (54, 74, 94) can also be provided. Typically, the slots (51, 71, 91) extend laterally across the dampers (56, 76, 96) but could also extend longitudinally with closed ends or one end open. By such an approach improved heat transfer is achieved without necessary increases in pressure gradients and flow rates.
摘要翻译：关于在燃气涡轮发动机（10）中的安装布置（50,70,90）来使用阻尼器（56,76,96），以便于冷却。已知提供开槽的上表面或山寨屋顶阻尼器以增强冷却效果。然而，不能优化冷却效率，特别是在安装装置的部件之间改善冷却效果可能是困难的，而不会有混合这种安装的燃气涡轮发动机（10）的总效率的降低。通过设置延伸穿过阻尼器（56,76,96）的冲击射流（54,75,94）到限定阻尼器（56,76,96）的上表面的狭槽（51,71,91）中，可以实现冷却效率。狭槽（51,71 91）通常是关闭的，以减少关于压差的要求。然而，也可以提供具有冲击射流（54,74,94）的开口槽（51,71,91）。通常，槽（51,71,91）横向延伸穿过阻尼器（56,76,96），但是也可以在封闭端或一端打开的情况下纵向延伸。通过这种方法，在不需要增加压力梯度和流速的情况下，可以实现改进的传热。

9. 发明授权

US08096769B2 Damper 有权
标题翻译：阻尼器
公开(公告)号：US08096769B2
公开(公告)日：2012-01-17
申请号：US12382535
申请日：2009-03-18
申请人： Ian Tibbott , Caner H. Helvaci
发明人： Ian Tibbott , Caner H. Helvaci
IPC分类号： F01D5/08
CPC分类号： F01D11/006 , F01D5/22 , F05D2250/314 , Y10S416/50
摘要： Dampers (56, 76, 96) are utilized with regard to mounting arrangements (50, 70, 90) in gas turbine engines (10) in order to facilitate cooling. It is known to provide slotted upper surface or cottage roof dampers to enhance cooling effect. However, cooling efficiency cannot be optimized and improving cooling effectiveness particularly between the parts of a mounting arrangement can be difficult without detrimental reductions in overall efficiency of a gas turbine engine (10) incorporating such a mounting. By provision of impingement jets (54, 75, 94) which extend through the damper (56, 76, 96) into slots (51, 71, 91) which define an upper surface of the damper (56, 76, 96) improvements in cooling efficiency can be achieved. The slots (51, 71 91) are typically closed to reduce requirements with respect to pressure differentials. However, open ended slots (51, 71, 91) with impingement jets (54, 74, 94) can also be provided. Typically, the slots (51, 71, 91) extend laterally across the dampers (56, 76, 96) but could also extend longitudinally with closed ends or one end open. By such an approach improved heat transfer is achieved without necessary increases in pressure gradients and flow rates.
摘要翻译：关于在燃气涡轮发动机（10）中的安装布置（50,70,90）来使用阻尼器（56,76,96），以便于冷却。已知提供开槽的上表面或山寨屋顶阻尼器以增强冷却效果。然而，不能优化冷却效率，特别是在安装装置的部件之间改善冷却效果可能是困难的，而不会有混合这种安装的燃气涡轮发动机（10）的总效率的降低。通过设置延伸穿过阻尼器（56,76,96）的冲击射流（54,75,94）到限定阻尼器（56,76,96）的上表面的狭槽（51,71,91）中，可以实现冷却效率。狭槽（51,71 91）通常是关闭的，以减少关于压差的要求。然而，也可以提供具有冲击射流（54,74,94）的开口槽（51,71,91）。通常，槽（51,71,91）横向延伸穿过阻尼器（56,76,96），但是也可以在封闭端或一端打开的情况下纵向延伸。通过这种方法，在不需要增加压力梯度和流速的情况下，可以实现改进的传热。

10. 发明授权

US09188018B2 Flap seal and sealing apparatus 有权
标题翻译：翼片密封和密封装置
公开(公告)号：US09188018B2
公开(公告)日：2015-11-17
申请号：US13551991
申请日：2012-07-18
申请人： Caner H. Helvaci , Glenn R. Paxton
发明人： Caner H. Helvaci , Glenn R. Paxton
IPC分类号： F01D11/00
CPC分类号： F01D11/005 , F05D2240/57 , F16J15/0887
摘要： A sealing plate for sealing a gap between two primary sealing plates is provided. The sealing plate has a sealing portion and a connector portion, wherein the sealing portion has a width which is greater than a width of the connector portion. An apparatus for sealing a gap between two structural components of a turbine, the apparatus including a plurality of primary sealing components, and at least one sealing plate is also provided, as is a turbine having a plurality of structural components with a gap between said structural components, wherein the gap is sealed by a plurality of sealing components, the sealing components comprising a plurality of primary sealing components and at least one sealing plate.
摘要翻译：提供用于密封两个主密封板之间的间隙的密封板。密封板具有密封部分和连接器部分，其中密封部分的宽度大于连接器部分的宽度。还提供了一种用于密封涡轮机的两个结构部件之间的间隙的设备，该设备包括多个主要密封部件和至少一个密封板，以及具有多个结构部件的涡轮机，所述结构部件在所述结构部件，其中所述间隙由多个密封部件密封，所述密封部件包括多个主密封部件和至少一个密封板。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式