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公开(公告)号：US20120251295A1
公开(公告)日：2012-10-04
申请号：US13408251
申请日：2012-02-29
IPC分类号： F01D5/18
CPC分类号： F23R3/002 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F23R2900/03041
摘要： A component of a gas turbine engine is provided. The component includes an external wall which, in use, is exposed on one surface thereof to working gas flowing through the engine. The component further includes effusion cooling holes formed in the external wall. In use, cooling air blows through the cooling holes to form a cooling film on the surface of the external wall exposed to the working gas. The component further includes an air inlet arrangement which receives the cooling air for distribution to the cooling holes. The component further includes a plurality of metering feeds and a plurality of supply plena. The metering feeds meter the cooling air from the air inlet arrangement to respective of the supply plena, which in turn supply the metered cooling air to respective portions of the cooling holes.
摘要翻译： 提供燃气涡轮发动机的部件。 该组件包括外壁，其在使用中在其一个表面上暴露于流过发动机的工作气体。 该部件还包括形成在外壁中的排出冷却孔。 在使用中，冷却空气吹过冷却孔，在暴露于工作气体的外壁的表面上形成冷却膜。 该部件还包括一个空气入口装置，其接收用于分配到冷却孔的冷却空气。 该组件还包括多个计量馈送和多个供应斑点。 计量供给将来自进气装置的冷却空气测量到供应凹槽的相应位置，该供应凹槽又将计量的冷却空气供应到冷却孔的相应部分。
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公开(公告)号：US20120057961A1
公开(公告)日：2012-03-08
申请号：US13216824
申请日：2011-08-24
CPC分类号： F01D11/10 , F01D11/122 , F05D2240/11 , F05D2260/202 , Y02T50/676 , Y10T29/4932
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 mainstream flow of the working gas passes through the passages formed between adjacent turbine blades. 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 has swirl directions which are co-directionally aligned with the swirl directions of the mainstream flow at the segment.
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，工作气体的主要流动通过形成在相邻涡轮叶片之间的通道。 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具有与该段主流流动的涡流方向共同对齐的旋流方向。
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公开(公告)号：US20120219401A1
公开(公告)日：2012-08-30
申请号：US13368718
申请日：2012-02-08
IPC分类号： F01D9/02
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。
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公开(公告)号：US20120027576A1
公开(公告)日：2012-02-02
申请号：US13177151
申请日：2011-07-06
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。
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公开(公告)号：US20120082567A1
公开(公告)日：2012-04-05
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
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。
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公开(公告)号：US20120076645A1
公开(公告)日：2012-03-29
申请号：US13207784
申请日：2011-08-11
申请人： Ian TIBBOTT
发明人： Ian TIBBOTT
IPC分类号： F01D5/08
CPC分类号： F01D11/24 , B60G21/055 , F01D5/187 , F01D9/065 , F01D11/001 , F05D2240/11 , F05D2240/15 , F05D2240/81 , F05D2250/182 , F05D2250/22 , F05D2250/25 , F05D2250/294 , F05D2250/75 , F05D2260/204 , F05D2260/2212 , F05D2260/2214
摘要： A component of a turbine stage of a gas turbine engine is provided. The component forms an endwall for the working gas annulus of the stage. The component has one or more internal passages behind the endwall which, in use, carry a flow of cooling air providing convective cooling for the component at the endwall. Each passage is formed by a plurality of straight passage sections. The passage sections connect end-to-end such that the connections between nearest-neighbour passage sections form angled bends. A first portion of the passage sections lie in a first plane. A second portion of the passage sections lie in a second plane which is spaced from and parallel to the first plane. A third portion of the passage sections extend between the first and the second planes.
摘要翻译： 提供了一种燃气轮机的涡轮级的部件。 该部件形成工作台的工作气体环的端壁。 该部件在端壁后面具有一个或多个内部通道，其在使用中承载冷却空气流，为端壁处的部件提供对流冷却。 每个通道由多个直的通道部分形成。 通道部分端对端连接，使得最近相邻的通道部分之间的连接形成倾斜的弯曲。 通道部分的第一部分位于第一平面中。 通道部分的第二部分位于与第一平面间隔开并平行于第一平面的第二平面中。 通道部分的第三部分在第一和第二平面之间延伸。
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公开(公告)号：US20120082568A1
公开(公告)日：2012-04-05
申请号：US13232584
申请日：2011-09-14
申请人： Ian TIBBOTT , Dougal R. JACKSON , Rory J. CLARKSON
发明人： Ian TIBBOTT , Dougal R. JACKSON , Rory J. CLARKSON
IPC分类号： F01D5/18
CPC分类号： F01D5/081 , F01D5/082 , F01D5/085 , F01D5/087 , F01D5/088 , F01D5/3007 , F01D5/3015 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A cooling arrangement is provided for a turbine disc of a gas turbine engine. The turbine disc has a plurality of circumferentially spaced disc posts forming fixtures therebetween for a row of turbine blades. Each turbine blade has an attachment formation which engages at a respective fixture, a platform radially outwardly of the attachment formation such that the adjacent platforms of the row form an inner endwall for the working gas annulus of the engine, and an aerofoil which extends radially outwardly from the platform. A respective cavity is formed between an exposed radially outer surface of each disc post and the inner endwall. The cooling arrangement has at each disc post, a cooling plate located in the respective cavity and spaced radially outwardly from the exposed outer surface of the disc post to form a cooling channel between the cooling plate and the exposed outer surface.
摘要翻译： 为燃气轮机的涡轮盘提供冷却装置。 涡轮盘具有多个周向间隔开的盘柱，在其间形成用于一排涡轮叶片的夹具。 每个涡轮机叶片具有附接结构，其接合在相应的固定装置处，附接结构的径向向外的平台，使得该排的相邻平台形成用于发动机的工作气体环的内端壁，以及一个径向向外延伸的翼型 从平台。 在每个盘柱的暴露的径向外表面和内端壁之间形成相应的空腔。 冷却装置在每个盘柱处具有位于相应空腔中的冷却板，并且与盘柱的暴露的外表面径向向外间隔开，以在冷却板和暴露的外表面之间形成冷却通道。
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公开(公告)号：US20130017060A1
公开(公告)日：2013-01-17
申请号：US13544211
申请日：2012-07-09
申请人： John H. BOSWELL , Ian TIBBOTT
发明人： John H. BOSWELL , Ian TIBBOTT
IPC分类号： F01D11/20
CPC分类号： F01D11/24 , F01D25/12 , F01D25/14 , F01D25/145 , Y02T50/675
摘要： An arrangement for heating and cooling a turbine casing of a gas turbine engine, the arrangement comprising an inboard duct, adjacent to an inboard surface of the turbine casing, an outboard facing wall of the inboard duct having a plurality of impingement holes opening towards the inboard surface of the casing, through which temperature control fluid can pass from within the inboard duct to impinge upon the inboard surface of the turbine casing.
摘要翻译： 一种用于加热和冷却燃气涡轮发动机的涡轮壳体的装置，该装置包括与涡轮机壳体的内侧表面相邻的内侧管道，内侧管道的外侧面向壁具有朝向内侧开口的多个冲击孔 壳体的表面，温度控制流体可以通过该表面从内侧管道内通过以撞击到涡轮机壳体的内侧表面。
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公开(公告)号：US20110255985A1
公开(公告)日：2011-10-20
申请号：US13053928
申请日：2011-03-22
IPC分类号： F01D5/14
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延伸穿过 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。
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公开(公告)号：US20110067378A1
公开(公告)日：2011-03-24
申请号：US12876576
申请日：2010-09-07
申请人： Ian TIBBOTT , Dougal Jackson
发明人： Ian TIBBOTT , Dougal Jackson
CPC分类号： F01D25/32 , B01D45/04 , B01D46/0039 , F01D9/065 , F02C7/18 , F05D2240/81 , F05D2250/181 , F05D2250/184 , F05D2260/202 , F05D2260/607 , Y02T50/67 , Y02T50/671 , Y02T50/675 , Y02T50/676
摘要： A separator device is provided for separating dirt particles from a flow of cooling air fed to airfoils of the turbine section of a gas turbine engine. In use the separator device extends across a conduit which bypasses the combustor of the engine to convey pressurised cooling air carrying dirt particles from the compressor section of the engine to openings which direct the air into the airfoils. The separator device is configured to direct a first portion of the impinging cooling air flow away from the openings and to allow a second portion of the impinging cooling air to continue to the openings. The first portion of cooling air has a higher concentration of the coarsest dirt particles carried by the cooling air than the second portion of cooling air.
摘要翻译： 提供了一种分离器装置，用于将灰尘颗粒与供给到燃气涡轮发动机的涡轮部分的翼型件的冷却空气流分离。 在使用中，分离器装置延伸穿过绕过发动机的燃烧器的导管，以将承载有污染颗粒的加压冷却空气从发动机的压缩机部分输送到将空气引导到翼型件的开口。 分离器装置构造成将冲击的冷却空气流的第一部分引导离开开口并允许冲击的冷却空气的第二部分继续到开口。 冷却空气的第一部分比冷却空气的第二部分具有比冷却空气携带的最粗糙的污垢颗粒更高的浓度。
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