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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：US20110135455A1
公开(公告)日：2011-06-09
申请号：US12956501
申请日：2010-11-30
申请人： Yi WANG , Miles T. TRUMPER , Mark J. WILSON , Peter IRELAND , Robert C. CHAMBERS
发明人： Yi WANG , Miles T. TRUMPER , Mark J. WILSON , Peter IRELAND , Robert C. CHAMBERS
IPC分类号： F04D29/58
摘要： An air-cooled oil cooler for the wall of an air flow passage of a gas turbine engine is provided, the oil cooler allowing improved heat exchange performance to be obtained. This is achieved by: (I) diverting air flow from the inner side of the oil cooler towards the outer side of the oil cooler, (ii) enhancing heat exchange performance at the leading edge of the cooler, and/or (iii) suppressing airflow wake at the trailing edge of the cooler.
摘要翻译： 提供了一种用于燃气涡轮发动机的空气流动通道的壁的风冷式油冷却器，能够获得改善的热交换性能的油冷却器。 这通过以下方式实现：（I）将空气流从油冷却器的内侧转向油冷却器的外侧，（ii）提高冷却器前缘处的热交换性能，和/或（iii）抑制 气流在冷却器的后缘处醒来。
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公开(公告)号：US20110317740A1
公开(公告)日：2011-12-29
申请号：US13161899
申请日：2011-06-16
申请人： Peter IRELAND , Andrew WILSON , Steven THORPE , Damian MARTIN
发明人： Peter IRELAND , Andrew WILSON , Steven THORPE , Damian MARTIN
IPC分类号： G01K7/02
CPC分类号： G01K13/02 , G01K13/028
摘要： A high temperature measurement probe comprises an elongate probe body having a measuring head which in use is located in a hot fluid flow. The probe further comprises a thermocouple extending along the interior of the probe body to terminate at a temperature-sensing thermocouple junction inside the measuring head. The probe body has internal passages for circulation of a coolant fluid therein. The measuring head contains a channel, one end of the channel forming an inlet for receiving hot fluid from the hot fluid flow and another end of the channel forming an outlet for discharging the hot fluid received at the inlet. Between the inlet and the outlet a section of the channel extends along the length direction of the probe body. The thermocouple runs along the section of the channel with the thermocouple junction proximate the upstream end of the section.
摘要翻译： 高温测量探头包括具有测量头的细长探针体，测量头在使用中位于热流体流中。 探头还包括沿着探针本体的内部延伸的热电偶，以终止于测量头内的温度感测热电偶结。 探针体具有用于在其中循环冷却剂流体的内部通道。 测量头包含通道，通道的一端形成用于从热流体流接收热流体的入口，并且通道的另一端形成用于排出在入口处接收的热流体的出口。 在入口和出口之间，通道的一部分沿探头主体的长度方向延伸。 热电偶沿着通道的部分延伸，热电偶接头靠近该部分的上游端。
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