公开(公告)号：US09068472B2

公开(公告)日：2015-06-30

申请号：US13368718

申请日：2012-02-08

申请人： Anthony J. Rawlinson ,  Peter Ireland ,  Lynne H. Turner ,  Ian Tibbott

发明人： Anthony J. Rawlinson ,  Peter Ireland ,  Lynne H. Turner ,  Ian Tibbott

IPC分类号： F01D5/18 ,  F01D9/06 ,  F01D11/08 ,  F01D25/12 ,  F01D11/12

CPC分类号： F01D25/12 ,  F01D5/186 ,  F01D5/187 ,  F01D9/06 ,  F01D11/08 ,  F01D11/122 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/20 ,  F05D2260/202

摘要： A component of a turbine stage of a gas turbine engine is provided, the component forming an endwall for the working gas annulus of the stage. The component has one or more internal plena behind the endwall which, in use, contain a flow of cooling air. The component further has a plurality of exhaust holes in the endwall. The holes connect the plena to a gas-washed surface of the endwall such that the cooling air effuses through the holes to form a cooling film over the gas-washed surface. Each exhaust hole has a flow cross-sectional area which is greater at an intermediate position between the entrance of the hole from the respective plenum and the exit of the hole to the gas-washed surface than it is at said exit.

摘要翻译： 提供了一种燃气涡轮发动机的涡轮级的部件，该部件形成了用于工作台的工作气体环的端壁。 该组件在端壁后面具有一个或多个内部斑点，其在使用中包含冷却空气流。 该部件还在端壁中具有多个排气孔。 这些孔将绦虫连接到端壁的气体洗涤表面，使得冷却空气通过孔流出，以在气洗表面上形成冷却膜。 每个排气孔的流动横截面面积在从相应的压力室的孔的入口与孔的出口到气体洗涤表面之间的中间位置处比在所述出口处更大。

公开(公告)号：US08714918B2

公开(公告)日：2014-05-06

申请号：US13177151

申请日：2011-07-06

申请人： Ian Tibbott ,  Peter Ireland ,  Anthony J Rawlinson ,  Lynne H Turner

发明人： Ian Tibbott ,  Peter Ireland ,  Anthony J Rawlinson ,  Lynne H Turner

IPC分类号： F01D11/10

CPC分类号： F01D11/08 ,  F01D11/10 ,  F01D11/24 ,  F01D25/12 ,  F05D2240/11 ,  F05D2250/313 ,  F05D2250/314 ,  F05D2260/202 ,  Y02T50/676 ,  Y10T29/49323

摘要： A shroud segment for a turbine stage of a gas turbine engine forms an endwall for the working gas annulus of the stage. The segment also provides a close clearance to the tips of a row of turbine blades which sweep across the segment. In use a leakage flow of the working gas passes through the clearance gap between the blade tips and the segment. The segment has a plurality of cooling holes and respective air feed passages for the cooling holes. The cooling holes are distributed over that part of the gas-washed surface of the segment which is swept by the blade tips. The cooling holes deliver, in use, cooling air which spreads over the gas-washed surface. The feed passages are configured such that the delivered air opposes the leakage flow of the working gas.

摘要翻译： 用于燃气涡轮发动机的涡轮级的护罩段形成用于工作台的工作气体环的端壁。 该段还提供了跨越段的一排涡轮机叶片的尖端的紧密间隙。 在使用中，工作气体的泄漏流通过叶片尖端和段之间的间隙。 该段具有用于冷却孔的多个冷却孔和各自的空气供给通道。 冷却孔分布在由叶片尖端扫过的段的气体洗涤表面的那部分上。 冷却孔在使用中提供散布在气洗表面上的冷却空气。 供给通道构造成使得所输送的空气与工作气体的泄漏流相反。

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。

公开(公告)号：US08133032B2

公开(公告)日：2012-03-13

申请号：US12327030

申请日：2008-12-03

申请人： Ian Tibbott ,  Edwin Dane ,  Dougal Richard Jackson

发明人： Ian Tibbott ,  Edwin Dane ,  Dougal Richard Jackson

IPC分类号： F01D5/14 ,  F01D5/18

CPC分类号： F01D5/20 ,  F01D11/08 ,  Y02T50/673

摘要： A rotor blade has a tip with an outer face including at least two channels which each extend to an outlet in the vicinity of the trailing edge. Accordingly, gas leakage around the tip must cross at least three walls, at least in the vicinity of the uncovered turning region near the trailing edge of the blade. Leakage gas entering the channels will tend to create a vortex and pass along the channel to the outlet.

摘要翻译： 转子叶片具有带有外表面的末端，该外表面包括至少两个通道，每个通道延伸到后缘附近的出口。 因此，尖端附近的气体泄漏必须至少跨越至少三个壁，至少在叶片后缘附近的未覆盖的转动区域附近。 进入通道的泄漏气体将倾向于产生涡流并沿着通道传递到出口。

公开(公告)号：US07850428B2

公开(公告)日：2010-12-14

申请号：US11707997

申请日：2007-02-20

申请人： Ian Tibbott ,  Edwin Dane

发明人： Ian Tibbott ,  Edwin Dane

IPC分类号： F01D5/08 ,  F01D5/18

CPC分类号： F01D5/186 ,  F05D2240/12 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/16 ,  F05D2250/71 ,  F05D2260/221

摘要： An aerofoil 20 for a gas turbine engine includes a root portion 22, a tip portion 24 located radially outwardly of the root portion 22, leading and trailing edges 26, 28 extending between the root portion 22 and the tip portion 24 and an internal cooling passage 34. The aerofoil 20 includes a plurality of cooling fluid discharge apertures 36 extending between the root portion 22 and the tip portion 24 in a trailing edge region 28a to discharge cooling fluid from the internal cooling passage 34 to an outer surface 31 of the aerofoil in the trailing edge region 28a and thereby provide a cooling film in the trailing edge region 28a. The cooling fluid discharge apertures 36 are arranged so that the flow rate of the cooling fluid discharged from the internal cooling passage 34 to the outer surface trailing edge region 28a varies between the root portion 22 and the tip portion 24.

摘要翻译： 用于燃气涡轮发动机的机翼20包括根部22，位于根部22的径向外侧的前端部24，在根部22和顶端部24之间延伸的前缘26和后缘26以及内部冷却通道 机翼20包括在后缘区域28a中在根部22和尖端部分24之间延伸的多个冷却流体排放孔36，以将冷却流体从内部冷却通道34排出到机翼的外表面31 后缘区域28a，从而在后缘区域28a中提供冷却膜。 冷却流体排出孔36被布置成使得从内部冷却通道34排出到外表面后缘区域28a的冷却流体的流量在根部22和尖端部24之间变化。

公开(公告)号：US20100124484A1

公开(公告)日：2010-05-20

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： F01D25/12

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：US06257831B1

公开(公告)日：2001-07-10

申请号：US09425175

申请日：1999-10-22

申请人： Michael Papple ,  William Abdel-Messeh ,  Ian Tibbott

发明人： Michael Papple ,  William Abdel-Messeh ,  Ian Tibbott

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  B22C9/10 ,  F05D2230/21 ,  F05D2240/126 ,  F05D2260/22141

摘要： A cooled gas turbine engine airfoil comprises a flow deflector arrangement adapted to re-direct a cooling fluid away from an unfilled opening left by a support member of a casting core used during the casting of the airfoil. The provision of the flow deflector arrangement advantageously allows for a larger core support, thereby facilitating the manufacture of the airfoil.

摘要翻译： 冷却的燃气涡轮发动机翼型件包括导流装置，该导流装置适于将冷却流体重新引导离开由在铸造机翼期间使用的铸芯的支撑构件留下的未填充开口。 提供导流装置有利地允许更大的芯支撑，从而有利于翼型件的制造。

公开(公告)号：US09074484B2

公开(公告)日：2015-07-07

申请号：US13207960

申请日：2011-08-11

申请人： Ian Tibbott ,  Oliver C T Tibbott

发明人： Ian Tibbott ,  Oliver C T Tibbott

IPC分类号： F01D5/18 ,  F01D5/08

CPC分类号： F01D5/186 ,  F01D5/081 ,  F01D5/187 ,  F05D2230/12 ,  F05D2240/304 ,  F05D2240/81

摘要： A cooled turbine rotor blade for a gas turbine engine is provided. The engine has an annular flow path for conducting working fluid though the engine. The blade has an aerofoil section for extending across the annular flow path. The blade further has a root portion radially inward of the aerofoil section for joining the blade to a rotor disc of the engine. The blade further has a platform between the aerofoil section and the root portion. The platform extends laterally relative to the radial direction of the engine to form an inner boundary of the annular flow path and to provide a rear overhang portion which projects in use towards a corresponding platform of a downstream nozzle guide vane. The platform contains at least one internal elongate plenum chamber for receiving cooling air. The longitudinal axis of the plenum chamber is substantially aligned with the circumferential direction of the engine. The plenum chamber supplies the cooling air to a plurality of exit holes formed in the external surface of the rear overhang portion to cool that portion.

摘要翻译： 提供了一种用于燃气涡轮发动机的冷却涡轮转子叶片。 发动机具有用于通过发动机传导工作流体的环形流动路径。 叶片具有用于延伸穿过环形流动路径的机翼部分。 叶片还具有用于将叶片接合到发动机的转子盘的机翼部分的径向内侧的根部分。 叶片还具有在机翼部分和根部之间的平台。 平台相对于发动机的径向方向横向延伸以形成环形流动路径的内边界，并提供在使用中向下游喷嘴引导叶片的相应平台突出的后悬伸部分。 平台包含至少一个用于接收冷却空气的内部细长的增压室。 增压室的纵向轴线基本上与发动机的圆周方向对准。 增压室将冷却空气供给到形成在后悬伸部分的外表面中的多个出口孔，以冷却该部分。

公开(公告)号：US08657576B2

公开(公告)日：2014-02-25

申请号：US12457450

申请日：2009-06-11

申请人： Ian Tibbott ,  Roderick M. Townes

发明人： Ian Tibbott ,  Roderick M. Townes

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/201

摘要： Cooling within aerofoils (30, 47, 67, 87) is a requirement in order that the materials from which the aerofoil (30, 47, 67, 87) is created can remain within acceptable operational parameters. Traditionally static pressure as well as enhanced dynamic pressure impingement flows have been utilized but there are problems with regard to achieving a necessary over pressure to avoid hot gas ingestion or reduced cooling effect. It will be appreciated that fluid flows and in particular coolant fluid flows must be used most appropriately in order to maintain operational efficiency. By providing a plurality of feed apertures (41, 61, 81) which are shaped to have an entry portion (51, 71, 91) which is generally elliptical and an exit portion (52, 72, 92) it is possible to grab and turn a proportion of a feed flow (44, 64, 84) for substantially perpendicular or other angular presentation to an opposed surface of a cooling chamber (42, 62, 82) within which cooling is required.

摘要翻译： 在机翼（30,77,67,87）内的冷却是要求，以便制造机翼（30,47,67,87）的材料可以保持在可接受的操作参数内。 已经使用传统的静压力和增强的动态压力冲击流，但是在实现必要的过压以避免热气体吸入或降低冷却效果方面存在问题。 应当理解，流体流动，特别是冷却剂流体流必须最适当地使用以保持操作效率。 通过设置多个进给孔（41,61,81），其形状为具有大致椭圆形的入口部分（51,71,91）和出口部分（52,72,92），可以抓取和 将进给流（44,64,84）的一部分用于基本垂直或其他角度呈现到需要冷却的冷却室（42,62,82）的相对表面。

公开(公告)号：US08419366B2

公开(公告)日：2013-04-16

申请号：US12458412

申请日：2009-07-10

申请人： Roderick M. Townes ,  Ian Tibbott ,  Edwin Dane

发明人： Roderick M. Townes ,  Ian Tibbott ,  Edwin Dane

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F01D5/187 ,  Y02T50/676

摘要： Cooling arrangements for blades, and in particular turbine blades utilizing gas turbine engines include impingement apertures with impingement jets, which improve cooling efficiency. By providing a leading passage, which is divided at least into a lower section and an upper section, the lower section can have a wall, which is solid for structural integrity while an upper section has impingement apertures for greater cooling efficiency.

摘要翻译： 叶片，特别是利用燃气涡轮发动机的涡轮叶片的冷却装置包括具有冲击射流的冲击孔，这提高了冷却效率。 通过提供至少分为下部和上部的引导通道，下部可具有壁，该壁为结构完整性而牢固，而上部具有用于更高冷却效率的冲击孔。