公开(公告)号：US08596961B2

公开(公告)日：2013-12-03

申请号：US12458905

申请日：2009-07-27

申请人： Ian Tibbott ,  Ian W R Harrogate

发明人： Ian Tibbott ,  Ian W R Harrogate

IPC分类号： F01D5/18

CPC分类号： F01D5/188 ,  F01D9/041 ,  F05D2230/21 ,  F05D2240/126

摘要： Within aerofoils, and in particular nozzle guide vane aerofoils in gas turbine engines problems can occur with regard to coolant flows from respective inlets at opposite ends of a cavity within the aerofoil. The cavity generally defines a hollow core and unless care is taken coolant flow can pass directly across the internal cavity. Previously baffle plates were inserted within the cavity to prevent such direct jetting across the cavity. Such baffle plates are subject to additional costs as well as potential unreliability problems. Baffles formed integrally with a wall within the aerofoil allow more reliability with regard to positioning as well as consistency of performance. The baffles can be perpendicular, upward or downwardly orientated or have a compound angle.

摘要翻译： 在机翼中，特别是在燃气涡轮发动机中的喷嘴引导叶片机翼，关于来自机翼中的空腔的相对端处的相应入口的冷却剂流可能发生问题。 空腔通常限定中空芯，除非注意，冷却剂流可以直接穿过内部空腔。 以前的挡板被插入腔内以防止这种直接喷射穿过空腔。 这种挡板受到额外的成本以及潜在的不可靠性问题的影响。 在机翼内与墙壁一体形成的挡板允许在定位方面更高的可靠性以及性能的一致性。 挡板可以垂直，向上或向下定向或具有复合角度。

公开(公告)号：US5417545A

公开(公告)日：1995-05-23

申请号：US205083

申请日：1994-03-03

申请人： Ian W. R. Harrogate

发明人： Ian W. R. Harrogate

IPC分类号： F01D5/18 ,  F01D9/02 ,  F01D9/04 ,  F02C7/00 ,  F02C7/18 ,  F01D9/06

CPC分类号： F01D5/186 ,  F01D9/02 ,  F01D9/023 ,  F05D2240/81

摘要： A turbine nozzle assembly includes an annular array of nozzle guide vanes located downstream of a combustor discharge casing. Each nozzle guide vane includes an aerofoil portion which is cast integrally with a radially inner platform and a radially outer platform. The radially outer platform of each nozzle guide vane has an extension to provide a smooth transition of the gases from the combustor discharge casing to the nozzle guide vanes. Two rows of cooling holes are provided in the extension to film cool the inner surface of the platform. A method is described to calculate the diameter of each of the cooling holes so that a uniform flow of cooling air passes over the inner surface of the each platform.

摘要翻译： 涡轮喷嘴组件包括位于燃烧器排出壳体下游的喷嘴导向叶片的环形阵列。 每个喷嘴导向叶片包括与径向内部平台和径向外部平台一体铸造的翼面部分。 每个喷嘴引导叶片的径向外部平台具有延伸部以提供气体从燃烧器排出壳体到喷嘴导向叶片的平滑过渡。 在延伸部分设有两排冷却孔，以使平台的内表面冷却。 描述了一种计算每个冷却孔的直径的方法，使得均匀的冷却空气流通过每个平台的内表面。

公开(公告)号：US07648333B2

公开(公告)日：2010-01-19

申请号：US11491080

申请日：2006-07-24

申请人： Ian Tibbott ,  Roderick M Townes ,  Ian W R Harrogate

发明人： Ian Tibbott ,  Roderick M Townes ,  Ian W R Harrogate

IPC分类号： F04D29/58

CPC分类号： F01D5/081 ,  F01D5/225 ,  F01D25/12 ,  F05D2240/81 ,  F05D2250/292 ,  F05D2260/201 ,  Y02T50/676

摘要： A cooling arrangement 21 for use within a gas turbine engine comprises a first shroud or platform 26 incorporating coolant passages 25 and a second shroud or platform 28. Generally, each platform or shroud 26, 28 will incorporate a pressure portion and a suction portion, with the pressure portion incorporating the coolant passages 25 through which the coolant flow 27 becomes incident on a surface 40 of the suction portion of the second shroud 28. The surface 40 is inclined or tapered towards the passage 25, such that there is limited direct impingement upon a front edge 39 of the surface 40. The coolant flow 27 thereby remains adjacent to the surface 40 for a longer period and so enhances cooling efficiency.

摘要翻译： 在燃气涡轮发动机中使用的冷却装置21包括结合有冷却剂通道25和第二护罩或平台28的第一护罩或平台26.通常，每个平台或护罩26,28将包括压力部分和吸入部分， 包括冷却剂通道25的压力部分，冷却剂流27通过该压力部分入射到第二护罩28的吸入部分的表面40上。表面40朝向通道25倾斜或渐缩，使得直接撞击到 表面40的前边缘39.因此，冷却剂流27保持与表面40相邻较长的时间，从而提高了冷却效率。

公开(公告)号：US08678751B2

公开(公告)日：2014-03-25

申请号：US12461814

申请日：2009-08-25

申请人： Ian Tibbott ,  Ian W. R. Harrogate

发明人： Ian Tibbott ,  Ian W. R. Harrogate

IPC分类号： F01D5/00

CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2220/3212 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/14 ,  F05D2250/25 ,  F05D2260/2212

摘要： Within components such as high pressure turbine blades and aerofoils in a gas turbine engine it is important to provide cooling such that these components remain within acceptable operational parameters. Typically, film cooling as well as convective cooling is utilized. Film cooling requires holes from a feed passage from which the coolant is presented upon an external surface to develop the film. The holes themselves can create cooling through convective cooling effects. In order to maximize the convective cooling effect holes are created which have an indirect path about a direct line between an inlet and an outlet for the hole. By creating an indirect path in the form of a helix or spiral which in turn may have a variable cross sectional area from the inlet to the outlet control of coolant flow can be achieved. The inlet may have a bell mouth shape while the hole may have a slot or elliptical cross section to achieve greater diffusion of the coolant flow in order to create an improved exit blow rate for instant film development.

摘要翻译： 在诸如燃气轮机发动机中的高压涡轮机叶片和翼型的部件内，重要的是提供冷却，使得这些部件保持在可接受的操作参数内。 通常，利用薄膜冷却以及对流冷却。 薄膜冷却需要来自进料通道的孔，冷却剂从该进料通道呈现在外表面上以显影薄膜。 孔本身可以通过对流冷却效果产生冷却。 为了最大限度地提高对流冷却效果，产生了孔，该孔具有围绕孔的入口和出口之间的直线的间接路径。 通过产生螺旋或螺旋形式的间接路径，从而可以实现从入口到出口控制冷却剂流动的可变横截面面积。 入口可以具有喇叭口形状，而孔可以具有狭槽或椭圆形横截面，以实现冷却剂流的更大扩散，以便为即时胶片显影产生改进的吹出速率。

公开(公告)号：US5470198A

公开(公告)日：1995-11-28

申请号：US299061

申请日：1994-08-31

申请人： Ian W. R. Harrogate ,  David H. Taylor ,  Arthur B. Griffin ,  David W. Tuson

发明人： Ian W. R. Harrogate ,  David H. Taylor ,  Arthur B. Griffin ,  David W. Tuson

IPC分类号： F01D9/02 ,  F01D9/04 ,  F01D11/00 ,  F02C7/00 ,  F02C7/28 ,  F01D5/18

CPC分类号： F01D9/023 ,  F01D11/005 ,  Y02T50/671 ,  Y02T50/675

摘要： A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly extending between nozzle guide vanes and combustion chamber discharge nozzles. The nozzle guide vanes have platforms having extensions which in one embodiment overlap the downstream ends of the discharge nozzles. Cooling air is supplied to the upstream edge portions of the platforms through holes in flanges on the discharge nozzles. The seal assembly defines a chamber adjacent the platform extensions which is supplied with cooling air through metering holes in the seal assembly which provides part of a boundary for a cooling air chamber, the boundary of the chamber having cooling air holes for metering cooling air into the chamber to cool the upstream portion of the nozzle guide vane outer platforms. Cooling air exits the chamber through holes in the platform extensions to film cool them.

摘要翻译： 燃气涡轮发动机中的冷却和密封装置包括在喷嘴导向叶片和燃烧室排出喷嘴之间延伸的密封组件。 喷嘴导叶具有具有延伸部的平台，在一个实施例中，该延伸部与排放喷嘴的下游端重叠。 冷却空气通过排放喷嘴上的凸缘中的孔被供应到平台的上游边缘部分。 密封组件限定了邻近平台延伸部分的室，该冷却空气通过密封组件中的计量孔供应冷却空气，该冷却空气为冷却空气室提供了一部分边界，该室的边界具有冷却空气孔，用于将冷却空气计入 以冷却喷嘴导向叶片外平台的上游部分。 冷却空气通过平台延伸部分中的孔离开室以使其冷却。

公开(公告)号：US5407319A

公开(公告)日：1995-04-18

申请号：US207626

申请日：1994-03-09

申请人： Ian W. R. Harrogate ,  David H. Taylor ,  Arthur B. Griffin ,  David W. Tuson

发明人： Ian W. R. Harrogate ,  David H. Taylor ,  Arthur B. Griffin ,  David W. Tuson

IPC分类号： F01D9/02 ,  F01D9/04 ,  F01D11/00 ,  F02C7/00 ,  F02C7/28 ,  F01D5/18

CPC分类号： F01D9/023 ,  F01D11/005 ,  Y02T50/671 ,  Y02T50/675

摘要： A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly (42,30) extending between nozzle guide vanes (20) and combustion chamber discharge nozzles (22). The nozzle guide vanes (20) have platforms (34,36) having extensions (34A,36A) which in one embodiment overlap the downstream ends of the discharge nozzles (22). Cooling air is supplied to the upstream edge portions of the platforms through holes (26,28C) in flanges (24,28) on the discharge nozzles (22). The seal assembly (42,30) defines a chamber (58,70) adjacent the platform extensions which is supplied with cooling air through metering holes (56,68) in the seal assembly. Cooling air exits the chamber (58,70) through holes (34B,36B) in the platform extensions to film cool them.

摘要翻译： 燃气涡轮发动机中的冷却和密封装置包括在喷嘴导向叶片（20）和燃烧室排出喷嘴（22）之间延伸的密封组件（42,30）。 喷嘴导向叶片（20）具有在一个实施例中与排放喷嘴（22）的下游端重叠的延伸部（34A，36A）的平台（34,36）。 冷却空气通过排放喷嘴（22）上的凸缘（24,28）中的孔（26,28C）供应到平台的上游边缘部分。 密封组件（42,30）限定了邻近平台延伸部的腔室（58,70），其通过密封组件中的计量孔（56,68）供应冷却空气。 冷却空气通过平台延伸部中的孔（34B，36B）离开室（58,70），以使其冷却。