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公开(公告)号：US5902093A
公开(公告)日：1999-05-11
申请号：US916386
申请日：1997-08-22
摘要： A rotor blade includes a dovetail and an airfoil joined thereto. The airfoil includes first and second spaced apart sides joined together laterally at opposite leading and trailing edges, and spanwise at a root and opposite tip. A serpentine cooling circuit extends inside the airfoil for channeling air therethrough for cooling the blade. The serpentine circuit includes first and second passes and a first bend therebetween for firstly receiving the cooling air in turn from the dovetail. A tip circuit is disposed between the tip and the serpentine circuit at the first bend for separating the tip from the first bend and providing cooling thereof near the trailing edge.
摘要翻译： 转子叶片包括燕尾榫和连接到其上的翼型件。 翼型件包括在相对的前缘和后缘处横向连接在一起的第一和第二间隔开的侧面，并且在根部和相对的尖端处展开。 蛇形冷却回路在翼型件的内部延伸，用于将空气引导通过以冷却叶片。 蛇形回路包括第一通道和第二通道以及在其间的第一弯头，用于首先从燕尾接收冷却空气。 尖端电路在第一弯曲处设置在尖端和蛇形电路之间，用于将尖端与第一弯曲部分离并在后缘附近提供冷却。
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公开(公告)号：US06193465B1
公开(公告)日：2001-02-27
申请号：US09161299
申请日：1998-09-28
IPC分类号： B63H300
CPC分类号： B23P15/04 , F01D5/189 , F01D5/20 , Y10T29/49343
摘要： A gas turbine engine airfoil is manufactured by forming an internal retention seat in two complementary airfoil parts. An insert is fabricated for retention in the seat. The two parts are assembled with the insert disposed in the seat therebetween. The parts are then bonded together to trap the insert therein to collectively define the airfoil. The insert and seat may be precisely fabricated for improving the efficiency of the airfoil.
摘要翻译： 通过在两个互补翼型件中形成内部保持座来制造燃气涡轮发动机翼型件。 制造用于保持在座中的插入件。 这两个部件与插入件组装在其间的座位中。 然后将这些部件结合在一起以将其中的插入物捕获以共同限定翼型件。 可以精确地制造插入件和座椅以提高翼型件的效率。
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公开(公告)号：US5993150A
公开(公告)日：1999-11-30
申请号：US8558
申请日：1998-01-16
申请人： Gary C. Liotta , Paul J. Acquaviva
发明人： Gary C. Liotta , Paul J. Acquaviva
CPC分类号： F01D11/24 , F01D11/10 , F05D2260/201 , Y02T50/67 , Y02T50/676
摘要： A turbine shroud includes a panel having a forward hook and an aft hook spaced therefrom. A primary cooling circuit extends through the panel adjacent the forward hook, and has a primary inlet for receiving primary air at a first pressure, and a primary outlet for discharging the primary air. A secondary cooling circuit extends through the panel adjacent the aft hook independently of the primary circuit. The secondary circuit includes a secondary inlet for receiving secondary air at a second pressure different than the first pressure, and a secondary outlet for discharging the secondary air. The dual cooled shroud accommodates differential gas pressure through the turbine.
摘要翻译： 涡轮机罩包括具有与其分开的前钩和后钩的面板。 主冷却回路延伸穿过邻近前钩的面板，并且具有用于接收第一压力的一次空气的主入口和用于排出一次空气的主出口。 二次冷却回路独立于主回路而延伸穿过靠近后钩的面板。 次级回路包括用于接收不同于第一压力的第二压力的二次空气的次级入口和用于排出二次空气的次级出口。 双冷却罩容纳通过涡轮机的差压气体压力。
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公开(公告)号：US6099252A
公开(公告)日：2000-08-08
申请号：US192227
申请日：1998-11-16
CPC分类号： F01D5/187
摘要： A gas turbine engine airfoil includes an axial serpentine cooling circuit therein. A plurality of the serpentine circuits are preferably stacked in a radial row along the airfoil trailing edge for cooling thereof.
摘要翻译： 燃气涡轮发动机翼型件包括其中的轴向蛇形冷却回路。 多个蛇形回路优选地沿翼型后缘沿径向排堆叠以进行冷却。
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公开(公告)号：US06183198B2
公开(公告)日：2001-02-06
申请号：US09192229
申请日：1998-11-16
IPC分类号： F01D518
CPC分类号： F01D5/186 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and spaced apart from each other therebetween to define a leading edge channel extending longitudinally from a root to a tip of the airfoil. A plurality of film cooling holes extend through the leading edge and are disposed in flow communication with the leading edge channel. An isolation plenum extends along the first sidewall and adjacent the leading edge channel, and is separated therefrom by a partition having a plurality of inlet holes. A plurality of film cooling gill holes extend through the first sidewall, and are disposed in flow communication with the isolation plenum. Cooling air is channeled from the leading edge channel to the isolation plenum for feeding the gill holes with reduced pressure air.
摘要翻译： 燃气涡轮发动机翼型件包括在相对的前缘和后缘处连接在一起并且彼此间隔开的第一和第二侧壁，以限定从叶片纵向延伸到翼型的尖端的前缘通道。 多个膜冷却孔延伸穿过前缘并且与前缘通道流体连通地设置。 隔离通风室沿着第一侧壁延伸并且邻近前缘通道，并且通过具有多个入口孔的隔板与其隔开。 多个薄膜冷却鳃孔延伸穿过第一侧壁，并且与隔离气室成流动连通地设置。 冷却空气从前缘通道引导到隔离气室，用于通过减压空气供给鳃孔。
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公开(公告)号：US6036441A
公开(公告)日：2000-03-14
申请号：US192225
申请日：1998-11-16
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and extending longitudinally from a root to a tip. The sidewalls are spaced apart from each other to define in part first and second adjoining flow chambers extending longitudinally therein, and defined in additional part by corresponding first and second partitions disposed between the sidewalls. The second partition is common to both chambers, and both partitions include respective pluralities of first and second inlet holes sized to meter cooling air therethrough in series between the chambers.
摘要翻译： 燃气涡轮发动机翼型件包括在相对的前缘和后缘处连接在一起的第一和第二侧壁，并且从根部到纵向延伸到尖端。 侧壁彼此间隔开，以限定在其中纵向延伸的第一和第二毗邻流动室，并且由另一部分由设置在侧壁之间的对应的第一和第二隔板限定。 第二分隔件对两个腔室是共同的，并且两个分隔件包括相应的多个第一入口孔和第二入口孔，其尺寸设计成用于计量串联在腔室之间的冷却空气。
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